1 cronología de lanzamientos espaciales · masa seca en órbita: 1580 kg la sonda luna 9 fue la...

Cronología de lanzamientos espaciales 1

Eladio Miranda Batlle

[email protected]

Cronología de

Lanzamientos

Espaciales

Año 1966

Copyright © 2009 by Eladio Miranda Batlle. All rights reserved.

Los textos, imágenes y tablas que se encuentran en esta cronología cuentan con la

autorización de sus propietarios para ser publicadas o se hace referencia a la fuente de

donde se obtuvieron los mismos.

Cronología del lanzamiento de misiones espaciales


Contenido

1966 Enero 06.01.66 DMSP-3B F5 (OPS 2394) / 1966- 001X 07.01.66 DMSP 0714 07.01.66 Kosmos 104 (Zenit-2 #28) 19.01.66 KH-7 24 (OPS 7253) OPS 3179 22.01.66 Kosmos 105 (Zenit-2 #29) 25.01.66 Kosmos 106 (DS-P1-I #1)

28.01.66 Transit-O 7/Transit 11

31.01.66 Luna 9 (E-6 #12)

Febrero 02.02.66 KH-4A 29 (OPS 7291) 03.02.66 ESSA 1

09.02.66 Samos-F3 5 (OPS 1439) /Ferret 8

10.02.66 Kosmos 107 (Zenit-2 #30) 11.02.66 Kosmos 108 (DS-U1-G #1) 15.02.66 KH-7 25 (OPS 1184) Bluebell 2C (OPS 3011) Bluebell 2S (OPS 3031) 17.02.66 Diapason (D 1A) 19.02.66 Kosmos 109 (Zenit-4 #15) 21.02.66 Kosmos (110) (DS-K-40 #2) 22.02.66 Kosmos 110 (Voskhod-3KV #3) 26.02.66 AS-201 28.02.66 ESSA 2

Marzo 01.03.66 Kosmos 111 (Luna (10a)) (E-6S #1) 09.03.66 KH-4A 30 (OPS 3488) 16.03.66 GATV 8 (TDA 3)

16.03.66 Gemini 8 / Gemini 8 Target

17.03.66 Kosmos 112 (Zenit-2 #31) 18.03.66 KH-7 26 (OPS 0879) NRL-PL 137 (OPS 0974) 21.03.66 Kosmos 113 (Zenit-4 #16) 24.03.66 Proton (3)

26.03.66 Transit-O 8 / Transit 12

27.03.66 Molniya-1 (3) 30.03.66 DMSP(66-026A) 30.03.66 OV1 4 OV1 5 (BORE) SPP 28 *

31.03.66 DMSP-3B F6 (OPS 0340) 31.03.66 Luna 10 (E-6S #2)

Abril 06.04.66 Kosmos 114 (Zenit-4 #17) 07.04.66 KH-4A 31 (OPS 1612) 08.04.66 Surveyor-SD 3 / Atlas Centaur 8 08.04.66 OAO 1 19.04.66 KH-7 27 (OPS 0910) 20.04.66 Kosmos 115 (Zenit-2 #32) 22.04.66 OV3 1 25.04.66 Molniya-1 3 26.04.66 Kosmos 116 (DS-P1-Yu #5) 30.04.66 Luna 1966A

Mayo 04.05.66 1966-002X 04.05.66 KH-4A 32 (OPS 1508) 06.05.66 Kosmos 117 (Zenit-2 #33) 11.05.66 Kosmos 118 (Meteor-1 #2) 14.05.66 KH-7 28 (OPS 1950) SSF-B 4 (OPS 6785) 15.05.66 Nimbus 2 17.05.66 Kosmos (119) (Zenit-4 #(18)) 17.05.66 GATV 9 (TDA 5) 17.05.66 Gemini 9 Target A 19.05.66 Transit-O 9 / Transit 13 24.05.66 KH-4A 33 (OPS 1778) 24.05.66 Kosmos 119 (DS-U2-I #1) 25.05.66 Explorer 32 (AE B) 30.05.66 Surveyor 1

Junio

01.06.66 ATDA (TDA 4) / Gemini 9 Target B

03.06.66 Gemini 9 03.06.66 KH-7 29 (OPS 1577) OPS 1856 /KH 7-29 Capsule 07.06.66 OGO 3 08.06.66 Kosmos 120 (Zenit-2 #34) 08.06.66 ERS 16

http://space.skyrocket.de/doc_sdat/dmsp-3b.htm

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=DM0714

http://space.skyrocket.de/doc_sdat/zenit-2.htm

http://space.skyrocket.de/doc_sdat/kh-7.htm


http://space.skyrocket.de/doc_sdat/ds-p1-i.htm

http://space.skyrocket.de/doc_sdat/transit-o.htm

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1966-005A

http://space.skyrocket.de/doc_sdat/luna_e6.htm

http://space.skyrocket.de/doc_sdat/kh-4a.htm

http://space.skyrocket.de/doc_sdat/essa.htm

http://space.skyrocket.de/doc_sdat/samos-f3.htm



http://space.skyrocket.de/doc_sdat/ds-u1-g.htm


http://space.skyrocket.de/doc_sdat/diapason.htm

http://space.skyrocket.de/doc_sdat/ds-k-40.htm

http://space.skyrocket.de/doc_sdat/voskhod-3kv.htm

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=APST201


http://space.skyrocket.de/doc_sdat/luna_e6s.htm


http://space.skyrocket.de/doc_sdat/gatv.htm

http://space.skyrocket.de/doc_sdat/gemini.htm




http://space.skyrocket.de/doc_sdat/proton-1.htm




http://space.skyrocket.de/doc_sdat/ov1.htm




http://space.skyrocket.de/doc_sdat/surveyor-sd.htm


http://space.skyrocket.de/doc_sdat/oao-1.htm




http://space.skyrocket.de/doc_sdat/ds-p1-yu.htm

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=NNN6602




http://space.skyrocket.de/doc_sdat/nimbus-1.htm


http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=GEM9TA




http://space.skyrocket.de/doc_sdat/ds-u2-i.htm

http://space.skyrocket.de/doc_sdat/explorer_ae-b.htm

http://space.skyrocket.de/doc_sdat/surveyor.htm

http://space.skyrocket.de/doc_sdat/atda.htm




http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1966-048B

http://space.skyrocket.de/doc_sdat/ogo.htm


http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1966-051C



09.06.66 RTS-1 1

SECOR 6 (EGRS 6) / MIDAS 10

ORS 2 10.06.66 OV3 4 (PHASR) 16.06.66 IDCSP 1 (OPS 9311) IDCSP 2 (OPS 9312) IDCSP 3 (OPS 9313) IDCSP 4 (OPS 9314) IDCSP 5 (OPS 9315) IDCSP 6 (OPS 9316) IDCSP 7 (OPS 9317) GGTS 1 17.06.66 Kosmos 121 (Zenit-4 #18) 21.06.66 KH-4A 34 (OPS 1599) 24.06.66 PAGEOS 1 25.06.66 Kosmos 122 (Meteor-1 #3)

Julio 01.07.66 Explorer 33 (IMP D) 05.07.66 Apollo 203 06.07.66 Proton 3 08.07.66 Kosmos 123 (DS-P1-Yu #6) 12.07.66 KH-7 30 (OPS 1850) 13.07.66 OV1 7 14.07.66 PasComSat (OV1 8) SPP 33 * 14.07.66 Kosmos 124 (Zenit-2 #35) 18.07.66 GATV 10 (TDA 1A) 18.07.66 Gemini 10 Gemini 10 Target 20.07.66 Kosmos 125 (US-A Test #2) 28.07.66 Kosmos 126 (Zenit-4 #19) 29.07.66 KH-8 1 (OPS 3014)

Agosto 04.08.66 OV3 3 08.08.66 Kosmos 127 (Zenit-4 #20) 09.08.66 KH-4A 35 (OPS 1545) 10.08.66 Lunar Orbiter 1 16.08.66 KH-7 31 (OPS 1832) SSF-B 5 (OPS 6810) 1966-074B 17.08.66 Pioneer 7

18.08.66 Transit-O 10/ Transit 14

19.08.66 RTS-1 2 SECOR 7 (EGRS 7) MIDAS 11 ORS 1 ERS 15 24.08.66 Luna 11 (E-6LF #1) 25.08.66 AS-202 26.08.66 IDCSP (8) IDCSP IDCSP (9) IDCSP (10) IDCSP (11) IDCSP (12) IDCSP (13)

IDCSP (14) GGTS 2 27.08.66 Kosmos 128 (Zenit-4 #21)

Septiembre 08.09.66 KH-4A 36 (OPS 1703) 12.09.66 GATV 11 (TDA 6) 12.09.66 Gemini 11/ Gemini 11 Target 15.09.66 DMSP-4A F1 (OPS 6026) 16.09.66 KH-7 32 (OPS 1686) SSF-B 6 (OPS 6874) 16.09.66 Kosmos (129) (Zenit-2 #(34)) 17.09.66 OGCh #51966-088A 20.09.66 Surveyor 2 20.09.66 KH-4A 1035 26.09.66 Ohsumi (#1) Lambda 4S-1 28.09.66 KH-8 2 (OPS 4096)

Octubre 02.10.66 ESSA 3 05.10.66 RTS-1 3 SECOR 8 (EGRS 8)/ MIDAS 12 12.10.66 KH-7 33 (OPS 2055) KH 7-33 Capsule SGLS 1 (OPS 5345) 14.10.66 Kosmos 129 (Zenit-2 #34) 20.10.66 Kosmos 130 (Zenit-4 #22) 20.10.66 Molniya-1 4

22.10.66 Luna 12 (E-6LF #2)

26.10.66 Surveyor-SD 4 / Atlas Centaur 9

26.10.66 Intelsat-2 1

28.10.66 OV3 2

Noviembre 02.11.66 KH-7 34 (OPS 2070) KH 7-34 Capsule

OPS 5424 / 1966-101A

02.11.66 OGCh #6

02.11.66 OV4 3 OV4 1R OV4 1T OV1 6 Gemini B * 06.11.66 Lunar Orbiter 2 08.11.66 KH-4A 37 (OPS 1866) 11.11.66 GATV 12 (TDA 7A) 11.11.66 Gemini 12 / Gemini 12 Target 12.11.66 Kosmos 131 (Zenit-4 #23) 16.11.66 Kosmos (132) (Strela-2 #2) 19.11.66 Kosmos 132 (Zenit-2 #35)

http://space.skyrocket.de/doc_sdat/rts-1.htm

http://space.skyrocket.de/doc_sdat/secor-1.htm


http://space.skyrocket.de/doc_sdat/ors-1.htm


http://space.skyrocket.de/doc_sdat/idcsp.htm







http://space.skyrocket.de/doc_sdat/ggts-1.htm


http://space.skyrocket.de/doc_sdat/pageos.htm

http://space.skyrocket.de/doc_sdat/explorer_imp-d.htm

http://space.skyrocket.de/doc_sdat/apollo-203.htm





http://space.skyrocket.de/doc_sdat/pascomsat.htm





http://space.skyrocket.de/doc_sdat/us-a_test.htm



http://space.skyrocket.de/doc_sdat/lunar-orbiter.htm



http://space.skyrocket.de/doc_sdat/pioneer-6.htm








http://space.skyrocket.de/doc_sdat/luna_e6lf.htm

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=APST202














http://space.skyrocket.de/doc_sdat/dmsp-4a.htm



http://space.skyrocket.de/doc_sdat/ogch.htm





http://space.skyrocket.de/doc_sdat/ohsumi.htm

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=LAM4S1












http://space.skyrocket.de/doc_sdat/intelsat-2.htm






http://space.skyrocket.de/doc_sdat/ov4-3.htm




http://space.skyrocket.de/doc_sdat/gemini-b.htm





http://space.skyrocket.de/doc_sdat/strela-2.htm




28.11.66 Kosmos 133 (Soyuz-Test #1)

Diciembre 03.12.66 Kosmos 134 (Zenit-4 #24) 05.12.66 KH-7 35 (OPS 1890) 07.12.66 ATS 1 11.12.66 OV1 9 (ERE) OV1 10

12.12.66 Kosmos 135 (DS-U2-MP #1) 14.12.66 Kosmos (136) (Soyuz-Test #(2)) 14.12.66 KH-8 3 (OPS 8968) 14.12.66 Biosat 1 (Bios 1) 19.12.66 Kosmos 136 (Zenit-2 #36) 19.12.66 Ohsumi (#2) Lambda 4S-2 21.12.66 Kosmos 137 (DS-U2-D #1) 21.12.66 Luna 13 (E-6M #1)

29.12.66 Samos-F3 6 (OPS 1584)/ Ferret 9

http://space.skyrocket.de/doc_sdat/soyuz_7k-ok-n.htm


http://space.skyrocket.de/doc_sdat/ats-1.htm



http://space.skyrocket.de/doc_sdat/ds-u2-mp.htm

http://space.skyrocket.de/doc_sdat/soyuz_7k-ok-n.htm


http://space.skyrocket.de/doc_sdat/biosat.htm


http://space.skyrocket.de/doc_sdat/ohsumi.htm


http://space.skyrocket.de/doc_sdat/ds-u2-d.htm

http://space.skyrocket.de/doc_sdat/luna_e6m.htm





Enero 1966

DMSP-3B F5 (OPS 2394) 1966-001X

Launch Date: 1966-01-06 Launch Vehicle: Thor Launch Site: Vandenberg AFB, United States Mass: 130.0 kg

Funding Agency Department of Defense-Department of the Air Force (United States) Discipline Surveillance and Other Military

DMSP 0714


Kosmos 104 (Zenit-2 #28)

Cosmos 104 was a first generation, low resolution Soviet photo surveillance satellite launched from the Baikonur cosmodrome aboard a Vostok rocket. The film capsule was recovered after 8 days. Program not completely met. Spacecraft put into incorrect orbit by abnormal function of second and third stages of booster. Launch Date: 1966-01-07 Launch Vehicle: Modified SS-6 (Sapwood) with 1st Generation Upper Stage Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 4730.0 kg

KH-7 24 (OPS 7253) OPS 3179

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard an Atlas Agena D rocket. It was a KH-7 (Key Hole-7) type spacecraft

Launch Date: 1966-01-19 Launch Vehicle: Atlas Launch Site: Vandenberg AFB, United States Mass: 2000.0 kg


Cosmos 105 was a first generation, low resolution Soviet photo surveillance satellite launched from Baikonur cosmodrome aboard a Vostok rocket. The film capsule was recovered after 8 days

Launch Date: 1966-01-22 Launch Vehicle: Modified SS-6 (Sapwood) with 1st Generation Upper Stage Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 4730.0 kg

Kosmos 106 (DS-P1-I #1)

Cosmos 106 was a Soviet DS type military satellite launched from Kapustin Yar. DS (Dnepropetrovsk Sputnik) were small satellites built by Yangel's OKB-586 / KB Yuzhnoye in the Ukraine for launch by the same KB's Kosmos launch vehicles. They were used for a wide range of military and scientific research and component proving tests. Launch Date: 1966-01-25 Launch Vehicle: Modified SS-4 (Sandal IRBM) plus Upper Stage Launch Site: Kapustin Yar, U.S.S.R Mass: 325.0 kg

Transit-O 7 / Transit 11

Transit 11 was a US Navy navigation satellite launched by a Scout A rocket. Transit, one of the first operational satellite systems, was also known as the Navy Navigation Satellite (NNS). The Transit spacecraft were developed for updating the inertial navigation systems on board US Navy Polaris submarines, and later for civilian use. Transit receivers used the known characteristics of the satellite's orbit, measured the Doppler shift of the





satellite's radio signal, and thereby calculated the receivers position on the earth. As a single spacecraft travelled overhead, the user measured the Doppler shift over a 15 minute period by receiving timing marks and satellite orbital information on two separate frequencies, 149.99 and 399.97 MHz. These signals were corrected for ionospheric refraction and the information was then fed into the users navigation system. Individual Transit satellites operated for over 10 years. Technical break- throughs during the program included gravity gradient stabilization, the use of radio-isotope thermoelectic generators (RTG), and navigation satellite technologies later used in the GPS system. Transit was superseded by the Navstar global positioning system. The use of the satellites for navigation was discontinued at the end of 1996 but the satellites continued transmitting and became the Navy Ionospheric Monitoring System (NIMS). Launch Date: 1966-01-28 Launch Vehicle: Scout Launch Site: Vandenberg AFB, United States Mass: 50.0 kg

Luna 9 (E-6 #12)

La primera sonda en la Historia que logró posarse con suavidad en la superficie de la Luna y mandar fotografías desde allí. Luna 9. Otros nombres: 1966-006A, Lunik 9, 01954 Fecha de lanzamiento: 31 de enero de 1966 a las 11:45:00 GMT Masa seca en órbita: 1580 kg La sonda Luna 9 fue la primera nave que consiguió un aterrizaje suave en la Luna y sobrevivir lo suficiente como para enviar fotografías hasta la Tierra. Esta sonda tenía un peso en el aterrizaje de tan sólo 99 kilogramos. Poseía un contenedor hermético donde se encontraba un equipo de transmisión de radio, un secuenciador de tiempo, los sistemas de control de calor, varios aparatos científicos, fuentes de energía y la cámara.

Foto:La sonda Luna 9

El cohete encargado del lanzamiento fue un Molniya 8K78M (4 Etapas R-7 / SS-6) y fue impulsada hasta nuestro satélite con la cuarta etapa del cohete que más tarde se separó de la sonda. Poco antes de llega a la Luna la sonda se desprendió del módulo esférico de aterrizaje ALS. Luna 9 tocó la superficie lunar en el Océano de las Tormentas (al oeste de los cráteres Reiner y Marius, en 7º8’ norte y 64º22’ O) el 3 de febrero de 1966 a las 18:45:30 GMT. En la imagen superior, en la esquina inferior izquierda se observa levemente una barra que actuaba como sensor. Al sentir el suelo de la Luna la cápsula de aterrizaje (en la esquina superior derecha) saltaba y caía en la superficie lunar Entonces los cuatro pétalos que formaban la nave se abrian para estabilizarla en el suelo. Unas antenas se desplegaron con un sistema de muelles y se colocaron en posición para retransmitir a la Tierra.

Foto: Aterrizador del Luna 9



Foto: Secuencia de aterrizaje

La cámara llevaba un sistema con un espejo orientable que le permitía tener una visión más amplia de la superficie lunar gracias a sus giros. La nave comenzó a los 5 minutos la misión de fotografiar el entorno durante siete sesiones de radio con un total de 8 horas y 5 minutos de duración que fueron retransmitidas a la Tierra en 3 series de imágenes de TV. La primera imagen tardó en llegar 7 horas, con un total de 9 imágenes adquiridas en 5 panoramas. Cuando fueron ensambladas permitieron contemplar el panorama alrededor de Luna 9 incluyendo las rocas y el horizonte hasta unos 1,4 kilómetros de distancia. Con esto los soviéticos lograron la primera llegada de imágenes desde la superficie de otro mundo.

Foto:Vista cercana del módulo

de descenso

Con las imágenes obtenidas se pudo obtener información sobre las características de la superficie lunar, incluyendo la cantidad y distribución de los cráteres, el tamaño de los materiales eyectados y las propiedades mecánicas de la superficie, como su resistencia, compactación, etc. Por su parte el detector de radiación, el único instrumento científico abordo, midió una dosis de 30 milirads por día. Tal vez el descubrimiento más importante de la misión fue que la superficie lunar podría soportar el peso de un objeto que aterrizara y que no se hundiría nada más posarse. El último contacto se realizó a las 22:55 GMT del 6 de febrero. La sonda fue la primera diseñada por el equipo de diseño de Lavochkin que a partir de entonces se encargaría de construir todas las sondas lunares e interplanetarias soviéticas y rusas.

Febrero 1966

KH-4A 29 (OPS 7291)

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Thor Agena D rocket. It was a KH-4A (Key Hole-4A) type spacecraft. Both panoramic cameras were operational throughout Launch Date: 1966-02-02 Launch Vehicle: Thor Launch Site: Vandenberg AFB, United States Mass: 1500.0 kg

Primera imagen enviada desde

la superficie lunar



ESSA 1

ESSA 1 was a spin-stabilized operational meteorological spacecraft designed to take and record daytime cloudcover pictures on a global basis for subsequent playback to a ground acquisition station. The satellite had essentially the same configuration as that of the TIROS series, i.e., an 18-sided right prism, 107 cm across opposite corners and 56 cm high, with a reinforced baseplate carrying most of the subsystems and a cover assembly (hat). Electrical power was provided by approximately 10,000 1- by 2-cm solar cells that were mounted on the cover assembly and by 21 nickel-cadmium batteries. Two redundant wide-angle cameras were mounted on opposite sides of the spacecraft and canted 75 deg from the spacecraft spin axis. A pair of crossed-dipole command and receiving antennas projected out and down from the baseplate. A monopole telemetry and tracking antenna extended up from the top of the cover assembly. The satellite was placed in a cartwheel orbital mode, with its spin axis maintained normal to the orbital plane. The satellite spin rate and attitude were determined primarily by a Magnetic Attitude Spin Coil (MASC). The MASC was a current-carrying coil mounted in the cover assembly. The magnetic field induced by the current interacted with the earth's magnetic field to provide the necessary torque to maintain a desired spin rate of 9.225 rpm. Five small solid-fuel thrusters mounted around the baseplate provided a secondard means of controlling the spacecraft spin rate. The satellite performed normally after launch until October 6, 1966, when the camera system failed. The spacecraft was deactivated on May 8, 1967, after being left on for an additional time period for engineering purposes. Launch Date: 1966-02-03 Launch Vehicle: Delta Launch Site: Cape Canaveral, United States Mass: 304.0 kg

Foto:ESSA 3 [NOAA]

Samos-F3 5 (OPS 1439) Ferret 8

This US Air Force electronics intelligence satellite was launched from Vandenberg AFB aboard a Thor Agena D rocket. The Ferrets catalogued Soviet air defence radars, eavesdropped on voice communications, and taped missile and satellite telemetry. Launch Date: 1966-02-09 Launch Vehicle: Thor Launch Site: Vandenberg AFB, United States Mass: 1500.0 kg


Cosmos 107 was a first generation, low resolution Soviet photo surveillance satellite launched from the Baikonur cosmodrome aboard a Vostok rocket. The film capsule was recovered after 8 days. Launch Date: 1966-02-10 Launch Vehicle: Modified SS-6 (Sapwood) with 1st Generation Upper Stage Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 4730.0 kg

Kosmos 108 (DS-U1-G #1)

Cosmos 108 was a Soviet DS type military satellite launched from Kapustin Yar. DS (Dnepropetrovsk Sputnik) were small satellites built by Yangel's OKB-586 / KB Yuzhnoye in the Ukraine for launch by the same KB's Kosmos launch vehicles. They





were used for a wide range of military and scientific research and component proving tests. Launch Date: 1966-02-11 Launch Vehicle: Modified SS-4 (Sandal IRBM) plus Upper Stage Launch Site: Kapustin Yar, U.S.S.R Mass: 355.0 kg

KH-7 25 (OPS 1184) Bluebell 2C (OPS 3011) Bluebell 2S (OPS 3031)

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Atlas Agena D rocket. It was a KH-7 (Key Hole-7) type spacecraft. Launch Date: 1966-02-15 Launch Vehicle: Atlas Launch Site: Vandenberg AFB, United States Mass: 2000.0 kg

Diapason (D 1A)

This was a small cylindrical satellite, 20 cm long and 50 cm in diameter which was used for making geodetic measurements. Observations consisted of doppler delay of radio signals, plus photography of the satellite against the star field. Satellite performance was satisfactory with useful observations occuring for over 5 years. Launch Date: 1966-02-17 Launch Vehicle: Diamant Launch Site: Hammaguir, Algeria Mass: 19.0 kg

Foto.Diapason [CNES]


Cosmos 109 was a second generation, high resolution Soviet photo surveillance satellite launched from the Baikonur cosmodrome aboard a Soyuz rocket. The satellite also carried biological experiments.

Launch Date: 1966-02-19 Launch Vehicle: Modified SS-6 (Sapwood) with 2nd Generation (Longer) Upper Stage Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 4730.0 kg

Kosmos (110) (DS-K-40 #2)

DS-K-40 was an experimental ELINT satellite to test technologies for the Tselina-O program.Fallo en elanzamiento,

Nation: U.S.S.R.

Type / Application:

experimental ELINT

Operator:

Contractors: Yuzhnoye

Equipment:

Configuration: DS Bus

Propulsion:

Lifetime:

http://space.skyrocket.de/doc_sdat/tselina-o.htm

http://space.skyrocket.de/doc_sdat/tselina-o.htm



Kosmos 110 (Voskhod-3KV #3)

Cosmos 110 was a Soviet spacecraft launched from the Baikonur cosmodrome aboard a Soyuz rocket. It incorporated a reentry body (capsule) for landing scientific instruments and test objects. It was a biological satellite that made a sustained biomedical experiment with the dogs Veterok and Ugolyok, after 22 days in orbit around the Earth, they were safely landed. Launch Date: 1966-02-22 Launch Vehicle: Modified SS-6 (Sapwood) with 2nd Generation (Longer) Upper Stage Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 5700.0 kg

AS-201

The Apollo-Saturn 201 (AS-201) mission was an unmanned suborbital flight to test the Saturn 1B launch vehicle and the Apollo Command and Service Modules. It was the first flight of the two-stage Saturn 1B. The objectives of the flight were to verify the structural integrity, launch loads, stage separation, and operation of subsystems of the Saturn 1B, and evaluate the Apollo spacecraft subsystems, heatshield, and mission support facilities. Due to loss of data during maximum heating of the heatshield the evaluation of the ablator at high re-entry rates was not achieved, but all other objectives were met. The Saturn 1B, carrying the unmanned Apollo spacecraft CSM-009, was launched from launch complex 34 of the eastern test range of Cape Canaveral. After ignition of the S-IVB liquid-hydrogen-powered second stage the launch escape tower was jettisoned and the recoverable cameras ejected. Following a seven minute burn the 2nd stage and instrument unit separated from the Apollo CSM spacecraft. The CSM reached a maximum altitude of 499 km over the Atlantic Ocean before beginning its descent. At this time a ullage maneuver was performed which consisted of rocket burns designed to increase the re-entry velocity in order to test the heatshield. The reaction-control system rockets were fired for 30 seconds, then the service modules

main propulsion engine was fired for 100 seconds and then for 10 seconds. The service module was jettisoned and the command module re-entered at 8300 meters/sec, generating a re-entry heat of roughly 2200 degrees C. Three main parachutes deployed at an altitude of 3700 meters and splashdown took place in the Atlantic at 16:49 UT, 37 minutes after launch, at 8.18 deg S. 11.15 deg W, 8472 km downrange. The target point was missed by 72 km, and the U.S.S. Boxer recovered the capsule by 19:20 UT. Launch Date: 1966-02-26 Launch Vehicle: Saturn 1B Launch Site: Cape Canaveral, United States Mass: 20820.1 kg

Foto:AS-201

ESSA 2

ESSA 2 was a sun-synchronous operational meteorological satellite designed to provide real-time earth cloudcover TV pictures to properly equipped ground receiving stations for use in weather analysis and forecasting. The satellite had essentially the same configuration as that of the TIROS spacecraft, i.e., and 18-sided right prism, 107 cm across opposite corners and 56 cm high, with a reinforced baseplate carrying most of the subsystems and a cover assembly (hat). Electrical power was

http://space.skyrocket.de/doc_sdat/voskhod-3kv.htm

http://nssdc.gsfc.nasa.gov/image/spacecraft/as_201.jpg



provided by approximately 10,000 1- by 2-cm solar cells that were mounted on the cover assembly and by 21 nickel-cadmium batteries. Two redundant wide-angle Automatic Picture Transmission (APT) cameras were mounted on opposite sides of the spacecraft with their optical axes perpendicular to the spin axis. Projecting downward from the baseplate were a pair of crossed-dipole command reception antennas. A monopole telemetry (136.500 MHz) and tracking (136.770 MHz) antenna extended outward from the top of the cover assembly. The satellite spin rate was controlled by means of a Magnetic Attitude Spin Coil (MASC), with the spin axis maintained normal to the orbital plane (cartwheel orbit mode) to within plus or minus 1 deg. The MASC was a current-carrying coil mounted in the cover assembly. The magnetic field induced by the current interacted with the earth's magnetic field to provide the torque necessary to maintain a desired spin rate of 10.9 rpm. The spacecraft performed normally after launch. Over 4 yr of useful cloudcover pictures were obtained before the camera systems were placed in a standby mode on March 20, 1970, owing to a telemetry conflict with ITOS 1. ESSA 2 was deactivated on October 16, 1970. Launch Date: 1966-02-28 Launch Vehicle: Delta Launch Site: Cape Canaveral, United States Mass: 286.0 kg

Marzo

Kosmos 111 (Luna (10a)) (E-6S #1)

Otros nombres: 1966-017A, 02093 Fecha de lanzamiento: 1 de marzo de 1966 a las 11:02:00 GMT Masa seca en órbita: 1580 kg Esta misión debía llegar a la Luna como un orbitador más de la serie, similar a la misión Luna 10 y basado en el bus de aterrizaje modelo Ye-6. Fue lanzada a la órbita terrestre desde Tyuratam (Cosmódromo de Baikonour) con un cohete Molniya (un SS-6 modificado) con éxito, pero la etapa superior

Blok-L (de 2ª generación) perdió el control de giro y no pudo enviar la sonda hacia una trayectoria lunar. Al quedarse en órbita terrestre recibió el nombre de Cosmos 111 y reentró en la atmósfera de nuestro planeta dos días después del lanzamiento.

KH-4A 30 (OPS 3488)

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Thor Agena D rocket. It was a KH-4A (Key Hole-4A) type spacecraft. All cameras operated satisfactorily.


GATV 8 (TDA 3)

The GATV (Gemini Agena Target Vehicle) was designed to be launched into Earth orbit prior to a Gemini mission and used for rendezvous and docking practice.

Nation: USA

Type / Application:

Docking Target

Operator: NASA

Contractors: ?

Equipment: ?

Configuration: Agena-D with docking equipment

Propulsion: Bell 8096

Lifetime:

Mass: 3260 kg

Orbit:

Foto:GATV 8 [NASA]







Gemini 8 / Gemini 8 Target

Insignia de la misión

Estadísticas de la Misión Nombre de la misión: Gemini 8 Call sign: Gemini 8 Número de tripulantes: 2 Lanzamiento: 16 de marzo, 1966 16:41:02.389 UTC Cabo Cañaveral LC 19 Acoplamiento: 16 de abril, 1966 Acoplado: ~22:14 UTC Desacoplado: ~~22:45 UTC Amerizaje: 17 de marzo, 1966 03:22:28 UTC 25°13.8′N 136°0′E Duración: 10 h 41 min 26 s Distancia recorrida: ~293,206 km Órbitas: ~6.75 Apogeo: (Primera órbita) 271,9 km Perigeo: (Primera órbita) 159,9 km Periodo: (Primera órbita) 88.83 min Inclinación: 28.91 deg Peso: 3,789 kg Gemini 8 (oficialmente llamado Gemini VIII) fue un vuelo espacial en 1966, en el programa Gemini de la NASA. Este era el 6º vuelo de una misión Gemini, el 14º vuelo estadounidense y el 22º vuelo espacial (incluidos los vuelos del X-15 por encima de los 100 km). Tripulación Neil Armstrong (voló en Gemini 8 y Apollo 11), Piloto Comandante David Scott (voló en Gemini 8, Apollo 9, y Apollo 15), Piloto

Tripulación de reserva Charles Conrad, Jr., Piloto comandante Richard F. Gordon, Jr., Piloto Parámetros de la misión Peso: 3,789 kg Perigeo: 159.9 km Apogeo: 271.9 km Inclinación: 28.91° Periodo: 88.83 min Objetivos Gemini VIII tenía dos objetivos principales, de los cuales se alcanzaron los dos. Los dos objetivos eran:lograr un encuentro en órbita, un acoplamiento y lograr una EVA extendida. Ed White, durante el Gemini IV, había pasado unos cortos 20 minutos fuera de la nave. El primer objetivo principal fue logrado por el comandante de nave espacial, Neil Armstrong, quien pilotó el Gemini VIII adentro de 9 dm del prelanzado Agena. Esto era el primer acoplamiento orbital alguna vez. El segundo objetivo debía haber sido logrado por el Piloto David Scott, quien debía pasar hasta dos horas fuera de la nave espacial, pero acontecimientos subsecuentes cancelaron el paseo espacial planificado. Lo que siguió al acoplamiento acertado por Armstrong eran algunos de los minutos más espeluznantes en la historia de losvuelos espaciales. La cápsula, todavía acoplada al Agena, comenzó a rodar continuamente. Habiendo nunca afrontado esto en la simulación, la tripulación se desacopló del Agena. Sin embargo, el problema era sobre la nave espacial, que ahora cayó aún más rápido, de una revolución por segundo. El único modo de parar el movimiento separarse del módulo adaptador, que quiso decir que Armstrong y Scott tuvieron que cortar su misión y hacer una reentrada de emergencia a la Tierra 10 horas después del lanzamiento. Ellos todavía tenían náuseas y estaban mareados después del amerizaje, así como decepcionados: Scott había perdido el paseo espacial planificado. Vuelo Esto fue cinco meses desde que la NASA había tratado de lanzar un Agena y Gemini. Esta vez todo trabajó perfectamente. El Agena se pone en una órbita circular de 298 km y se orienta a la



http://es.wikipedia.org/wiki/16_de_marzo

http://es.wikipedia.org/wiki/1966

http://es.wikipedia.org/wiki/Coordinated_Universal_Time

http://es.wikipedia.org/wiki/Cabo_Ca%C3%B1averal




http://es.wikipedia.org/wiki/Programa_Gemini

http://es.wikipedia.org/wiki/NASA

http://es.wikipedia.org/wiki/X-15

http://es.wikipedia.org/wiki/Neil_Armstrong

http://es.wikipedia.org/wiki/Apollo_11



http://es.wikipedia.org/wiki/David_Scott



http://es.wikipedia.org/w/index.php?title=Richard_F._Gordon,_Jr.&action=edit&redlink=1

http://es.wikipedia.org/wiki/Peso

http://es.wikipedia.org/wiki/Perigeo

http://es.wikipedia.org/wiki/Apogeo

http://es.wikipedia.org/wiki/Periodo_orbital

http://es.wikipedia.org/wiki/Actividad_extravehicular




http://es.wikipedia.org/wiki/Dm

http://es.wikipedia.org/wiki/Agena






altitud correcta para el atraco. La cápsula Gemini fue puesta en los 160 km en la órbita de 272 km por el modificado Titán II ICBM.

Foto:Vista del Agena desde el Gemini 8

Rendezvous y acoplamiento Primero se queman a 1 hora y 34 minutos en la misión, cuando ellos bajaron su apogeo con un 5 segundo se quema. El segundo se queman estaba en el apogeo de la segunda órbita. Esta vez ellos levantaron su perigeo por añadiendo 15 metros por segundo a su velocidad. Su tercio se quema se aseguró que ellos estaban en el mismo avión orbital. Esta vez ellos fueron girados 90 ° de su dirección de viajes e hicieron un quemar

de 8 metros por segundo mientras ellos eran sobre Océano Pacífico. Ellos entonces tuvieron que hacer 0,8 m/s se queman después de que el revisor de tierra comprendió(realizó) que ellos eran ligeramente desconectados debido a problemas con el thrusters no que cierra correctamente.


Cosmos 112 was a first generation, low resolution Soviet photo surveillance satellite launched from the Plesetsk cosmodrome aboard a Vostok rocket. The film capsule was recovered after 8 days. Launch Date: 1966-03-17 Launch Vehicle: Modified SS-6 (Sapwood) with 1st Generation Upper Stage Launch Site: Plesetsk, U.S.S.R Mass: 4730.0 kg

KH-7 26 (OPS 0879) / NRL-PL 137 (OPS 0974)



Cosmos 113 was a second generation, high resolution Soviet photo surveillance satellite launched from the Baikonur cosmodrome aboard a Soyuz rocket. Launch Date: 1966-03-21 Launch Vehicle: Modified SS-6 (Sapwood) with 2nd Generation (Longer) Upper Stage Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 4730.0 kg

Gemini 8 Agena Info.

Agena GATV-5003

NSSDC ID: 1966-019A

Peso 3,175 kg

Sitio de lanzamiento

LC-14

Fecha de lanzamiento

16 de marzo, 1966

Hora lanzamiento 15:00:03 UTC

1er Perigeo 299.1 km

1er Apogeo 299.7 km

Periodo 90.47 m

Inclinación 28.86

Reentrada 15 de septiembre, 1967

http://es.wikipedia.org/wiki/Km

http://es.wikipedia.org/wiki/Titan_II

http://es.wikipedia.org/wiki/Misil_bal%C3%ADstico_intercontinental





http://es.wikipedia.org/wiki/15_de_septiembre




Proton (3)

The N-4 sereies of satellites, a.k.a. Proton-1, carried instruments to study super-high energy cosmic particles. The instruments were carried in a pressurized compartment and consisted of ionisation calorimeters to study the energy of particles in the 1013 eV range and determining the intensity and energy spectrum of galactic electrons, and measuring the intensity and energy spectrum of cosmic gamma-rays over 50 MeV.

Nation: U.S.S.R.

Type / Application:

Science

Lifetime:

Mass: 12200 kg

Orbit: 183 km x 589 km, 63.44° (#1) / 189 km x 608 km, 63.45° (#2) / 185 km x 585 km, 63.47° (#3)

Transit-O 8Transit 12

Transit 12 was a US Navy navigation satellite launched by a Scout A rocket. Transit, one of the first operational satellite systems, was also know as the Navy Navigation Satellite (NNS). The Transit spacecraft were developed for updating the inertial navigation systems on

board US Navy Polaris submarines, and later for civilian use. Transit receivers used the known characteristics of the satellite's orbit, measured the Doppler shift of the satellite's radio signal, and thereby calculated the receivers position on the earth. As a single spacecraft travelled overhead, the user measured the Doppler shift over a 15 minute period by receiving timing marks and satellite orbital information on two separate frequencies, 149.99 and 399.97 MHz. These signals were corrected for ionospheric refraction and the information was then fed into the users navigation system. Individual Transit satellites operated for over 10 years. Technical break- throughs during the program included gravity gradient stabilization, the use of radio-isotope thermoelectic generators (RTG), and navigation satellite technologies later used in the GPS system. Transit was superseded by the Navstar global positioning system. The use of the satellites for navigation was discontinued at the end of 1996 but the satellites continued transmitting and became the Navy Ionospheric Monitoring System (NIMS). Launch Date: 1966-03-26 Launch Vehicle: Scout Launch Site: Vandenberg AFB, United States Mass: 50.0 kg

Molniya-1 (3)

Lanzamiento fallido.

DMSP(66-026A)

Originally part of a classified system of USAF weather satellites, the spacecraft's missions were not revealed until March 1973. The cylindrically shaped spacecraft carried both visual and infrared sensors. The satellite was one of the experimental models for a series of USAF weather satellites designed to provide the Air Force Global Weather Central and other users with high-resolution cloud cover imagery. The satellite was spin-stabilized and operated at a nominal altitude of 450

Foto:Proton 3







nautical miles in a sun-synchronous polar orbit. Launch Date: 1966-03-30 Launch Vehicle: Thor Launch Site: Vandenberg AFB, United States Mass: 150.0 kg

OV1 4 / OV1 5 (BORE) / SPP 28 * OV1-4 was an Air Force technology satellite launched from Vandenberg AFB aboard an Atlas D rocket. It performed thermal control experiments. OV1 5: Background optical radiation experiment (BORE) IR sensors Launch Date: 1966-03-30 Launch Vehicle: Atlas D Launch Site: Vandenberg AFB, United States Mass: 87.6 kg

DMSP-3B F6 (OPS 0340)

Foto:Thor-LV2D Burner-1 (2)

Nation: USA

Type / Application:

Meteorology

Operator: USAF

Contractors: RCA Astro

Equipment: ?

Configuration:

Propulsion: ?

Lifetime:

Mass:

Orbit: SSO

Luna 10 (E-6S #2)

Otros nombres: 1966-027A, Lunik 10, 02126 Fecha de lanzamiento: 31 de marzo de 1.966 a las 10:48:00 GMT Masa seca en órbita: 1.582 kg La sonda Luna 10 (nave de reserva de la misión anterior y que formaba parte de la serie de sondas Ye-6S) fue lanzada hacia la Luna el 31 de marzo de 1966 en un cohete Molniya 8K78M. Tras abandonar la órbita terrestre y realizar una maniobra de corrección el 1 de abril, la nave llegó a nuestro satélite el 3 de abril de 1966 a las 18:44 GMT y completó su primera órbita 3 horas después, con una inclinación de 71.9º y a 350 x 1000 kilómetros de nuestro satélite. De esta forma se convertía en el primer objeto hecho por el hombre que entraba en órbita de otro cuerpo planetario. La instrumentación científica pesaba en total 245 kilogramos e incluía: • Espectrómetro de rayos gamma para energías entre 0.3 y 3 MeV • Magnetómetro triaxial • Detector de meteoritos • Sensor de plasma solar • Sensor de infrarrojos para medir las condiciones ambientales de la Luna y la radiación. Se realizaron por completo los estudios gravitacionales. Además la sonda envió hacia la Tierra el himno ‘La Internacional’ ya que se celebraba el 23º Congreso del Partido Comunista de la Unión Soviética. Este himno estaba grabado en dos osciladores de estado sólido que habían sido programados para hacer sonar la canción. Durante un ensayo en la noche del 3 de abril la grabación fue bien, pero a la siguiente mañana los controladores se dieron cuenta que faltaba una nota y para subsanarlo reprodujeron la grabación de la noche anterior, afirmando que se estaba recibiendo en directo desde la Luna.






Foto:Sonda Luna 10

Tal vez su descubrimiento más importante fue la primera evidencia de la existencia de las concentraciones de masa llamadas ‘mascones’, áreas de alta densidad debajo de las cuencas de los mares, que distorsionan las trayectorias de las órbitas de las sondas. Este descubrimiento normalmente se le ha acreditado a las sondas Lunar Orbiter norteamericanas. Además obtuvo datos importantes sobre el campo magnético y la naturaleza de las rocas lunares, descubriendo que eran comparables a las rocas basálticas terrestres. La sonda funcionó durante 485 órbitas lunares y tuvieron lugar 219 transmisiones de datos en 60 días, hasta que se interrumpió la comunicación el 30 de mayo de 1966.

Abril 1966


Cosmos 114 was a second generation, high resolution Soviet photo surveillance satellite launched from the Plesetsk cosmodrome aboard a Soyuz rocket.

Launch Date: 1966-04-06 Launch Vehicle: Modified SS-6 (Sapwood) with 2nd Generation (Longer) Upper Stage Launch Site: Plesetsk, U.S.S.R Mass: 4730.0 kg

KH-4A 31 (OPS 1612)

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Thor Agena D rocket. It was a KH-4A (Key Hole-4A) type spacecraft. The aft-looking camera malfunctioned after the recovery of bucket "1". No material was received in bucket "2" (1031-2).


Surveyor-SD 3 / Atlas Centaur 8

Launch Date: 1966-04-08 Launch Vehicle: Atlas-Centaur Launch Site: Cape Canaveral, United States Mass: 784.7 kg Masa seca en órbita: 784 kgs El test final llegó hasta la órbita de forma perfecta, pero un fallo hizo que empezara a girar fuera de control. La nave reentró en la atmósfera terrestre un mes despues y se desintegró. La órbita tenía una altura de 182 x 336 kms y una inclinación de 30,7º Tán solo 25 días despues de que el SM2 ardiera, la NASA lanzó el Surveyor 1, la primera de la serie con todos los instrumentos y llegó con perfección a la Luna.

OAO 1

OAO 1 was a solar-cell-powered satellite instrumented to make precision astronomical observations and to measure the absorption and emission characteristics of the stars, planets, nebulae, and the interplanetary and interstellar media from visible to gamma-ray regions. The stabilization system permitted three axes a pointing accuracy of 1 arc minute after the star tracker acquired a guide star. The




http://space.skyrocket.de/doc_sdat/oao-1.htm



control system permitted an ultimate pointing accuracy of 0.1 arc second. OAO 1 was launched in a nominal nearly perfect circular orbit and operate as planned for the first 7 min after separation. Suqsequent high voltage arcing and battery depletion caused the mission to be terminated as a failure after 20 orbits without activating the experiments. Major problems were attributed to a failure in the power supply system and to high volatage arcing in the star trackers. Launch Date: 1966-04-08 Launch Vehicle: Atlas-Agena D Launch Site: Cape Canaveral, United States Mass: 1769.0 kg

Foto:OAO 1

KH-7 27 (OPS 0910)



Cosmos 115 was a first generation, low resolution Soviet photo surveillance satellite launched from the Baikonur cosmodrome aboard a Vostok rocket. The film capsule was recovered after 8 days. The program was partially completed. There was abnormal operation of a SA-10 camera


OV3 1

OV3-1 was an Air Force research satellite launched from Vandenberg AFB aboard a Scout B rocket. It performed radiation experiments.

Launch Date: 1966-04-22 Launch Vehicle: Scout Launch Site: Vandenberg AFB, United States Mass: 69.0 kg

Molniya-1 3

Molniya 1/ 3 was a first-generation Russian communications satellite (COMSAT) orbited to test and perfect a system of radio communcations and television broadcasting using earth satellites as active transponders and to experiment with the system in practical use. The basic function of the satellite was to relay television programs and long-distance two-way multichannel telephone, phototelephone, and telegraph links from Moscow to the various standard ground receiving stations in the 'Orbita' system. The satellite was in the form of a hermetically sealed cylinder with conical ends -- one end contained the orbital correcting engine and a system of microjets, and the other end contained externally mounted solar and earth sensors. Inside the cylinder were (1) a high-sensitivity receiver and three 800-MHz 40-w transmitters (one operational and two in reserve), (2) telemetering devices that monitored equipment operation, (3) chemical batteries that were constantly recharged by solar cells, and (4) an electronics computer that controlled all equipment on board. Mounted around the central cylinder were six large solar battery panels and two directional, high-gain



http://nssdc.gsfc.nasa.gov/image/spacecraft/oao.jpg



parabolic aerials, 180 deg apart. One of the aerials was directed continually toward the earth by the reserve. Signals were transmitted in a fairly narrow beam ensuring a strong reception at the earth's surface. The satellite received telemetry at 1000 MHz. Television service was provided in a frequency range of 3.4 to 4.1 GHz at 40 w. Molniya 1/ 3, whose cylindrical body was 3.4 m long and 1.6 m in diameter, was much heavier than corresponding U.S. COMSATS, and it had about 10 times the power output of the Early Bird COMSAT. In addition, it did not employ a geosynchronous equatorial orbit as have most U.S. COMSATs because such an orbit would not provide coverage for areas north of 70 deg n latitude. Instead, the satellite was boosted from a low-altitude larking orbit into a highly elliptical orbit with two high apogees daily over the northern hemisphere -- one over Russia and one over North America -- and relatively low perigees over the southern hemisphere. During its apogee, Molniya 1C remained relatively stationary with respect to the earth below for nearly 8 of every 12 hr. By placing three or more Molniya 1 satellites in this type of orbit, spacing them suitably, and shifting their orbital planes relative to each other by 120 deg, a 24-hr/day communications system could be obtained. Molniya 1C relayed color TV transmissions from Moscow to France in a test of the French-Russian SECAM-III television transmission system. In addition, Molniya 1C was the first of the series to carry a television camera to transmit back cloudcover pictures. The camera was externally mounted and was equipped with various filters and interchangeable wide- and narrow-angle lenses. From its high apogees over the northern hemisphere, the satellite transmitted detailed cloudcover pictures of the entire disc of the earth that were similar to the ATS pictures. These pictures from Molniya 1/ 3 were used in conjunction with cloudcover pictures taken by the lower orbiting satellites of the 'Meteor' weather satellite system to obtain a comprehensive and detailed view of global weather systems. Launch Date: 1966-04-25 Launch Vehicle: Modified SS-6 (Sapwood) with 2nd Generation Upper Stage +

Escape Stage Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 998.0 kg

Kosmos 116 (DS-P1-Yu #5)


Luna 1966A

Fecha de lanzamiento: 30 de abril de 1.966 Masa seca en órbita: 1.620 kg Se trataba de otra sonda orbitadora lunar de la serie soviética Luna. Durante el lanzamiento falló el cohete que debía ponerla en órbita terrestre y el conjunto se estrelló a unos cientos de kilómetros de la Torre de Lanzamiento.

Mayo 1966

1966-002X

Launch Date: 1966-05-03 Launch Vehicle: Thrust Augmented Thor-Agena D Launch Site: Vandenberg AFB, United States Mass: 1500.0 kg

http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=NNN6602



KH-4A 32 (OPS 1508)

Foto:KH-4A 4 [USAF]

Nation: USA

Type / Application:

Reconnaissance, photo (film return type)

Operator: USAF

Contractors: Lockheed

Equipment: J-1 camera, index camera

Configuration: Agena-D, 2 SRVs

Propulsion: Bell 8096, 2 Star 12 retro motors

Lifetime:

Mass:



Kosmos 118 (Meteor-1 #2)

Cosmos 118 was the ninth Russian experimental meteorlogical satellite and the seventh launched from the Tyuratam site. It was the fourth in a series of prototype satellites that led eventually to the orbiting of Russia's first announced experimental weather satellite, Cosmos 122. No offical description of the Cosmos 118 flight has ever been released. However, the orbital parameters and configuration of the satellite were so similar to those of Cosmos 122 that it is generally assumed that Cosmos 118 was a precursor to the satellites of the experimental Cosmos 'Meteor' system. The satellite was in the form of a cylinder 5 m long and 1.5 m in diameter with two solar panels attached to the sides. A steerable antenna, also mounted on the side, transmitted at 90 MHz. The primary objective of the flight probably was to test the basic spacecraft hardware. Tests were probably also made on improved TV and IR cloud cameras and actimometric instruments, which may have failed to operate properly. As of June 1972, the satellite remained in orbit in a deactivated mode. Similar flights were made by Cosmos 44, 58, and 100. Launch Date: 1966-05-11 Launch Vehicle: Modified SS-6 (Sapwood) with 1st Generation Upper Stage Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 4730.0 kg

KH-7 28 (OPS 1950) SSF-B 4 (OPS 6785)



http://space.skyrocket.de/doc_eng/star-12.htm





Nimbus 2

Nimbus 2, the second in a series of second-generation meteorological research-and-development satellites, was designed to serve as a stabilized, earth-oriented platform for the testing of advanced meteorological sensor systems and the collecting of meteorological data. The polar-orbiting spacecraft consisted of three major elements: (1) a sensory ring, (2) solar paddles, and (3) the control system housing. The solar paddles and the control system housing were connected to the sensory ring by a truss structure, giving the satellite the appearance of an ocean buoy. Nimbus 2 was nearly 3.7 m tall, 1.5 m in diameter at the base, and about 3 m across with solar paddles extended. The sensory ring, which formed the satellite base, housed the electronics equipment and battery modules. The lower surface of the torus-shaped sensory ring provided mounting space for sensors and telemetry antennas. An H-frame structure mounted within the center of the torus provided support for the larger experiments and tape recorders. Mounted on the control system housing, which was located on top of the spacecraft, were sun sensors, horizon scanners, gas nozzles for attitude control, and a command antenna. Use of a stabilization and control system permitted the spacecraft's orientation to be controlled to within plus or minus 1 deg for all three axes (pitch, roll, and yaw). The spacecraft carried (1) an advanced vidicon camera system (AVCS) for recording and storing remote cloudcover pictures, (2) an automatic picture transmission (APT) camera for providing real-time cloudcover pictures, and (3) both high- and medium-resolution infrared radiometers (HRIR and MRIR) for measuring the intensity and distribution of electromagnetic radiation emitted by and reflected from the earth and its atmosphere. The spacecraft and experiments performed normally after launch until July 26, 1966, when the spacecraft tape recorder failed. Its function was taken over by the HRIR tape recorder until November 15, 1966, when it also failed. Some real-time data were collected until January 17, 1969, when the spacecraft mission was terminated owing to deterioration of the horizon scanner

used for earth reference. More detailed information can be found in the "Nimbus II Users' Guide" (TRF B03406), available from NSSDC.+ Nimbus 2, the second in a series of second-generation meteorological research-and-development satellites, was designed to serve as a stabilized, earth-oriented platform for the testing of advanced meteorological sensor systems and the collecting of meteorological data. The polar-orbiting spacecraft consisted of three major elements: (1) a sensory ring, (2) solar paddles, and (3) the control system housing. The solar paddles and the control system housing were connected to the sensory ring by a truss structure, giving the satellite the appearance of an ocean buoy. Nimbus 2 was nearly 3.7 m tall, 1.5 m in diameter at the base, and about 3 m across with solar paddles extended. The sensory ring, which formed the satellite base, housed the electronics equipment and battery modules. The lower surface of the torus-shaped sensory ring provided mounting space for sensors and telemetry antennas. An H-frame structure mounted within the center of the torus provided support for the larger experiments and tape recorders. Mounted on the control system housing, which was located on top of the spacecraft, were sun sensors, horizon scanners, gas nozzles for attitude control, and a command antenna. Use of a stabilization and control system permitted the spacecraft's orientation to be controlled to within plus or minus 1 deg for all three axes (pitch, roll, and yaw). The spacecraft carried (1) an advanced vidicon camera system (AVCS) for recording and storing remote cloudcover pictures, (2) an automatic picture transmission (APT) camera for providing real-time cloudcover pictures, and (3) both high- and medium-resolution infrared radiometers (HRIR and MRIR) for measuring the intensity and distribution of electromagnetic radiation emitted by and reflected from the earth and its atmosphere. The spacecraft and experiments performed normally after launch until July 26, 1966, when the spacecraft tape recorder failed. Its function was taken over by the HRIR tape recorder until November 15, 1966, when it also failed. Some real-time data were collected



until January 17, 1969, when the spacecraft mission was terminated owing to deterioration of the horizon scanner used for earth reference. More detailed information can be found in the "Nimbus II Users' Guide" (TRF B03406), available from NSSDC.

Kosmos (119) (Zenit-4 #18)


GATV 9 (TDA 5)

The GATV (Gemini Agena Target Vehicle) was designed to be launched into Earth orbit prior to a Gemini mission and used for rendezvous and docking practice

Gemini 9 Target A

The Gemini 9 Agena Target Vehicle (vehicle GATV 5004) was intended as a docking target for the Gemini 9 mission, scheduled to launch 99 minutes after the GATV. Launch of the GATV took place at 10:12 a.m. EST (15:12 UT) on 17 May 1966. At 120.6 seconds after liftoff, the Atlas no. 2 booster engine swiveled to an extreme hardover position about 10 seconds before booster engine cutoff. The other booster and sustainer engine, under autopilot, worked to counter the asymmetrical thrust, but the vehicle pitched downward and after booster separation the vehicle continued flying under sustained thrust, having pitched down 216 degrees from the 67 degree nominal position, so it

was flying north back toward Cape Kennedy at a climbing angle of 13 degrees above horizontal. It had also rolled to a position where ground guidance could not lock on. The vernier engines cut off at 300 seconds. The Agena separated on schedule and both vehicles plunged into the sea about 172 km northeast of the launch site, 145 km off the coast of Florida seven and a half minutes after launch. Radar data from the Grand Bahama Island station at 436 seconds after launch placed the vehicle about 191.6 km from the launch site at 29,500 meters altitude, headed north and descending. The exact reason for the loss of engine pitch control was unknown, data indicated that a short-to-ground occurred in the circuit for the servoamplifier output command signal. The short may have been caused by cryogenic leakage in the thrust section. Scheduled launch of the Gemini 9 spacecraft was cancelled. Gemini Agena Target Vehicle The Gemini Agena Target Vehicle was designed to be launched into Earth orbit prior to a Gemini mission and used for rendezvous and docking practice. The GATV had a docking cone at the forward end into which the nose of the Gemini spacecraft could be inserted and held with docking latches. The GATV was a 6 meter long cylinder with a diameter of 4.9 meters. The primary and secondary propulsion systems were at the back end of the target vehicle with the attitude control gas tanks and the main propellant tanks. The docking cone was connected to the front end by shock absorbing dampers. Acquisition running lights and target vehicle status display indicators were situated on the front end. A 2.1 meter long retractable L-band boom antenna extended from the side of the cylinder near the front. Tracking and command of the GATV were also aided by a rendezvous beacon, two spiral L-band antennas, two tracking antennas (C-band and S-band), two VHF telemetry antennas, and a UHF command antenna. Micrometeoroid packages and other experiments could also be mounted on the GATV. Gemini Program The Gemini program was designed as a bridge between the Mercury and Apollo programs, primarily to test equipment and



http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=GEM9TA



mission procedures in Earth orbit and to train astronauts and ground crews for future Apollo missions. The general objectives of the program included: long duration flights in excess of of the requirements of a lunar landing mission; rendezvous and docking of two vehicles in Earth orbit; the development of operational proficiency of both flight and ground crews; the conduct of experiments in space; extravehicular operations; active control of reentry flight path to achieve a precise landing point; and onboard orbital navigation. Each Gemini mission carried two astronauts into Earth orbit for periods ranging from 5 hours to 14 days. The program consisted of 10 crewed launches, 2 uncrewed launches, and 7 target vehicles, at a total cost of approximately 1,280 million dollars.

Launch Date: 1966-05-17 Launch Vehicle: Atlas-Agena D Launch Site: Cape Canaveral, United States Mass: 3252.0 kg

Foto:Gemini 9 Target A


Transit 13 was a US Navy navigation satellite launched by a Scout A rocket. Transit, one of the first operational satellite systems, was also known as the Navy Navigation Satellite (NNS). The Transit spacecraft were developed for updating the inertial navigation systems on board US Navy Polaris submarines, and later for civilian use. Transit receivers used the known characteristics of the satellite's orbit, measured the Doppler shift of the satellite's radio signal, and thereby

calculated the receivers position on the earth. As a single spacecraft travelled overhead, the user measured the Doppler shift over a 15 minute period by receiving timing marks and satellite orbital information on two separate frequencies, 149.99 and 399.97 MHz. These signals were corrected for ionospheric refraction and the information was then fed into the users navigation system. Individual Transit satellites operated for over 10 years. Technical break- throughs during the program included gravity gradient stabilization, the use of radio-isotope thermoelectic generators (RTG), and navigation satellite technologies later used in the GPS system. Transit was superseded by the Navstar global positioning system. The use of the satellites for navigation was discontinued at the end of 1996 but the satellites continued transmitting and became the Navy Ionospheric Monitoring System (NIMS). Launch Date: 1966-05-19 Launch Vehicle: Scout Launch Site: Vandenberg AFB, United States Mass: 50.0 kg

KH-4A 33 (OPS 1778)

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Thor Agena D rocket. It was a KH-4A (Key Hole-4A) type spacecraft. The stellar camera shutter of bucket "2" remained opened for approximately 200 frames. Launch Date: 1966-05-24 Launch Vehicle: Thor Launch Site: Vandenberg AFB, United States Mass: 1500.0 kg

Kosmos 119 (DS-U2-I #1)

Cosmos 119 was a Soviet DS type military satellite launched from Kapustin Yar. DS (Dnepropetrovsk Sputnik) were small satellites built by Yangel's OKB-586 / KB Yuzhnoye in the Ukraine for launch by the




http://space.skyrocket.de/doc_sdat/ds-u2-i.htm

http://nssdc.gsfc.nasa.gov/planetary/image/gemini_atv_9f.jpg



same KB's Kosmos launch vehicles. They were used for a wide range of military and scientific research and component proving tests Launch Date: 1966-05-24 Launch Vehicle: Modified SS-4 (Sandal IRBM) plus Upper Stage Launch Site: Kapustin Yar, U.S.S.R Mass: 250.0 kg

Explorer 32 (AE B)

Explorer 32 was an aeronomy satellite which was designed to directly measure temperatures, composition, densities, and pressures in the upper atmosphere on a global basis. The satellite was a stainless steel, vacuum-sealed sphere, 0.889 m in diameter. The experimental payload included one ion and two neutral mass spectrometers, three magnetron density gauges, and two electrostatic probes. Additional equipment included optical and magnetic aspect sensors, magnetic attitude and spin rate control systems, and a tape recorder for data acquisition at locations remote from ground receiving stations. Power was supplied by silver-zinc batteries and a solar cell array mounted on the satellite exterior. Two identical pulse-modulated telemetry systems and a canted turnstile antenna were employed. The two neutral-particle mass spectrometers failed about 6 days after launch. The remaining experiments operated satisfactorily and provided useful data for most of the 10-month satellite lifetime. The spacecraft ceased to function due to battery failures which resulted from depressurization of the sphere Launch Date: 1966-05-25 Launch Vehicle: Delta Launch Site: Cape Canaveral, United States Mass: 224.5 kg

Foto: Explorer 32 (AE B) [NASA]

Surveyor 1

(30 de mayo de 1966 / 2 de junio de 1966) - 995 kg Descenso en el Océano de las Tempestades a una velocidad de 22 m/min. Emite 11.150 fotografías hasta el 13 de julio de 1966. Último contacto fue el 7 de enero de 1967. Porta una cámara de TV y más de 100 sensores para medir las condiciones de la nave. Prueba que el suelo lunar aguanta el peso de una nave. Alunizó a 2,5ºS-43,2ºW. El Programa Surveyor fue el tercer y último programa norteamericano de sondas lunares automáticas con capacidad fotográfica, de análisis químico y excavación del suelo.

Historia

http://space.skyrocket.de/doc_sdat/explorer_ae-b.htm


http://es.wikipedia.org/wiki/13_de_julio


http://es.wikipedia.org/wiki/7_de_enero


http://es.wikipedia.org/wiki/C%C3%A1mara

http://es.wikipedia.org/wiki/Sensor

http://es.wikipedia.org/wiki/Peso

http://es.wikipedia.org/wiki/Sonda

http://es.wikipedia.org/wiki/Fotograf%C3%ADa

http://es.wikipedia.org/wiki/Qu%C3%ADmica



Se trató de 7 misiones con 5 éxitos, lanzadas entre el 31 de mayo de 1966 y el 7 de enero de 1968 y cuyos objetivos en conjunto fueron: posibilidad de realizar alunizajes suaves, transformándose en base lunar, proporcionar información básica y realizar estudios científicos sobre la superficie de la Luna para el programa Apollo. El diseño, desarrollo y construcción de la primera sonda fue realizado por el Jet Propulsion Laboratory el 1 de marzo de 1961 mediante contrato con la Hughes Aircraft Company que encargó su elaboración a la Ryan Electronics, Santa Barbara Research Center, National Waterlift Corp. y Thiokol Chemical Corporation. Características La estructura básica de estas sondas es similar en todas, y solamente se diferencian en el instrumental que llevan a bordo. Poseen tres patas en forma tubular con amortiguadores y pies articulados de aluminio con un sistema en panal para absorber el golpe del alunizaje. En el centro de la estructura lleva un mástil de 3 m de altura en el que se localizan dos paneles solares con 3.960 células y un sistema de antena plana, dos antenas omnidireccionales y dos cajas de control de temperatura dónde se aloja el equipo electrónico. Su diámetro es de 4,30 m con el trípode desplegado y un peso de 1.134 kg, siendo el de la carga de instrumental científico de 154 kg. Estas sondas van equipadas con un retrocohete de combustible sólido y tres motores del tipo Vernier de combustible líquido. El sistema de navegación en el viaje Tierra-Luna es inercial con rastreadores para orientarse con el Sol y la estrella Canopus. Posee un sistema de radar que sirve de altímetro para evaluar la distancia a la superficie lunar y ordenar la intervención del motor de frenado, así como medir la velocidad de descenso y ajustar los motores Vernier. Disponen de un recogedor de muestras o mini excavadora que podía alargarse hasta un máximo de 162,6 cm y podía girar en un arco de 112º. La cuchara podía elevarse hasta una altura de 1 m y profundizar hasta 46 cm en el suelo, depositando el material extraído en uno de los pies donde era fotografiado. La

superficie cubierta por el brazo era de 7 m². En los análisis químicos se empleó un detector equipado con una pastilla radioactiva de curio 242 que bombardeaba la superficie con partículas alfa. El detector descendía hasta la superficie lunar sujeto por un hilo de nylon, y permitía a las partículas penetrar por un espesor de 0,025 mm, identificando los componentes del suelo mediante la energía reflejada por los núcleos de los átomos de los elementos constitutivos de los mismos, cada uno de los cuales posee un poder reflectante específico. Otras identificaciones se consiguieron mediante la medición de la energía de los protones expulsada por los núcleos atómicos. Programa de vuelo Disparo directo mediante un lanzador de la serie Atlas con tramo superior Centauro. A 98 km de altitud se desprenden los paneles aislantes. A 121 km de altitud se abre el cono de protección del Surveyor mientras los motores empujan a la sonda hacia la Luna. La sonda orienta el panel fotoeléctrico hacia el Sol mientras la antena de alto alcance es orientada hacia la Tierra. Tras orientarse con la estrella Canopus, el Surveyor efectúa unas correcciones de ajuste mediante unos cohetes A 1.609 km de la Luna, la sonda tiene una velocidad de 7.884 km A 84 km de la superficie, el motor se activa durante 41 segundos, actuando como retrofreno con un empuje negativo de 4.536 kg. En el momento del encendido, a causa de la atracción lunar la velocidad de la nave es de 9.493 km/h, descendiendo hasta los 110 km/h a 12.000 m de altitud. A 305 m, la velocidad es de 116 km/h, descendiendo la nave de forma suave gracias a los cohetes Vernier guiados por el radar-altímetro. A 3,66 metros de altitud sobre la Luna, y con una velocidad de 5,6 km/h, los cohetes de apagan y la sonda cae al suelo en caída libre a una velocidad de 13 km/h, actuando los amortiguadores y las tres suelas en forma de panal situadas bajo las patas. Se inician los experimentos previstos.

http://es.wikipedia.org/wiki/31_de_mayo


http://es.wikipedia.org/wiki/7_de_enero


http://es.wikipedia.org/wiki/Alunizaje

http://es.wikipedia.org/wiki/Luna

http://es.wikipedia.org/wiki/Apollo

http://es.wikipedia.org/wiki/Jet_Propulsion_Laboratory





http://es.wikipedia.org/wiki/Aluminio

http://es.wikipedia.org/wiki/Panel_solar

http://es.wikipedia.org/wiki/Antena

http://es.wikipedia.org/wiki/Combustible

http://es.wikipedia.org/wiki/Motor

http://es.wikipedia.org/wiki/Vernier

http://es.wikipedia.org/wiki/Canopus

http://es.wikipedia.org/wiki/Radar

http://es.wikipedia.org/wiki/Alt%C3%ADmetro

http://es.wikipedia.org/wiki/Velocidad

http://es.wikipedia.org/wiki/Cent%C3%ADmetro

http://es.wikipedia.org/wiki/M%C2%B2

http://es.wikipedia.org/wiki/Curio

http://es.wikipedia.org/wiki/Nylon

http://es.wikipedia.org/wiki/%C3%81tomo

http://es.wikipedia.org/wiki/Prot%C3%B3n

http://es.wikipedia.org/wiki/Atlas_(cohete)

http://es.wikipedia.org/wiki/Sol

http://es.wikipedia.org/wiki/Canopus_(estrella)

http://es.wikipedia.org/wiki/Km



Junio 1966

ATDA (TDA 4) Gemini 9 Target B

The Gemini 9 Augmented Target Docking Adapter (ATDA) was launched from Cape Canaveral using an Atlas-Agena D rocket at 10:00:02 a.m. EST (15:00:02.363 UT) on 1 June 1966. The spacecraft was successfully injected into a near-circular 304 km orbit, but telemetry signals indicated that the launch shroud, which covered the docking adaptor, had separated but had not been jettisoned. This was confirmed when Gemini 9 was launched two days later and the astronauts observed the launch shroud still on the ATDA blocking the docking port, looking, according to Tom Stafford, like an "angry alligator". Rendezvous within 8 meters of the ATDA was achieved by Gemini 9 on the third revolution. The shroud had not jettisoned because the lanyards had been installed improperly with the loose ends taped down, due to "insufficiently detailed" instructions. Plans to cut the fiber glass shroud loose were considered but discarded as too dangerous to the astronauts. The flight plan was then revised and Gemini 9 completed two different equiperiod rendezvous maneuvers with the ATDA. The ATDA was left in a 290 x 300 km orbit. The Augmented Target Docking Adapter had been prepared as a backup target in case of an Agena Target Vehicle failure. The ATDA was a short cylinder consisting of a target docking adapter cone mounted on front and containing a communications system, a guidance and control system, and a reaction control system. It also had running lights, but unlike the Gemini Agena Target Vehicles, the ATDA was not stabilized. Gemini Program The Gemini program was designed as a bridge between the Mercury and Apollo programs, primarily to test equipment and mission procedures in Earth orbit and to train astronauts and ground crews for future Apollo missions. The general objectives of the program included: long duration flights in excess of of the

requirements of a lunar landing mission; rendezvous and docking of two vehicles in Earth orbit; the development of operational proficiency of both flight and ground crews; the conduct of experiments in space; extravehicular operations; active control of reentry flight path to achieve a precise landing point; and onboard orbital navigation. Each Gemini mission carried two astronauts into Earth orbit for periods ranging from 5 hours to 14 days. The program consisted of 10 crewed launches, 2 uncrewed launches, and 7 target vehicles, at a total cost of approximately 1,280 million dollars. Launch Date: 1966-06-01 Launch Vehicle: Atlas-Agena B Launch Site: Cape Canaveral, United States Mass: 794.0 kg

Foto :Gemini 9 Target B

Gemini 9

Insignia de la mission

Estadísticas de la misión Nombre de la misión: Gemini 9A Número de tripulantes: 2 Lanzamiento: 3 de junio, 1966 13:39:33.335 UTC Cabo Cañaveral LC 19 Reentrada: 6 de junio, 1966 14:00:23 UTC Duración: 3 días 0 horas 20 minutos 50 segundos Distancia Recorrida: ? Órbitas: 47

http://space.skyrocket.de/doc_sdat/atda.htm



http://es.wikipedia.org/wiki/3_de_junio



http://es.wikipedia.org/wiki/6_de_junio




Tripulación del Gemini 9A

(I-D: Stafford, Cernan) Launch, orbit and landing data Launch date: 03.06.1966 Launch time: 13:39 UT Launch site: Cape Canaveral Launch pad: LC-19 Altitude: 311,5 km Inclination: 28,86° Landing date: 06.06.1966 Landing time: 14:00 UT Landing site: 27° 52' N, 75° 0,4' W

Crew No. Surname Given name Job 1 Stafford Thomas Patten "Tom" CDR 2 Cernan Eugene Andrew "Gene" PLT

Flight Launch from Cape Canaveral; landing 500 km east of Cape Canaveral in the Atlantic Ocean. Former prime crew (Elliot See and Charles Bassett) was killed in an T-38 training airplane crash on February 28, 1966, so their backups Stafford and Cernan became prime crew. Astronauts Lovell and Aldrin became the new backup-crew. The main goals of this mission were to rendezvous and dock with the Augmented Target Docking Adapter (ATDA) and to conduct extravehicular activities (EVA). Launch of the ATDA and of Gemini 9A were successful, but the docking with the Augmented Target Docking Adapter ADTA was not achieved because the shroud on the ATDA failed to separate. EVA by Cernan (2h 07m). The secondary objective of this EVA, evaluation of the

astronaut maneuvering unit (AMU), was not achieved. Every work during the EVA took much longer, than expected and he had could not maintain body position. Cernan became exhausted and the face plate fogged over - he had to grope and couldn't see anything. At the end of his EVA he had big problems to return into the capsule and to close the hatch. Stafford had to help him. Cernan later was bitterly disappointed that he had been unable to fly the Air Force's maneuvering unit. Crew also performed several other experiments, so as bioassay of body fluids (the only medical experiment onboard). A micrometeorite collection package (mounted on the ATDA) should had been picked by Cernan during his EVA. Due of his blindness from the fogging face plate, he only was able to take some photos of this package. Another package was mounted on the Gemini capsule and could be retrieved. Other experiments were the zodiacal light photography and the airglow horizon photography, which were partly successful, but also impaired through Cernan's problems during his spacewalk. The splashdown, only 3 km far from the recovery ship, the USS Wasp, was broadcast live on TV.

Photos / Drawings

http://www.spacefacts.de/maps/english/lc-19.htm

http://www.spacefacts.de/maps/english/gemini-9.htm

http://www.spacefacts.de/bios/astronauts/english/stafford_thomas.htm

http://www.spacefacts.de/bios/astronauts/english/cernan_eugene.htm

http://www.spacefacts.de/bios/astronauts/english/see_elliott.htm

http://www.spacefacts.de/bios/astronauts/english/bassett_charles.htm



http://www.spacefacts.de/bios/astronauts/english/lovell_james.htm

http://www.spacefacts.de/bios/astronauts/english/aldrin_buzz.htm









KH-7 29 (OPS 1577)/ OPS 1856 KH 7-29 Capsule

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Atlas Agena D rocket. It was a KH-7 (Key Hole-7) type spacecraft


OGO 3

The purpose of the OGO 3 spacecraft, the third of a series of six Orbiting Geophysical Observatories, was to conduct many diversified geophysical experiments to obtain a better understanding of the earth as a planet. OGO 3 consisted of a main body that was parallelepipedal in form, two solar panels, each with a solar-oriented experiment package (SOEP), and two orbital plane experiment packages (OPEP). One face of the main body was designed to be earth pointing (Z axis), and the line connecting the two solar panels (X axis) was intended to be perpendicular to the earth-sun-spacecraft plane. The solar panels were able to rotate about the X axis. The OPEPs were mounted on, and could rotate about, an axis which was

parallel to the Z axis and attached to the main body. Due to a failure in the attitude control subsystem on July 23, 1966, the spacecraft was put into a permanent spin mode about the Z axis. Both the orientation of the spin axis and the spin period were variable, the latter usually in the range 90 s to 125 s. At launch, the local time of apogee was 2300 h. OGO 3 carried 21 experiments. Thirteen of these were particle studies, and two were magnetic field studies. In addition, there was one each of the following types of experiments: interplanetary dust, VLF, Lyman-alpha, gegenschein, atmospheric composition, and radio astronomy. Real-time data were transmitted at 1, 8, or 64 kbs depending on the distance from the spacecraft to earth. Playback data were tape recorded at 1 kbs and transmitted at 64 kbs. Two wideband transmitters, one feeding into an omnidirectional antenna and the other feeding into a directional antenna, were used to transmit data. A special purpose telemetry system, feeding into either antenna, was also used to transmit wideband data in real time only. Tracking was accomplished by using radio beacons and a range and range-rate S-band transponder. Routine spacecraft operation was discontinued on December 1, 1969, after which only data from Heppner's experiment (E-11) was acquired. All spacecraft support terminated on February 29, 1972. By March 1971 spacecraft perigee had increased to 16,400 km and the inclination had increased to 75.8 de

Launch Date: 1966-06-07 Launch Vehicle: Atlas-Agena B Launch Site: Cape Canaveral, United States Mass: 514.8 kg


Cosmos 120 was a first generation, low resolution Soviet photo surveillance satellte launched from the Baikonur cosmodrome aboard a Soyuz rocket. The film capsule was recovered after 8 days. Launch Date: 1966-06-08 Launch Vehicle: Modified SS-6 (Sapwood) with 2nd Generation (Longer) Upper Stage Launch Site: Tyuratam (Baikonur





http://space.skyrocket.de/doc_sdat/ogo.htm




Cosmodrome), U.S.S.R Mass: 4730.0 kg

ERS 16

ERS 16 was an Air Force technology satellite launched from Vandenberg AFB aboard an Atlas Agena D rocket. It performed metal-to-metal bonding experiments. Launch Date: 1966-06-09 Launch Vehicle: Atlas Launch Site: Vandenberg AFB, United States Mass: 4.5 kg

RTS-1 1/ SECOR 6 (EGRS 6) MIDAS 10 / ORS 2

Foto:RTS-1 payload

SECOR 6 (SEquential COllation of Range) was a US Army/USAF spacecraft launched from Vandenberg AFB aboard an Atlas Agena-D rocket. This small geodetic satellite was used to precisely determine points on the earth. Experiments with these led to Timation, and finally to the GPS Navstar system. ORS 2 (ERS 16): Cold welding experiments

OV3 4 (PHASR)

OV3-4 was a radiation research satellite for the US Air Force.


IDCSP 1 (OPS 9311) IDCSP 2 (OPS 9312) IDCSP 3 (OPS 9313) IDCSP 4 (OPS 9314) IDCSP 5 (OPS 9315) IDCSP 6 (OPS 9316) IDCSP 7 (OPS 9317) GGTS 1

The Initial Defense Communications Satellite Program provided the Pentagon with its first geosynchronous communications system. IDCSP satellites were spin-stabilized 26 sided polygons, 86 cm in diameter, covered with solar panels, and had a mass of 45 kg. Eight were dispersed on a single Titan 3C rocket into slightly sub-synchronous orbit where they would drift about thirty degrees per day. The idea was that a backup was always visible to the earth station if one failed. IDCSP satellites transmitted reconnaisance photos and other data during the Viet Nam war. They were succeeded by NATO and DSCS true geosynchronous satellites.

Launch Date: 1966-06-16 Launch Vehicle: Titan III-C Launch Site: Cape Canaveral, United States Mass: 45.0 kg


Cosmos 121 was the tenth Russian experimental meteorologcal satellite and the first launched from the Plesetsk site. Although the satellite was intended primarily for nonscientific reconnaissance purposes, it carried supplemental equipment for conducting meteorological studies to aid in the development of

















instruments for operational meteorological satellites. The primary meteorological objective of the Cosmos 121 mission was to measure the intensity of reflected and scattered radiation in the 0.6- to 0.8-micron band to determine the spatial variation of the radiation spectrum in the mesoscale range. THe spin-stabilized satellite was in the form of a cylinder with hemispherical ends and was 5 m long and 2.44 m in diameter. The announced scientific instrumentation consisted of an earthward-facing high-resolution photometer whose optical axis was parallel to the local vertical. Spacecraft telemetry (19.995 MHz) was handled via antennas mounted on the ends of the satellite body. The mission was a success. After nearly 8 days in orbit, the satellite reentered the atmosphere on June 25, 1966, and the satellite instrumentation package was successfully recovered. Launch Date: 1966-06-17 Launch Vehicle: Modified SS-6 (Sapwood) with 2nd Generation (Longer) Upper Stage Launch Site: Plesetsk, U.S.S.R Mass: 4730.0 kg

KH-4A 34 (OPS 1599)

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Thor Agena D rocket. It was a KH-4A (Key Hole-4A) type spacecraft. Failure of velocity/altitude programmer produced poor imagery after revolution 5.


PAGEOS 1

The PAGEOS (Passive Geodetic Earth Orbiting Satellite) spacecraft was a 30.48-m inflatable sphere, and had no instrumentation on board. It was the second (following GEOS 1) NASA satellite in the National Geodetic Satellites Program. PAGEOS 1 was made up of 84 gores and 2 pole caps of 0.0127-mm aluminized mylar film. The gores were 48 m

long with maximum width of 1.24 m and the pole caps were 1.02 m in diameter. The primary purpose of the satellite was to provide a tracking target for geodetic purposes. It had a specular reflectance of 0.862, and a diffuse reflectance of 0.029, providing a reflecting light source whose brightness was relatively independent of observer-satellite-sun phase angle. The surface was also 97% reflectant for microwave energy in the range from 17 to 4E5 kHz. The launch, orbit, separation, inflation and initial operation were nominal, with more than 40 ground stations participating in the observation program. The orbit was generally considered too high for drag-density study, although some work was done in this area by the Smithsonian Astrophysical Observatory. For a more detailed description, see David E. Bowker, "PAGEOS Project Compilation of Information for Use of Experimenter" (TRF B01718), NASA-TM-X-1344, 1967 Launch Date: 1966-06-24 Launch Vehicle: Thrust Augmented Thor-Agena D Launch Site: Vandenberg AFB, United States Mass: 56.7 kg

Foto:PAGEOS 1 [NASA]

Kosmos 122 (Meteor-1 #3)

Cosmos 122 was the first announced Russian meteorological satellite and the last in a series of prototype meteorological satellites that included Cosmos 44, 58,


http://space.skyrocket.de/doc_sdat/pageos.htm



100, and 118. It was the last meteorological satellite launched from the Tyuratam site with an A-1 launch vehicle at a 65-deg orbital inclination, and it provided a transition from the prototype series to the Cosmos "Meteor" experimental weather satellite system. Cosmos 122 was orbited to test meteorological instrumentation designed for obtaining images of cloud cover, snow cover, and ice fields on the day and night sides of the earth and for measuring fluxes of outgoing radiation reflected and radiated by the earth-atmosphere system. The instrumentation consisted of (1) two vidicon cameras for daytime cloudcover pictures, (2) a high-resolution scanning IR radiometer for nighttime and daytime imaging of the earth and clouds, and (3) an array of narrow- and wide-angle radiometers covering the 0.3- to 3-, 8- to 12-, and 3- to 30-micrometer channel for measuring the intensity of radiation reflected from the clouds and oceans, the surface temperatures of the earth and cloud tops, and the total flux of thermal energy from the earth-atmosphere system into space, respectively. The satellite was in the form of a large cylindrical capsule, 5 m long and 1.5 m in diameter. Two large solar cell panels of three segments each were deployed from opposite sides of the cylinder after satellite separation from the launch vehicle. The solar panels were rotated to constantly face the sun during satellite daytime by means of a sun sensor controlled drive mechanism fitted in the top end of the center body. The meteorological instruments were housed in a hermetically sealed compartment located in thelower part of the capsule, while the basic satellite servicing systems were contained in a special hermetically sealed compartment in the upper part of the capsule. Data were transmitted to earth at a frequency of 90 MHz by means of a steerable high-gain parabolic antenna that was attached to the center section of the satellite body by a long arm. The satellite was triaxially stabilized by a series of inertial flywheels, driven by electric motors, whose kinetic energy was dampened by torques produced by electromagnets interacting with the earth's magnetic field. Cosmos 122 was oriented by earth sensors with one of its axes directed earthward along

the local vertical, a second oriented along the orbital velocity vector, and a third oriented perpendicular to the orbital plane. This orientation ensured that the optical axes of the instruments were constantly directed earthward. Cosmos 122 ceased operations in late October 1966. Launch Date: 1966-06-25 Launch Vehicle: Modified SS-6 (Sapwood) with 1st Generation Upper Stage Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 4730.0 kg

Julio 1966

Explorer 33 (IMP D)

· Otros nombres: IMP-D (Interplanetary Monitoring Platform), 1966-058A, AIMP 1, Anchored IMP 1, Explorer 33, 02258 · Fecha de lanzamiento: 1 de julio de 1966 a las 16:04:00 GMT · Masa seca en órbita: 212 kg La sonda Explorer 33 era una nave estabilizada por giro con este eje paralelo al plano de la eclíptica y con un ritmo de giro variable entre los 2,2 y los 3,6 segundos. Su objetivo fundamental era el estudio del medio interplanetario incluyendo el plasma, las partículas cargadas, los campos magnéticos de la Tierra y entre los planetas y los rayos X solares. Debía convertirse en la primera sonda norteamericana que orbitara la Luna pero un mal funcionamiento de los motores aceleró la sonda y la nave no llegó a alcanzar la órbita lunar quedando en una órbita muy excéntrica de la Tierra. A pesar de ello pudo cumplir con sus objetivos. Durante el primer periodo de tres años de vida la sonda varió su perigeo entre los 6 y los 44 radios terrestres y el apogeo entre los 70 y los 135 radios terrestres con una inclinación respecto al ecuador variable entre los 7 y los 60 grados. Los periodos principales de adquisición de datos fueron:

http://space.skyrocket.de/doc_sdat/explorer_imp-d.htm



- El primero entre el 1 de julio de 1966 (lanzamiento) al 14 de enero de 1970 - El segundo entre el 21 de febrero y el 6 de marzo de 1970 - El tercero entre el 31 de julio y el 14 de septiembre de 1970 - El cuarto entre el 15 de enero y el 28 de febrero de 1971 - El quinto entre el 23 de marzo y el 31 de mayo de 1971 - Y el sexto y último entre el 23 de agosto y el 15 de septiembre de 1971 Tras el 21 de septiembre de 1971 no se obtuvieron más datos ya que se perdió definitivamente el contacto con la nave.

Foto: Una réplica de la sonda Explorer-33

Apollo 203

The Apollo/Saturn AS-203 mission was an unmanned test of the S-IVB (second stage) and the Iu (instrument unit) of the Saturn V to obtain flight information under orbital conditions. The configuration of the Saturn IB was made to match the Saturn V as closely as possible. The two-stage launch vehicle boosted a payload consisting of the S-IVB, Iu, and a nose cone into a 188 km circular orbit with a period of 88.21 minutes and an inclination of 31.94 degrees. The S-IVB engine burned once in the Earth's atmosphere and then was shut down. The engine's capability to restart after coast was demonstrated. Flight information was obtained on venting and chill down systems, attitude and guidance control, thermal control, and performance of the propellant tanks. Two cameras were mounted to take photos to record the behavior of the liquid hydrogen fuel in the

tanks. One of the cameras failed before launch, the other transmitted images to Earth. During the fourth orbit internal pressures built up in the S-IVB stage while a pressure differential test was being performed. The pressures built up well in excess of design values and the stage fragmented. However, all mission objectives were achieved. Launch Date: 1966-07-05 Launch Vehicle: Saturn 1B Launch Site: Cape Canaveral, United States Mass: 26552.0 kg

Foto:Apollo AS-203

Foto:Apollo 203 [GDK]

Proton 3

Proton 3 was the third in a series of spacecraft from which cylindrical payloads containing instruments for studying cosmic rays of energies up to 10 to the 13 eV were launched. Proton 3 also studied the nuclear interaction of particles in the range of 10 to the 12 eV. This payload decayed after 72 days in orbit.

Launch Date: 1966-07-06 Launch Vehicle: Proton Booster Plus Upper Stage

http://space.skyrocket.de/doc_sdat/apollo-203.htm


http://nssdc.gsfc.nasa.gov/image/spacecraft/as203_launch.jpg



Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 12200.0 kg

Kosmos 123 (DS-P1-Yu #6)


KH-7 30 (OPS 1850)


OV1 7

Launch Date: 1966-07-13 Launch Vehicle: Atlas D Launch Site: Vandenberg AFB, United States Mass: 118.0 kg

PasComSat (OV1 8) / SPP 33 *

PasComSat (Passive Communication Satellite) was an inflateable gridsphere launched on an OV1 propulsion module. A gridsphere is a balloon consisting of wire mesh embedded in a photolyzable balloon.

After inflation in space, the UV radiation causes the ballon to vaporize, leaving a wire frame in spherical shape. This gridsphere reflects radio waves as good as a aluminized balloon, but has much less atmospherical drag. A follow up was launched as experiment

Foto: PASCOMSAT (OV1 8) [USAF]



Cosmos 124 was a first generation, low resolution Soviet photo surveillance satellite launched from the Baikonur cosmodrome aboard a Soyuz rocket. The film capsule was recovered after 8 days


GATV 10 (TDA 1A)

The GATV (Gemini Agena Target Vehicle) was designed to be launched into Earth orbit prior to a Gemini mission and used for rendezvous and docking practice




http://space.skyrocket.de/doc_sdat/pascomsat.htm






Gemini 10 Gemini 10 Target


Estadísticas de la misión Nombre de la misión: Gemini 10 Número de tripulantes: 2 Lanzamiento: 18 de julio, 1966 22:20:26.648 UTC Cabo Cañaveral LC 19 Reentrada: 21 de julio, 1966 21:07:05 UTC Duración: 2 días 22 horas 46 minutos 39 segundos Distancia Recorrida: ~1.968.823 km Órbitas: 43

Kosmos 125 (US-A Test #2)

Cosmos 125 was a Soviet Radar Ocean Reconnaissance Satellite (RORSAT) prototype launched from the Baikonur cosmodrome aboard a Soyuz launch vehicle. RORSATs were launched to search the oceans for US Navy task forces and other shipping.

Launch Date: 1966-07-20 Launch Vehicle: Soyuz Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 4000.0 kg


Cosmos 126 was a second generation, high resolution Soviet photo surveillance satellite launched from the Baikonur cosmodrome aboard a Soyuz rocket.

Launch Date: 1966-07-28 Launch Vehicle: Modified SS-6 (Sapwood)

with 2nd Generation (Longer) Upper Stage Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 4730.0 kg

KH-8 1 (OPS 3014)

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Titan 3B rocket. It was a KH-8 (Key Hole-8) type spacecraft.

Launch Date: 1966-07-29 Launch Vehicle: Titan IIIB-Agena D Launch Site: Vandenberg AFB, United States Mass: 3000.0 kg

Agosto 1966

OV3 3

OV3-3 spacecraft was placed into a polar orbit to measure trapped and precipitating particles and correlated electromagnetic wave fields. The spacecraft was spin stabilized at 8 rpm, and its systems performed well for 14 months, until September 1967 when the onboard tape recorder failed. After that time, low-latitude, real-time tracking continued into 1969 when the spacecraft was deactivated


Foto:OV3-3






http://es.wikipedia.org/wiki/21_de_julio


http://space.skyrocket.de/doc_sdat/us-a_test.htm


http://nssdc.gsfc.nasa.gov/image/spacecraft/ov3-3.jpg





KH-4A 35 (OPS 1545) This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Thor Agena D rocket. It was a KH-4A (Key Hole-4A) type spacecraft. All cameras operated satisfactorily. This was the first mission flown with pan geometry modification. Launch Date: 1966-09-08 Launch Vehicle: Thor Launch Site: Vandenberg AFB, United States Mass: 1500.0 kg

Lunar Orbiter 1

Otros nombres: 1966-073A, Lunar Orbiter-A, 02394 Fecha de lanzamiento: 10 de agosto de 1966 a las 19:26:00 GMT Masa seca en órbita: 385.6 kg Consumo de energía: 375 W La sonda Lunar Orbiter 1 fue diseñada con el objetivo de fotografiar amplias y llanas zonas de la superficie lunar para la selección de un lugar de aterrizaje seguro para las futuras sondas Surveyor y las misiones Apollo. Además de instrumentos para el estudio de la superficie, la nave lleva un sensor de intensidad de la radiación y otro de impactos de micrometeoritos. La nave fue lanzada desde Cabo Cañaveral sobre un cohete Atlas/Agena D (SLV-3) y alcanzó una órbita de aparcamiento terrestre a las 19:31 GMT. A las 20:04 se realizó el

encendido de la última etapa del cohete que la puso en trayectoria de transferencia lunar para un vuelo de 90 horas hasta la nuestro satélite, con una corrección de trayectoria realizada el 12 de agosto a las 01:00 GMT.

Lanzamiento de Lunar Orbiter 1

La nave experimentó pronto un fallo del seguidor de la estrella Canopus (posiblemente por un rayo de Sol) y algo de sobrecalentamiento en el viaje hasta la Luna. El problema del seguidor de estrellas fue solucionado ya que se usó la Luna como referencia para la navegación y el exceso de calor se resolvió orientando la sonda 36º en contra del Sol para dejar los instrumentos a la sombra. …………………………………… Tras 92,1 horas de viaje, la nave quedó colocada en una órbita casi ecuatorial alrededor de la Luna, con una altura inicial de 189,1 x 1.866,8 Km., con un periodo de 3 horas y 37 minutos y una inclinación de 12,2 grados. El 21 de agosto el periastro fue bajado hasta los 58 Km. y el 25 de agosto hasta los 40,5 Km. La nave adquirió fotografías de la superficie lunar entre el 18 y el 29 de agosto de 1966, con un error de lectura final que ocurrió el 14 de septiembre de 1966. Se consiguieron un total de 42 imágenes de alta resolución y 187 de mediana resolución de 9 zonas de alto interés para las misiones Apollo, cubriendo unos 5 millones de kilómetros cuadrados de la superficie lunar, consiguiendo un 75% de los objetivos de la misión, a pesar de que varias fotos de alta resolución obtenidas al



comienzo de la misión estaban algo manchadas. Además se obtuvieron las primeras fotografías de la Tierra jamás captadas desde la Luna.

Primera imagen de la Tierra desde la Luna

KH-7 31 (OPS 1832) SSF-B 5 (OPS 6810) 1966-074B

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Atlas Agena D rocket. It was a KH-7 (Key Hole-7) type spacecraft.


Pioneer 7

Otros nombres: 1966-075A, Pioneer-B, 02398 Fecha de lanzamiento: 17 de agosto de 1.966 las 15:20:00 GMT Masa seca en orbita: 138 kg Pioneer 7 was the second in a series of solar-orbiting, spin-stabilized, solar-cell and battery-powered satellites designed to obtain measurements of interplanetary phenomena from widely separated points in space on a continuing basis. The spacecraft carried experiments to study positive ions and electrons in the solar wind, the interplanetary electron density (radio propagation experiment), solar and galactic cosmic rays, and the interplanetary magnetic field. Its main antenna was a high-gain directional antenna. The spacecraft was spin-stabilized at about 60 rpm, and the spin axis was perpendicular to the ecliptic plane and pointed approximately toward the south ecliptic pole. By ground command, one of five bit

rates, one of four data formats, and one of four operating modes could be selected. The five bit rates were 512, 256, 64, 16, and 8 bps. Three of the four data formats contained primarily scientific data and consisted of 32 seven-bit words per frame. One scientific data format was used for the two highest bit rates. Another was used for the three lowest bit rates. The third contained data from only the radio propagation experiment. The fourth data format contained mainly engineering data. The four operating modes were (1) real time, (2) telemetry store, (3) duty cycle store, and (4) memory readout. In the real-time mode, data were sampled and transmitted directly (without storage) as specified by the data format and bit rate selected. In the telemetry store mode, data were stored and transmitted simultaneously in the format and at the bit rate selected. In the duty cycle store mode, a single frame of scientific data was collected and stored at a rate of 512 bps. The time period between which successive frames were collected and stored could be varied by ground command between 2 and 17 min to provide partial data coverage for periods up to 19 h, as limited by the bit storage capacity. In the memory readout mode, data were read out at whatever bit rate was appropriate to the satellite distance from the earth.

Foto:Pioneer 7


Transit 14 was a US Navy navigation satellite launched by a Scout A rocket. Transit, one of the first operational satellite systems, was also known as the Navy Navigation Satellite (NNS).



http://space.skyrocket.de/doc_sdat/pioneer-6.htm





The Transit spacecraft were developed for updating the inertial navigation systems on board US Navy Polaris submarines, and later for civilian use. Transit receivers used the known characteristics of the satellite's orbit, measured the Doppler shift of the satellite's radio signal, and thereby calculated the receivers position on the earth. As a single spacecraft travelled overhead, the user measured the Doppler shift over a 15 minute period by receiving timing marks and satellite orbital information on two separate frequencies, 149.99 and 399.97 MHz. These signals were corrected for ionospheric refraction and the information was then fed into the users navigation system. Individual Transit satellites operated for over 10 years. Technical break- throughs during the program included gravity gradient stabilization, the use of radio-isotope thermoelectic generators (RTG), and navigation satellite technologies later used in the GPS system. Transit was superseded by the Navstar global positioning system. The use of the satellites for navigation was discontinued at the end of 1996 but the satellites continued transmitting and became the Navy Ionospheric Monitoring System (NIMS). Launch Date: 1966-08-18 Launch Vehicle: Scout Launch Site: Vandenberg AFB, United States Mass: 58.0 kg

RTS-1 2 / SECOR 7 (EGRS 7) / MIDAS 11 / ORS 1 / ERS 15

Nation: USA

Type / Application:

Early Warning

Operator: USAF

Contractors:

Equipment: RTS-1 ir telescope on spin table

Configuration: Agena-D with payload module and solar arrays


This Missile Defense Alarm System (MIDAS) Early Warning satellite was launched from Vandenberg AFB aboard an Atlas Agena D rocket.

The MIDAS program, also known as Air Force Program 461, carried out 12 launches between 1960 and 1966 using four different types of increasingly sophisticated infrared sensors. The objective was to develop a satellite that could carry an infrared sensor to detect ICBM launches. Launch Date: 1966-08-19 Launch Vehicle: Atlas-Agena D Launch Site: Vandenberg AFB, United States Mass: 2000.0 kg ERS 15 was an Air Force technology satellite launched from Vandenberg AFB aboard an Atlas Agena D rocket. It performed cold welding experiments.

Luna 11 (E-6LF #1)

Otros nombres: 1966-078A, Lunik 11, 02406 Fecha de lanzamiento: 24 de agosto de 1.966 a las 08:09:00 GMT Masa seca en órbita: 1.640 kg Fue lanzada hacia la Luna por un cohete Molniya el 24 de agosto de 1966 como parte del programa soviético Luna y como modificación de su segunda generación (modelo Ye-6LF). Entró en la órbita lunar el 27 de agosto a las 21:47 GMT, dos semanas después de Lunar Orbiter de la NASA, quedando en una órbita de 160 x 1.193 kilómetros y 27º de inclinación. Entre sus objetivos estaba el estudio de: - Las emisiones lunares de rayos gamma y X para determinar la composición química. - Anomalías gravitacionales (mascones) descubiertas por Luna 10. - Concentración de flujos de meteoros cerca de la Luna - Intensidad de radiación en el entorno lunar Además debía encargarse de realizar las primeras fotografías lunares obtenidas desde la órbita. Para todo ello se usó el bus básico Ye-6 al que se dotó de diversos instrumentos y de una cámara similar a la usada en Zond-




3, pero reemplazando la pequeña cápsula aterrizadora de la serie.… ……………….. La resolución de las fotos se estimó teóricamente en unos 15 a 20 metros por píxel, sin embargo la cámara falló durante la misión cuando la sonda perdió su capacidad de orientación al entrar un objeto extraño en una de las toberas utilizadas. En total se realizaron 137 transmisiones de radio y 277 órbitas antes de que las baterías fallaran el 1 de octubre de 1966.

Esquema sondas Luna 11 y 12

AS-202

The Apollo-Saturn 202 (AS-202) mission was an unmanned suborbital flight to test the Saturn 1B launch vehicle and the Apollo Command and Service Modules. The objectives of the flight were to verify the structural integrity, launch loads, stage separation, and operation of subsystems of the Saturn 1B, and evaluate the Apollo spacecraft separations, emergency detection system, subsystems, heatshield at high re-entry velocity, and mission support facilities. All objectives were achieved. The Saturn 1B and its payload consisting of the Apollo CSM-011 were launched from complex 34 of the eastern test range at Cape Canaveral. After both stages of the Saturn 1B completed their burns and

separated, the service module propulsion engine burned for 3 minutes, 35 seconds to boost the spacecraft to a peak altitude of 1,128.6 km. The rapid restart capability of the service module's engines was tested by firing three more times, the last separating the service module from the command module. The firings also accelerated the command module re-entry to greater than 8900 meters/sec (32,000 km/hr). Maximum temperature of the spacecraft exterior was calculated at about 1500 deg. C, temperature inside the cabin was 21 deg. C (70 F). The main parachutes deployed at 7250 meters altitude and the spacecraft splashed down at 18:49 UT, 93 minutes after liftoff. Splashdown occurred in the Pacific Ocean at 16.11 N, 168.97 E, roughly 800 km SE of Wake Island and 370 km from target. The capsule was recovered by the aircraft carrier U.S.S. Hornet at 03:17 UT on 26 August. Launch Date: 1966-08-25 Launch Vehicle: Saturn 1B Launch Site: Cape Canaveral, United States Mass: 25809.7 kg

Foto:AS-202

IDCSP (8) / IDCSP IDCSP (9) (10) (11) (12) (13) (14) GGTS 2 Launch vehicle failure.


http://nssdc.gsfc.nasa.gov/image/spacecraft/as_202.jpg



The IDCSP (Initial Defence Communication Satellite Program) provided the Pentagon with its first geosynchronous communications system and replaced the cancelled ADVENT project. GGTS 2 mission failed due to a launch vehicle failure. Launch Date: 1966-08-26 Launch Vehicle: null Launch Site: Cape Canaveral, United States Mass: 362.0 kg



Septiembre 1966

KH-4A 36 (OPS 1703)

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Thor Agena D rocket. It was a KH-4A (Key Hole-4A) type spacecraft. All cameras operated satisfactorily


GATV 11 (TDA 6)


Gemini 11 /Gemini 11 Target


Nombre de la misión: Gemini 11 Número de tripulantes: 2 Lanzamiento: 12 de septiembre, 1966 14:42:26.546 UTC Cabo Cañaveral LC 19 Reentrada: 15 de septiembre, 1966 13:59:35 UTC Duración: 2 días 23 horas 17 minutos 8 segundos Distancia Recorrida: ~1.983.565 km Órbitas: 44

Tripulación del Gemini 11

(I-D: Gordon, Conrad)

Crew

No. Pais Surname Given name 1 EE.UU Conrad Charles, Jr. "Pete" 2 EE.UU Gordon Richard Francis, Jr.

Flight

Launch from Cape Canaveral; landing 1330 km southeast from Cape Canaveral in the Atlantic Ocean…………………………………

http://space.skyrocket.de/doc_sdat/advent.htm


http://es.wikipedia.org/wiki/12_de_septiembre







The main goal of this flight was again to dock with an Agena target vehicle. Secondary objectives included docking practice, an EVA, 11 scientific experiments, docked maneuvers, a tethered vehicle test, demonstrating automatic reentry, and parking the GATV. The launch was postponed twice; On September 9 due to a small leak in the first stage oxidizer tank of the GLV; and on the 10th due to a suspected malfunction of the autopilot on the Agena-capsule. Docking with unmanned Agena target vehicle GATV-11 was completed after five flight maneuvers and only 94 minutes after the launch. There were no fuel problems and the crew began docking practice (two dockings and re-dockings of both astronauts). Two EVA`s by Gordon (0h 38m) and (2h 08m). In the first EVA he attached the tether from the GATV to the spacecraft docking bar, but became fatigued too, even the GATV was modificated with handrails. The face plate of his helmet fogged and this EVA was shortened. The whole compex of two spacecrafts was then brought up to a high apogee record of 1.360 km, using the boosters of the Agena target vehicle. The spacecrafts were then redocked and the joined pair was brought into a rotation to build a small gravity in the spacecrafts. The rotation rate checked out at 55 degrees per minute, and the crew could test for a minute amount of artificial gravity, but they did not sense any physiological effect of gravity. All in all 12 experiments performed (9 scientific and 3 technological), but only two photograph experiments were new. The other seven - weather, terrain, and airglow horizon photography, radiation and zero-g effects, ion-wake measurement, nuclear emulsion, and the ultraviolet astronomical camera - and all three technological experiments - mass determination, night image intensification, and power tool evaluation - had already been assigned to previous missions. The night image intensification was enjoyed by the astronauts, but were also a little bit handicapped due to a dirty window on Conrads site. At the end of the mission the first fully

automatic controlled re-entry was performed. The recovery ship was the USS Guam.

Photos / Drawings

DMSP-4A F1 (OPS 6026)

The cylindrically shaped Block 4 satellites incorporated two new one-inch diameter vidicon cameras, video (2), a large capacity tape recorder, and an all-digital command subsystem with magnetic core memory, giving fully programmable coverage of either direct readout or readout of recorded data without interference. Nominal satellite spin rate was decreased to reduce smear, permitting a higher resolution TV system for improved picture quality. Dual cameras and a high capacity recorder provided complete daily coverage of the entire northern hemisphere and tactical coverage anywhere on the earth. An improved IR 'C' system was incorporated on this spacecraft. The Defense Meteorological Satellite Program's Block 4 space segment consisted of satellites in 450 nautical mile sun-synchronous polar orbits each carrying a payload of meteorological sensors. Primary cloud imaging sensors capable of globally viewing the earth in the visible and infrared spectrums were carried by every satellite. The ascending node of the satellites were either in the early morning time period or at mid-day. The final data

http://www.spacefacts.de/bios/astronauts/english/gordon_richard.htm

http://www.spacefacts.de/bios/astronauts/english/conrad_charles.htm



product was a film product directly usable for imagery analysis. Originally part of a classified system of USAF weather satellites, this spacecraft mission was not revealed until March 1973. Launch Date: 1966-09-15 Launch Vehicle: Thor Launch Site: Vandenberg AFB, United States Mass: 150.0 kg

Foto:DMSP-4A

KH-7 32 (OPS 1686) SSF-B 6 (OPS 6874)



Kosmos (129) (Zenit-2 #(34))

Nation: U.S.S.R.

Type / Application:

Reconnaissance, photo (low resolution, film return type), ELINT

Operator:

Contractors:

Equipment: Ftor-2 Camera package, Kust-12M ELINT package

Configuration: Zenit bus

Propulsion:

OGCh #51966-088ª

OGCh () was an attempt to create an orbital warhead to circumvent the US ballistic missile early warning radars. It consisted of a conical reentry vehicle and an maneuvering stage. The manuevering unit, which oriented the spacecraft in orbit and autonomously determined when to make the braking manoeuvre to bring the re-entry vehicle down from orbit. It included an inertial navigation system and a radar altimeter which measured the altitude of the orbit and determined when to make the braking manoeuvre. The retro-rocket engine was a single chamber engine, the Yangel RD-854, with a vacuum thrust of 7.7 tons. Four nozzles on the sides of the main engine (using exhaust gases from the main engine) provided steering capability. Four additional tangentially located nozzles provided yaw capability. Each nozzle was throttleable. A solid fuel cartridge then spun up the turbine assembly of the liquid propellant (N2O4/UDMH) braking engine. Although an orbital flight reduced the payload mass and reduced accuracy in comparison to ballistic ICBMs, it was considered an advantage to have nuclear weapons, which could attack every target from every direction. Originally to be launched by the GR-1 missile, it was redesigned for the R-36-O missile. After several suborbital tests, the U.S.S.R. flew a number in fractional orbits - i.e. orbital velocity was reached, but the vehicle was deorbited before completing an orbit. The warheads impacted at the Kapustin Yar missile range. The system was in service at 18 silos at Baikonur from 25 August 1969 to January 1983. Under SALT-2 the system was deactivated. The OGCh missile had a 7.5 year guaranteed fuelled storage life and a five minute reaction time.

http://space.skyrocket.de/doc_lau/gr1.htm

http://space.skyrocket.de/doc_lau_det/r-36-o.htm



Foto:OGCh [GDK]

Surveyor 2 This spacecraft was the second of a series designed to achieve a soft landing on the moon and to return lunar surface photography for determining characteristics of the lunar terrain for Apollo lunar landing missions. It was also equipped to return data on radar reflectivity of the lunar surface, bearing strength of the lunar surface, and spacecraft temperatures for use in the analysis of lunar surface temperatures. The target area proposed was within Sinus Medii. During the midcourse maneuver, one vernier engine failed to ignite, resulting in an unbalanced thrust that caused the spacecraft to tumble. Attempts to salvage the mission failed. The Surveyor program involved building and launching 7 Surveyor spacecraft to the Moon at a total cost of $469 million. Launch Date: 1966-09-20 Launch Vehicle: Atlas-Centaur Launch Site: Cape Canaveral, United States Mass: 292.0 kg

Foto:Surveyor 2

(20 a 23 de septiembre de 1966) - 1.000 kg Copia del Surveyor 1. Cae a la superficie lunar por falta de estabilidad y se estrella a 5ºN-25ºW. No se obtuvo, por tanto, ningún dato científico.

KH-4A 1035

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Thor Agena D rocket. It was a KH-4A (Key Hole-4A) type spacecraft. All cameras operated satisfactorily. This was the first mission flown with pan geometry modification. Launch Date: 1966-09-20 Launch Vehicle: Thor Launch Site: Vandenberg AFB, United States Mass: 1500.0 kg

Ohsumi (#1) Lambda 4S-1


Foto: Ohsumi [ISAS]

Nation: Japan

Type / Application:

Technology

Operator: ISAS

Contractors:

Launch Date: 1966-09-26 Launch Vehicle: Lambda


http://nssdc.gsfc.nasa.gov/image/spacecraft/surveyor_beach.jpg



Launch Site: Uchinoura Space Center, Japan Mass: 26.0 kg

KH-8 2 (OPS 4096)


Launch Date: 1966-09-28 Launch Vehicle: Titan Launch Site: Vandenberg AFB, United States Mass: 3000.0 kg

Octubre 1966

ESSA 3

ESSA 3 was a sun-synchronous operational meteorological satellite designed to take and record daytime earth cloudcover pictures on a global basis for subsequent playback to a ground acquisition facility. The spacecraft was also capable of providing worldwide measurements of reflected solar and long-wave radiation leaving the earth. The spacecraft had essentially the same configuration as that of a TIROS satellite, i.e., an 18-sided right prism, 107 cm across opposite corners and 56 cm high, with a reinforced baseplate carrying most of the subsystems and a cover assembly (hat). Electrical power was provided by approximately 12,000 1- by 2-cm solar cells that were mounted on the cover assembly and by 21 nickel-cadmium batteries. Two redundant Advanced Vidicon Camera System (AVCS) cameras were mounted on opposite sides of the spacecraft, with their optical axes perpendicular to the spin axis. Two sets of flat plate radiometers were also suspended on opposite sides of the satellite beneath the edge of the baseplate. A pair of crossed-dipole command receiver antennas projected out and down from the baseplate. A monopole telemetry and tracking antenna extended out from the top of the cover assembly. The satellite spin

rate was controlled by means of a Magnetic Attitude Spin Coil (MASC), with the spin axis maintained normal to the orbital plane (cartwheel orbit mode) to within plus or minus 1 deg. The MASC was a current-carrying coil mounted in the cover assembly. The magnetic field induced by the current interacted with the earth's magnetic field to provide the torque necessary to maintain a desired spin rate of 9.225 rpm. ESSA 3 performed normally until January 20, 1967, when the radiometer experiment failed. The first AVCS camera failed on September 29, 1967, the remaining camera failed on October 9, 1968, and the satellite was deactivated on December 2, 1968. Launch Date: 1966-10-02 Launch Vehicle: Delta Launch Site: Vandenberg AFB, United States Mass: 145.0 kg

Foto: ESSA 3 [NOAA]

RTS-1 3 / SECOR 8 (EGRS 8) MIDAS 12

Nation: USA

Type / Application:

Early Warning

Operator: USAF

Contractors:

Equipment: RTS-1 ir telescope on spin table

Configuration: Agena-D with payload module and solar arrays


This Missile Defense Alarm System (MIDAS) satellite was launched along with



SECOR 8 from Vandenberg AFB aboard an Atlas Agena D rocket. The MIDAS program, also known as Air Force Program 461, carried out 12 launches between 1960 and 1966 using four different types of increasingly sophisticated infrared sensors. The objective was to develop a satellite that could carry an infrared sensor to detect ICBM launches. Launch Date: 1966-10-05 Launch Vehicle: Atlas-Agena D Launch Site: Vandenberg AFB, United States Mass: 2000.0 kg

KH-7 33 (OPS 2055) KH 7-33 Capsule / SGLS 1 (OPS 5345)

This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Atlas Agena D rocket. It was a KH-7 (Key Hole-7) type spacecraft. This US Air Force photo surveillance satellite was launched from Vandenberg AFB aboard a Atlas Agena D rocket. It was a KH-7 (Key Hole-7) type spacecraft. Launch Date: 1966-10-12 Launch Vehicle: Atlas Launch Site: Vandenberg AFB, United States


Cosmos 129 was a first generation, low resolution Soviet photo surveillance satellite launched from the Plesetsk cosmodrome aboard a Vostok rocket. The film capsule was recovered after 8 days. Launch Date: 1966-10-14 Launch Vehicle: Modified SS-6 (Sapwood) with 1st Generation Upper Stage Launch Site: Plesetsk, U.S.S.R Mass: 4730.0 kg


Cosmos 130 was a second generation, low resolution Soviet photo surveillance satellite launched from the Baikonur cosmodrome aboard a Soyuz rocket. Launch Date: 1966-10-20 Launch Vehicle: Modified SS-6 (Sapwood) with 2nd Generation (Longer) Upper Stage Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 4730.0 kg

Molniya-1 4

Molniya 1/ 4 was a first-generation Russian communications satellite (COMSAT) orbited to test and perfect a system of radio communications and television broadcasting using earth satellites as active transponders and to experiment with the system in practical use. The basic function of the satellite was to relay television programs and long-distance two-way multichannel telephone, phototelephone, and telegraph links from Moscow to the various standard ground receiving stations in the 'Orbita' system. The satellite was in the form of a hermetically sealed cylinder with conical ends -- one end contained the orbital correcting engine and a system of microjets, and the other end contained externally mounted solar and earth sensors. Inside the cylinder were (1) a high-sensitivity receiver and three 800-MHz 40-w transmitters (one operational and two in reserve), (2) telemetering devices that monitored equipment operation, (3) chemical batteries that were constantly recharged by solar cells, and (4) an electronic computer that controlled all equipment on board. Mounted around the central cylinder were six large solar battery panels and two directional, high-gain parabolic aerials, 180 deg apart. One of the aerials was directed continually toward the earth by the highly sensitive earth sensors. The second aerial was held in reserve. Signals were transmitted in a fairly narrow beam ensuring a strong reception at the earth's surface. The satellite received telemetry at 1000 MHz. Television service was provided in a frequency range of 3.4 to 4.1 GHz at 40 w. Molniya 1/ 4, whose cylindrical body was 3.4 m long and 1.6 m



in diameter, was much heavier than corresponding U.S. COMSATs, and it had about 10 times the power output of the Early Bird COMSAT. In addition, it did not employ a geosynchronous equatorial orbit as have most U.S. COMSATs because such an orbit would not provide coverage for areas north of 70 deg n latitude. Instead, the satellite was boosted from a low-altitude parking orbit into a highly elliptical orbit with two high apogees daily over the northern hemisphere -- one over Russia and one over North America -- and relatively low perigees over the southern hemisphere. During its apogee, Molniya 1/ 4 remained relatively stationary with respect to the earth below for nearly 8 of every 12 hr. By placing three of more Molniya 1 satellites in this type of orbit, spacing them suitably, and shifting their orbital planes relative to each other by 120 deg, a 24-hr/day communication system could be obtained. In addition, Molniya 1D carried an externally mounted television camera equipped with various filters and interchangeable wide- and narrow-angle lenses to send back detailed pictures of large cloud systems. From its high apogees over the northern hemisphere, the satellite transmitted pictures of the earth's entire disc that were similar to the ATS pictures. These pictures from Molniya 1/ 4 were used in conjunction with cloudcover pictures taken by the lower orbiting satellites of the Cosmos 'Meteor' weather satellite system to obtain a comprehensive and detailed view of global weather systems. The satellite reentered the atmosphere on September 11, 1968, after 692 days in orbit. Launch Date: 1966-10-20 Launch Vehicle: Modified SS-6 (Sapwood) with 2nd Generation Upper Stage + Escape Stage Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 998.0 kg

Luna 12 (E-6LF #2)

Otros nombres: 1966-094A, Lunik 12, 02508 Fecha de lanzamiento: 22 de octubre de 1.966 a las 08:38:00 GMT Masa seca en órbita: 1.620 kg

Tras ser lanzada por un cohete Molniya, entró en órbita lunar el 25 de octubre de 1.966 a una distancia de 133 x 1.200 kilómetros y 10º de inclinación. La sonda debía cumplir con los objetivos marcados para Luna 11 y para ello portaba un sistema de televisión que obtuvo y transmitió imágenes de la superficie lunar desde la órbita. Las fotografías contenían 1.100 líneas escaneadas con una resolución máxima de entre 15 y 20 metros. Las primeras imágenes devueltas se obtuvieron el día 27 de octubre y fueron publicadas por la prensa soviética y mostraban el Mar de las Lluvias y el cráter Aristarco. Tras esta imagen no se volvió a publicar ninguna más por lo que se desconoce el número total de imágenes capturadas.

Imagen adquirida por Luna 12

Tras su misión fotográfica la sonda fue puesta en modo de giro estabilizado para finalizar su misión con los restantes instrumentos. Las transmisiones de radio cesaron el 19 de enero de 1.967 tras 602 órbitas lunares y 302 transmisiones de radio.

Surveyor-SD 4 / Atlas Centaur 9

Atlas Centaur 9 was a launch vehicle development flight. It carried a Surveyor model that was injected into simulated lunar transfer orbit. It demonstrated a two-burn parking orbit operational capability.




Launch Date: 1966-10-26 Launch Vehicle: Atlas-Centaur Launch Site: Cape Canaveral, United States Mass: 952.6 kg

Intelsat-2 1

The Intelsat II series of satellites, first launched in 1966, marked the third generation of communications satellites developed by Hughes. At the time they were the largest satellites ever launched into synchronous orbit for commercial operation. They were built for the International Telecommunications Satellite Organization (INTELSAT) under the direction of the Communications Satellite Corporation (COMSAT), which acts as manager for INTELSAT in the operation and control of the satellites. Earlier Hughes satellites included Syncom, which was built for the National Aeronautics and Space Administration [NASA], and Early Bird, the world's first commercial synchronous orbit satellite, launched by COMSAT in 1965. Since then four Intelsat II satellites have been launched. The first satellite, F-1, was launched October 26, 1966, for emplacement above the Pacific but failed to achieve synchronous orbit when the apogee engine thrust terminated approximately 4 seconds after ignition. Normal burning time would have been 16 seconds. The satellite, despite its nonsynchronous orbit, was used to transmit live television and other communications traffic. Intelsat II F-2 was launched January 11, 1967, into synchronous orbit above the Pacific near the International Date Line. Regular 24 hour commercial service via the satellite began January 27, 1967. The operation linked earth stations in the United States, Hawaii, Australia, and Japan. Intelsat II F-3 was launched March 22, 1967, and positioned in synchronous orbit above the Atlantic. The fourth satellite in the series, Intelsat II F-4, was launched September 27, 1967, for commercial operation over the Pacific. The Intelsat II satellites, in addition to commercial operation, provided communications support services for NASA's manned lunar landing program. The three satellites of the

series, in continuous service throughout their 3 year design lifetime, are now retired. The Intelsat II's, twice as large as Early Bird and with more than twice the power, were equipped with an advanced antenna design developed by Hughes that permitted direct contact with a number of ground stations simultaneously. The design concept of the satellite followed the same basic principles developed by Hughes for Early Bird. These included spin stabilization, a toroidal antenna beam that continually encompassed the earth, and a simple gas jet system for attitude control and stationkeeping. The spacecraft structure consisted basically of a central stiffened tube directly supporting the apogee motor and communications antenna. An aft radial bulkhead and rib assembly supported the majority of the payload electronics. A forward bulkhead supported lateral and radial loads imposed by the apogee engine. Both ends of the structure were closed by thermal shields, the shield at the antenna end serving a dual role as an antenna ground plane. The basic communications system was composed of two redundant linear repeaters with 125 MHz bandwidth and 6 dB noise figure and four 6 watt traveling wave tubes, of which one, two, or three could be turned on in parallel. The satellite's telemetry subsystem was similar to that of Early Bird and comprised two encoders, two VHF transmitters, and eight whip antennas. The encoders modulated both VHF transmitters and the 4 GHz beacon signals. Both VHF transmitters could be commanded on and off. The beacon signals were transmitted continuously and modulated with telemetry signals. Communications capacity of each satellite was 240 two-way telephone circuits or one two-way TV channel. The outer surface of the satellite was covered with 12,756 n/p silicon solar cells. These delivered 85 watts of electrical power under normal operating conditions. A self-contained apogee motor, fired by command from ground control, supplied the velocity boost required to inject the satellite into synchronous orbit from the transfer orbit. Launch vehicle for the satellite was the Delta-E1.

http://space.skyrocket.de/doc_sdat/intelsat-2.htm

http://space.skyrocket.de/doc_lau_det/delta-e1.htm



Foto:Intelsat-2 1

OV3 2

OV3-2 was a small spin stabilized solar cell powered satellite instrumented for direct studies of the ionosphere and trapped radiation. The spacecraft was an octagonal cylinder 74 cm long and 74 cm across the points. It was powered by n-p solar cells, located on the octagon panels, and nickel cadmium batteries. PAM/FM/FM telemetry and turnstile antenna were employed. The spacecraft systems included a command receiver, tape recorder, and sun sensors and magnetometers for aspect measurements. The spacecraft was built by Space General Corp. for AFCRL. Launch Date: 1966-10-28 Launch Vehicle: Scout Launch Site: Vandenberg AFB, United States Mass: 81.0 kg

Foto:OV3 [USAF]

Noviembre 1966

KH-7 34 (OPS 2070) KH 7-34 Capsule OPS 5424


1966-101A

This unannounced payload was a precursor to the following Cosmos flights -- 139, 160, 169, 170, 171, 178, 179, 183, 187, 218, 244, 298, 354, and 365. Many peices of debris at several altitudes remained following this launch. Launch Date: 1966-11-02

Launch Vehicle: Modified SS-9 (SCARP) or SS-13 (SCRAG) with Orbital & Reentry Stages Launch Site: Tyuratam (Baikonur Cosmodrome), U.S.S.R Mass: 4400.0 kg

OGCh #6

Lanzamiento fallido. Nation: U.S.S.R.






Type / Application:

Fractional Orbital Bombardment System (FOBS) test

Operator:

Contractors:

Equipment:

Configuration:

Propulsion: RD-854

Lifetime:

Mass: 1700 kg

Orbit: 139 km x 270 km, 49.6° (typical)

OV4 3 / OV4 1R / OV4 1T / OV1 6 Gemini B *

OV4-3 was an MOL cannister launched by the US Air Force from Cape Canaveral aboard a Titan 3C rocket. The Manned Orbiting Laboratory (MOL) was the US Air Force's planned manned space project after Dynasoar was cancelled, until it in turn was cancelled in 1969. Experiments planned ranged the gamut from military reconnaisance using large optical cameras and side-looking radar, through interception and inspection of satellites, to exploring the usefullness of man in space and test of manned maneuvering units. After cancellation, some of the reconnaisance systems ended up in later KH series satellites, and some of the manned experiments were accomplished on Skylab. OV4-1R was launched along with OV4-3 and OV4-1T by the US Air Force from Cape Canaveral aboard the same Titan 3C rocket. It conducted "Whispering gallery" experiments along with the Gemini 2 reentry module reused to test reentry with hatch cut into heat shield. When recovered, it was discovered that reentry actually melted the hatch shut, indicating the design was valid for MOL (Manned Orbiting Laboratory), which was the USAF's manned space project after Dynasoar was cancelled, until it was concelled in 1969. MOLs planned experiments ranged the gamut from military reconnaisance using large optical cameras and side-looking radar, through interception and inspection of satellites, to exploring the usefullness of man in space and test of the manned maneuvering units. After cancellation, some of the reconnaisance systems ended

up in later KH series satellites, and some of the manned experiments were accomplished on Skylab OV1-6 was an MOL satellite launched by the US Air Force along with OV4-3, OV4-1R and OV4-1T, from Cape Canaveral aboard a Titan 3C rocket. MOL (Manned Orbiting Laboratory) was the USAF's planned space project after Dynasoar was cancelled, until it in turn was cancelled in 1969. Planned experiments ranged the gamut from military reconnaisance using large optical cameras and side-looking radar, through interception and inspection of satellites, to exploring the usefullness of man in space and test of the manned maneuvering units. After cancellation, some of the reconnaisance systems ended up in later KH series satellites, and some of the manned experiments were accomplished on Skylab. OV4-1T was an MOL satellite launched by the US Air Force from Cape Canaveral aboard a Titan 3C rocket. It performed "Whispering gallery" experiments. MOL (Manned Orbiting Laboratory) was the USAF's planned manned space project after Dynasoar was cancelled, until it in turn was cancelled in 1969. Planned experiments ranged the gamut from military resonnaisance using large optical cameras and side-looking radar, through interception and inspection of satellites, to exploring the usefullness of man in space and test of the manned maneuvering units. After cancellation, some of the reconnaisance systems ended up in later KH series satellites, and some of the manned experiments were accomplished on Skylab.

Foto:OV4 3 [GDK]

The prototype Gemini-B, which was launched on a suborbital trajectory, was the refurbished Gemini-2 capsule, making it the first reused spacecraft. It was launched with the MOL-Heatshield Qualification Test on a Titan-3C launch vehicle.




http://space.skyrocket.de/doc_sdat/gemini-b.htm



http://space.skyrocket.de/doc_lau_det/titan-3c.htm



Launch Date: 1966-11-02 Launch Vehicle: Titan III-C Launch Site: Cape Canaveral, United States Mass: 109.0 kg

Lunar Orbiter 2

Otros nombres: 1966-100A, Lunar Orbiter-B, 02534 Fecha de lanzamiento: 6 de noviembre de 1966 a las 23:21:00 GMT Masa seca en órbita: 385.6 kg Potencia: 375 W La sonda Lunar Orbiter 2 fue diseñada con el objetivo de fotografiar amplias y llanas zonas de la superficie lunar para la selección de un lugar de aterrizaje seguro para las futuras sondas Surveyor y las misiones Apollo. Entre los diversos sensores que portaba se encontraba un medidor de la intensidad de la radiación y un lector de datos de impactos de micrometeoritos. Fue lanzada desde el Complejo 13 a bordo de un cohete Atlas-Agena D que la colocó en una órbita de aparcamiento. Tras 14 minutos de sobrevolar la Tierra fue lanzada en una órbita hacia la Luna, realizando una etapa de crucero de 94 horas. El 8 de noviembre se realizó una maniobra de corrección que aumentaría la velocidad de los 3.051 a los 3.133 kilómetros por hora, momento en el cual la sonda estaba a 265.485 kilómetros de la Tierra.

Foto: Montaje de Lunar Orbiter

El 10 de noviembre a las 20:26 GMT y a una distancia de 352.370 kilómetros de la Tierra y 1.260 kilómetros de la Luna, la nave

encendió sus motores para colocarse en órbita lunar a 5.028 kilómetros por hora. El 15 de noviembre se detectó un impacto de micrometeorito en uno de los sensores. La orbita inicial en la Luna era de 196 x 1.850 Km. con una inclinación de 11,8 º. El periastro fue bajado hasta los 49,7 Km. cinco días después tras 33 orbitas. Un fallo del amplificador el ultimo día de lectura de datos, el 7 de diciembre, resultó en la perdida de seis fotografías. El 8 de diciembre la inclinación fue alterada hasta los 17,5º para proporcionar nuevos datos sobre la gravedad lunar. En total, la nave adquirió fotografías entre el 18 y el 25 de noviembre de 1966, llegando a un total de 609 imágenes de alta resolución y 208 de baja resolución, la mayoría de excelente calidad y una resolución de 1 metro o mejor. Entre estas imágenes se incluía una espectacular vista oblicua del cráter Copernicus que fue ampliamente difundida por los medios de comunicación como una de las mejores imágenes del siglo.

Foto:El cráter Copérnico desde Lunar Orbiter 2.

El resto de instrumentos proporcionó datos de gran calidad. Al final de la misión se recogieron tres impactos de micrometeoritos. La nave fue usada para realizar prácticas de seguimiento hasta que fue estrellada en la superficie lunar a 3º N y 119,1º E el 11 de octubre de 1967.

KH-4A 37 (OPS 1866)

KH-4A 1037 was a photo surveillance satellite launched by the US Air Force from Vandenberg AFB aboard a Thor Agena D rocket. This Key Hole (KH) mission was the second pan geometry mission. A higher




than normal base plus fog were encountered on both main camera records Launch Date: 1966-11-08 Launch Vehicle: Thor-Agena Launch Site: Vandenberg AFB, United States Mass: 1500.0 kg

GATV 12 (TDA 7A)


Nation: USA

Type / Application:

Docking Target

Operator: NASA

Contractors: ?

Equipment: ?

Configuration: Agena-D with docking equipment


Lifetime:

Mass: 3260 kg

Orbit:

Gemini 12 / Gemini 12 Target

Insignia de la misión

Estadísticas de la mission Nombre de la misión: Gemini 12 Número de tripulantes: 2 Lanzamiento: 11 de noviembre, 1966 20:46:33.419 UTC Cabo Cañaveral LC 19 Reentrada: 15 de noviembre, 1966 19:21:04 UTC Duración: 3 días 22 horas 34 minutos 31 segundos Distancia Recorrida: ~2.574.950 km Órbitas: 59

Launch, orbit and landing data

Crew No.Surname Given name Job 1 Lovell James Arthur, Jr. "Shaky" CDR 2 Aldrin Edwin Eugene "Buzz" PLT Flight Launch from Cape Canaveral; landing 1130 km southeast from Cape Canaveral in the Atlantic Ocean. It was the final Gemini-mission. The major objectives of this mission were nearly the same as for Gemini 11, but they were more successful. In preparation for this mission, new, improved restraints were added to the outside of the capsule, and a new technique-underwater training-was introduced, which would become a staple of all future space-walk simulation. The docking with the unmanned Agena target vehicle GATV-12 was successful, even there were problems with the rendezvous radar. For the second time, a Gemini crew was able to practice docking and undocking. The climb to a higher orbit, however, was cancelled because of a problem with the Agena booster. There was also a malfunction with the fuels cells in the Gemini-capsule. Aldrin performed three EVA's during one flight, which was a new record. The first (stand-up EVA) was on 12.11.1966 (2h 29m) in which he photographed starfields, installed a movie camera, fixed the new handrails and retrieved a micrometeorite collection


http://es.wikipedia.org/wiki/11_de_noviembre




http://es.wikipedia.org/wiki/15_de_noviembre


http://www.spacefacts.de/bios/astronauts/english/lovell_james.htm


http://www.spacefacts.de/mission/english/gemini-11.htm




package. He did his work very calm and became not exhausted. The second spacewalk, an umbilical EVA, was performed on 13.11.1966 (2h 06m), in which he attached a 100-foot tether from the GATV to the spacecraft docking bar and evaluated various restraint systems. The final EVA, again a stand-up EVA, was performed on 14.11.1966 (0h 55m), in which he snapped several ultraviolet photographs of constellations. It was again an automatic controlled reentry, only 5,5 km far from the recovery ship, the carrier USS Wasp. Photos / Drawings


Cosmos 131 was a second generation, high resolution Soviet photo surveillance satellite launched from the Plesetsk cosmodrome aboard a Soyuz rocket.

Launch Date: 1966-11-12 Launch Vehicle: Modified SS-6 (Sapwood) with 2nd Generation (Longer) Upper Stage Launch Site: Plesetsk, U.S.S.R Mass: 4730.0 kg

Kosmos (132) (Strela-2 #2)

Lanzamiento fallido

Foto:Strela-2M [Novosti Kosmonavtiki]



Kosmos 133 (Soyuz-Test #1)

Cosmos 133 was a Soviet Soyuz test satellite launched from the Baikonur cosmodrome aboard a Vostok rocket. It was the first test flight of the Soyuz 7K-OK earth orbit spacecraft. It was a planned "all up" test with a second Soyuz to be launched the following day and automatically dock with Cosmos 133. However, its attitude control system malfunctioned, resulting in rapid consumption of orientation fuel, leaving it spinning at 2 rpm. After heroic efforts by ground control and 5 attempts at retrofire over two days, the craft was finally coming down for a landing. Due to the inaccuracy of the reentry burn, it was determined that the capsule would land in China. The self



destruct command was given and the satellite exploded November 30, 1966 at 10:21 GMT.


Diciembre 1966


Cosmos 134 was a second generation, high resolution Soviet photo surveillance satellite launched from Baikonur cosmodrome aboard a Soyuz rocket. The satellite also carried scientific experiments.


KH-7 35 (OPS 1890)


Launch Date: 1966-12-05 Launch Vehicle: Atlas-Agena Launch Site: Vandenberg AFB, United States Mass: 2000.0 kg

ATS 1

ATS 1 (Applications Technology Satellite) was designed and launched for the purpose of (1) testing new concepts in spacecraft design, propulsion, and stabilization, (2) collecting high-quality cloudcover pictures and relaying processed meteorological data via an earth-synchronous satellite, (3) providing in situ measurements of the aerospace

environment, and (4) testing improved communication systems. The spin-stabilized spacecraft was cylindrically shaped and measured 135 cm long and 142 cm in diameter. The primary structural members were a honeycombed equipment shelf and thrust tube. Support rods extended radially outward from the thrust tube. Solar panels were affixed to the support rods and formed the outer walls of the spacecraft. Equipment components and payload were mounted in the annular space between the thrust tube and solar panels. In addition to solar panels, the spacecraft was equipped with two rechargeable nickel-cadmium batteries to provide electrical power. Eight 150-cm-long VHF experiment whip antennas were mounted around the aft end of the spacecraft, while eight telemetry and command antennas were placed on the forward end. Spacecraft guidance and orbital corrections were accomplished by 2.3-kg hydrogen peroxide and hydrazine thrusters, which were activated by ground command. The satellite was initially placed at 151.16 deg W longitude over the Pacific Ocean in a geosynchronous orbit. In general, most of the experiments were successful. Data coverage was nominal until about 1970, after which limited real-time data acquisition was carried out by NOAA until the May 1974 launch of SMS 1. Limited ATS 1 data acquisition was begun by NASA at about that time for ATS 1 - ATS 6 correlative studies. The spacecraft has served as a communications satellite for a number of state, federal, and public organizations up to the present. It is planned to continue operations at its final longitude of 164 deg E until September 1983 and then move the spacecraft out of the geostationary orbit. Launch Date: 1966-12-07 Launch Vehicle: Atlas-Agena D Launch Site: Cape Canaveral, United States Mass: 352.0 kg

OV1 9 (ERE) / OV1 10

OV1-9 and OV1 10 was a research satellite launched by the US Air Force from Vandenberg AFB aboard an Atlas Agena D




rocket. It performed radiation bio-hazard experiments. The spacecraft was placed into a polar orbit to study Lyman-alpha, airglow, auroral emissions, solar X rays, cosmic radiation, and magnetic and electric fields. The track of the satellite followed a meridian of nearly constant local time (initially about 0100 h on the night side, with progression toward earlier times at 1 h per month). A full nightime pass between the terminators was completed in 30 min. The spacecraft was earth-oriented by gravity gradient booms. Launch Date: 1966-12-11 Launch Vehicle: Atlas-Agena Launch Site: Vandenberg AFB, United States Mass: 130.0 kg

Kosmos 135 (DS-U2-MP #1)


Kosmos (136) (Soyuz-Test #(2))

Nation: U.S.S.R.

Type / Application:

Manned spcecraft

Operator:

Contractors:

Equipment:

Configuration: 7K-OK

Propulsion: KTDU-35

KH-8 3 (OPS 8968)


Launch Date: 1966-12-14 Launch Vehicle: Titan Launch Site: Vandenberg AFB, United States Mass: 3000.0 kg

Biosat 1 (Bios 1)

Biosatellite 1 carried biological specimens to determine the effects of the space environment on life processes. The reentry vehicle separated but the rocket failed, leaving the capsule in orbit. No useful scientific data were obtained. Launch Date: 1966-12-14 Launch Vehicle: Delta Launch Site: Cape Canaveral, United States Mass: 950.0 kg


Cosmos 136 was a first generation, low resolution Soviet photo surveillance satellite launched from the Plesetsk cosmodrome aboard a Vostok. The film capsule was recovered after 8 days. The satellite also carried a science package

Launch Date: 1966-12-19 Launch Vehicle: Modified SS-6 (Sapwood) with 1st Generation Upper Stage Launch Site: Plesetsk, U.S.S.R Mass: 4730.0 kg

http://space.skyrocket.de/doc_sdat/ds-u2-mp.htm




Ohsumi (#2) Lambda 4S-2

Foto:Ohsumi [ISAS]


Kosmos 137 (DS-U2-D #1)


Luna 13 (E-6M #1)

Segundo aterrizador soviético que logra posarse con éxito en la superficie lunar, retransmitiendo numerosas fotografías. Luna 13. Otros nombres: 1966-116A, Lunik 13, 02626 Fecha de lanzamiento: 21 de diciembre de 1966 a las 10:19:00 GMT Masa seca en órbita: 1700 kg

La sonda Luna 13 fue lanzada a la órbita terrestre usando un cohete Molniya 8K78M (4-Etapas R-7 / SS-6) y fue puesta rumbo a la Luna usando una última etapa orbital. Tras 3 días de viaje llegó a nuestro satélite el 24 de diciembre y realizó un aterrizaje suave en la superficie lunar en la región de Oceanus Procellarum a las 18:01 GMT, en el Océano de las Tormentas entre los cráteres Krafft y Seleucus a 18º52’ N y 62º3’ O, siendo de esta forma la segunda sonda soviética que se posaba con suavidad en la Luna.

Foto:Sonda Luna-13

Tras abrirse los pétalos de la cápsula, las antenas fueron desplegadas y a los cuatro minutos comenzarón las retransmisiones de datos e imágenes a la Tierra. Durante los días 25 y 26 de diciembre el sistema de televisión de la cápsula transmitió panoramas del terreno circundante con imágenes obtenidas con diferentes ángulos de iluminación solar. Cada panorama mantenía ocupadas a las antenas para su transmisión durante unos 100 minutos. En total se recibieron 5 panoramas mostrando un terreno más suave y liso que el observado por Luna 9. Una de las dos cámaras (para conseguir imágenes en estereo) falló lo que no impidió el éxito de la misión. A diferencia de los anteriores aterrizadores de la serie Luna, la sonda de 113 kilogramos estaba equipada con:……………………. - Dos penetrómetros mecánicos para medir la consistencia del suelo. El sistema estaba formado por dos brazos desplegables equipados con una cabeza de titanio que eran hundidos en el suelo con gran potencia gracias a unas pequeñas cargas explosivas

http://space.skyrocket.de/doc_sdat/ds-u2-d.htm



para medir la densidad del suelo, que resultó ser de 0,8 gramos por centímetro cúbico.

El penetrómetro con la cabeza de titanio.

La sonda con los dos brazos desplegados. El sensor de densidad.

Un dinamógrafo que estaba formado por tres acelerómetros en los 3 ejes para medir las fuerzas en el aterrizaje. Permitía deducir la estructura del suelo hasta los 30 centímetros de profundidad. - Cuatro radiómetros para medir la radiación lunar. Estos aparatos median la radiación infrarroja de la superficie indicando una temperatura a medio día de 117±3 °C, mientras que un detector de radiación indicaba que los niveles no serían peligrosos para los humanos.

Luna-13

Todos estos instrumentos permitían conocer las características mecánicas y físicas y la reflectividad de los rayos cósmicos en la superficie lunar. Las transmisiones desde la nave finalizaron el 28 de diciembre a las 06:13 GMT cuando se perdió definitivamente el contacto debido al agotamiento de las baterías.

IMÁGENES LUNA-13



Samos-F3 6 (OPS 1584) Ferret 9

This US Air Force electronics intelligence satellite was launched from Vandenberg AFB aboard a Thor Agena D rocket.The Ferrets catalogued Soviet air defence radars, eavesdropped on voice communications, and taped missile and satellite telemetry. Launch Date: 1966-12-29 Launch Vehicle: Thor Launch Site: Vandenberg AFB, United States Mass: 1500.0 kg




Referencias (1) http://Sondasespaciales.com (2) http://notesp.blogspot.com/ (3) http://space.skyrocket.de/home.htm (4)http://es.wikipedia.org/wiki/Wikipedia:Portada

(5) http://www.nasa.gov/

Bibliogafia The Complete Book of Spaceflight / David Darling / John Wiley & Sons, Inc. http://www.nasa.gov/centers/kennedy/shuttleoperations/archives/2005.html http://www.planet4589.org/space/jsr/jsr.html http://www.spacefacts.de/english/flights.htm http://es.wikipedia.org/wiki/Misiones_del_Programa_STS http://claudelafleur.qc.ca/Spacecrafts-2008.html http://spaceflightnow.com/news/n0812/25glonass

1 cronología de lanzamientos espaciales · masa seca en órbita: 1580 kg la sonda luna 9 fue la...

Documents