F A C T S H E E T

www.atk.com

–  Lightweight: ⅓ total mass* (150 W/kg BOL) – High Strength: >10x max on-orbit acceleration* – High Deployed Stiffness: 3-8x higher 1st mode* – Compact: ¼ stowage volume and footprint* (40 kW/m3)

– Reliable: simple kinematics; deployment powered by a single (redundant) motor

–  Interchangeable with rigid array technology – Scalable: ~Ø1.7 m (0.5 kW) to Ø10 m (20 kW) and beyond – Customizable: may be optimized for $/W, W/kg, deployed

frequency, etc. – Maneuverable: option to withstand >3 g’s deployed

(e.g. for landing, docking, or transfer orbit power) – All photovoltaic technologies accommodated including

with concentrators * compared with rigid panel solar array of same power"

Motor Driven Deployment / Staging Options: –  “Standard” wing staging (e.g. Phoenix, ST8) – With hinged standoff boom (e.g. Orion CEV)

Non-export controlled – Marketing Level

www.atk.com

–  Lightweight: ⅓ total mass* (150 W/kg BOL) – High Strength: >10x max on-orbit acceleration* – High Deployed Stiffness: 3-8x higher 1st mode* – Compact: ¼ stowage volume and footprint* (40 kW/m3)

– Reliable: simple kinematics; deployment powered by a single (redundant) motor

–  Interchangeable with rigid array technology – Scalable: ~Ø1.7 m (0.5 kW) to Ø10 m (20 kW) and beyond – Customizable: may be optimized for $/W, W/kg, deployed

frequency, etc. – Maneuverable: option to withstand >3 g’s deployed

(e.g. for landing, docking, or transfer orbit power) – All photovoltaic technologies accommodated including

with concentrators * compared with rigid panel solar array of same power"

Motor Driven Deployment / Staging Options: –  “Standard” wing staging (e.g. Phoenix, ST8) – With hinged standoff boom (e.g. Orion CEV)

Non-export controlled – Marketing Level

The Shape of Power in SpaceUltra

• Lightweight: 1/3 total mass* (150 W/kg BOL)

• High strength: >10x max on-orbit acceleration*

• High Deployed Stiffness: 3-8x higher 1st mode*

• Compact: 1/4 stowage volume and footprint* (40 kW/m3)

• Reliable: flight proven; deployment powered by a single (redundant) motor

Flexible

• Interchangeable with rigid array technology

• Scalable: ~Ø1.7 m (0.5 kW) to Ø10 m (20 kW) and beyond

• Customizable: may be optimized for $/W, W/kg, deployed frequency, etc.

• Maneuverable: option to withstand >3 g’s deployed (e.g. for landing, docking, or transfer orbit power)

• All photovoltaic technologies accommodated including with concentrators

Motor Driven Deployment / Staging Options:• “Standard” wing staging (e.g. Phoenix, ST8)

• With hinged standoff boom (e.g. Orion CEV)

Actual Photo. Credit: NASA • JPL • University of Arizona • Texas A&M • James Canvin

* compared with rigid panel solar array of same power

UltraFlex™ Solar Array SystemsBreakthrough Performance, Competitive Cost, Space Flight Proven

OrbitalATK.com

©2017 Orbital ATK. All Rights Reserved. FS007_15_OA_7463

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700

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6000

10 15 20 25 30 35 40

Array  Pow

er,  B

OL  (kW,  2  wings)

Array  M

ass  (kg,  2  wings)

Wing  Dia  (m)

2 decades of development and Flight Heritage

www.atk.com

Non-export controlled – Marketing Level 12/4/13

UltraFlex Solar Array Systems MegaFlex Array-level (2 wings) performance

vs. Diameter (30% TJ cells)

Program

Dat

e Hardware Built

Wing Dia. (m)

Cell Technology (efficiency)

Maturity Achieved Comments

Qualification UltraFlex

solar array wing 19

94 -

1995 Qual Wing

(1 active gore)

3.1 BSFR Silicon (13.7%)

Successfully completed full

wing level qualification

tests

Qual-wing system (with one active gore) successfully qualified - survived all thermal, vibration, and vacuum environments. Successful coupon testing: 1650 cycles -150C to 100C.

Mars 01-Lander 19

98 2 Flight Wings

2.1

High Efficiency

Silicon(17%)

Flight hardware built, qualified, and delivered.

Robust design deploys without offloading in 1g. Program cancelled due to NASA budget constraints. Successful coupon testing 200 cycles -140C to 80C.

Mars Phoenix Lander

2004

- 20

07

2 Flight Wings

2.1 TJ(24%)

100% Flight success

Robust design deploys without offloading in 1g environment and provides >103 watts/kg specific power

NASA-New Millenium ST8

2004

-200

9

Full-scale EDU

5.5Mass

Simulators

Completed CDR; TRL 6

achieved. Mission

Cancelled

Scale-up hardware and modeling capability validated by extensive hardware build & test program

NASA CEV - Orion

(now MPCV) 2008

-201

1

Many validation coupons

6 TJ(28%)

PDR 8/2009 (on hiatus)

UF Technology selected for flagship manned NASA mission 2.7g’s on-orbit strength. Coupon qualifications.

Orbital CRS Cygnus

2011

-201

4

10 Flight wings

3.7 ZTJ Luna (29%)

Delivered, flight pending

UF selected for ISS "COTS" resupply cargo mission. ~5 g's deployed strength to withstand Station plume loads.

MegaFlex: Advanced Solar Array

for SEP 2012

-201

4

Full-scale Flight-like

Wing9.6

Large-area TJ & IMM coupons

TRL 5 demonstration

program

Technology Development to enable near-term Solar Electric Propulsion missions of 30-50kW with scalability to 250kW.

Mars Insight

2013

-201

5

2 Flight Wings

2.15

High Aspect ratio ZTJ 29.5+%

Red / BOL optimized

CDR 3/2014(in production)

Scaled-up of Mars Phoenix arrays; 75 m/s Martian wind load capability.

UltraFlex Solar Array Systems

Two Decades of Development and Flight Heritage

MegaFlex350kW Spacecraft in EELVMegaFlex incorporates a folding panel for twice the power on a given launch vehicle.

0

100

200

300

400

500

600

700

0

1000

2000

3000

4000

5000

6000

10 15 20 25 30 35 40

Array  Pow

er,  B

OL  (kW,  2  wings)

Array  M

ass  (kg,  2  wings)

Wing  Dia  (m)

2 decades of development and Flight Heritage

www.atk.com

Non-export controlled – Marketing Level 12/4/13

UltraFlex Solar Array Systems MegaFlex Array-level (2 wings) performance

vs. Diameter (30% TJ cells)

Program

Dat

e Hardware Built

Wing Dia. (m)

Cell Technology (efficiency)

Maturity Achieved Comments

Qualification UltraFlex

solar array wing 19

94 -

1995 Qual Wing

(1 active gore)

3.1 BSFR Silicon (13.7%)

Successfully completed full

wing level qualification

tests

Qual-wing system (with one active gore) successfully qualified - survived all thermal, vibration, and vacuum environments. Successful coupon testing: 1650 cycles -150C to 100C.

Mars 01-Lander 19

98 2 Flight Wings

2.1

High Efficiency

Silicon(17%)

Flight hardware built, qualified, and delivered.

Robust design deploys without offloading in 1g. Program cancelled due to NASA budget constraints. Successful coupon testing 200 cycles -140C to 80C.

Mars Phoenix Lander

2004

- 20

07

2 Flight Wings

2.1 TJ(24%)

100% Flight success

Robust design deploys without offloading in 1g environment and provides >103 watts/kg specific power

NASA-New Millenium ST8

2004

-200

9

Full-scale EDU

5.5Mass

Simulators

Completed CDR; TRL 6

achieved. Mission

Cancelled

Scale-up hardware and modeling capability validated by extensive hardware build & test program

NASA CEV - Orion

(now MPCV) 2008

-201

1

Many validation coupons

6 TJ(28%)

PDR 8/2009 (on hiatus)

UF Technology selected for flagship manned NASA mission 2.7g’s on-orbit strength. Coupon qualifications.

Orbital CRS Cygnus

2011

-201

4

10 Flight wings

3.7 ZTJ Luna (29%)

Delivered, flight pending

UF selected for ISS "COTS" resupply cargo mission. ~5 g's deployed strength to withstand Station plume loads.

MegaFlex: Advanced Solar Array

for SEP 2012

-201

4

Full-scale Flight-like

Wing9.6

Large-area TJ & IMM coupons

TRL 5 demonstration

program

Technology Development to enable near-term Solar Electric Propulsion missions of 30-50kW with scalability to 250kW.

Mars Insight

2013

-201

5

2 Flight Wings

2.15

High Aspect ratio ZTJ 29.5+%

Red / BOL optimized

CDR 3/2014(in production)

Scaled-up of Mars Phoenix arrays; 75 m/s Martian wind load capability.

10 15 20 25 30 35 400100

Arr

ay P

ower

, BO

L (k

W, 2

win

gs)

Arr

ay M

ass

(kg,

2 w

ings

)

MegaFlex Array-level (2 wings) performancevs. Diameter (30% TJ cells)

Wing Diameter (m)

200300

400500600700

01000

20003000

4000500060007000

LEO

GEO

Planetary Lander

Deep Space (Solar Electric Propulsion)

Successfully completed full wing level qualification tests

Flight hardware built, qualified, and delivered.

100% Flight success

Completed CDR; TRL 6 achieved. Mission Cancelled

PDR 8/2009 (on hiatus)

Flown 3 Missions

TRL 5 demonstration program

Delivered2018 Flight

BSFR Silicon (13.7%)

High Efficiency Silicon (17%)

TJ (24%)

Mass Simulators

TJ (28%)

ZTJ Luna (29%)

Large-area TJ & IMM coupons

HIgh Aspect ratio ZTJ 29.5+%Red / BOL optimized

Qual Wing (1 active gore)

2 Flight Wings

2 Flight Wings

Full-scale EDU

Many validation coupons

10 Flight wings

Full-scale Flight-like Wing

2 Flight Wings

3.1

2.1

2.1

5.5

6

3.7

9.6

2.15

‘94-’95

‘98

04’-07’

04’-09’

08’-11’

11’-14’

12’-14’

13’-15’

Qual-wing system (with one active gore) successfully qualified - survived all thermal, vibration, and vacuum environments.Successful coupon testing: 1650 cycles - 150C to 100C.

Robust design deploys without offloading in 1g. Program cancelled due to NASA budget constraints. Successful coupon testing 200 cycles -140C to 80C.

Robust design deploys without offloading in 1g environment and provides >103 watts/kg specific power

Scale-up hardware and modeling capability validated by extensive hardware build & test program

UF Technology selected for flagship manned NASA mission 2.7g’s on-orbit strength. Coupon qualifications.

UF selected for ISS "COTS" resupply cargo mission. ~5 g's deployed strength to withstand Station plume loads.

Technology Development to enable near- term Solar Electric Propulsion missions of 30-50kW with scalability to 250kW.

Scaled-up of Mars Phoenix arrays; 75 m/s Martian wind load capability.MarsInsight

MegaFlex:AdvancedSolar Arrayfor SEP

Orbital ATKCRSCygnus

NASA CEV -Orion(now MPCV)

NASA - NewMilleniumST8

MarsPhoenixLander

Quali�cationUltraFlexSolar ArrayWing

Mars 01 -Lander

CommentsMaturityAchieved

CellTechnology(ef�ciency)

WingDiameter

(m)

HardwareBuilt

DateYear(s)

Program

Qualified for all Space Environments:

More InformationOrbital ATK Space ComponentsDeployables600 Pine AvenueGoleta, California 93117(805) 685-2262Info-SpaceComponents@orbitalatk.com