Download - PPT ROKET ENG
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Nama Anggota
Albi Nuari H
Aji Prakoso
Sidiq Nuradiansyah
Yudha Bagus A
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Roket merupakan wahana luar angkasa, pelurukendali, atau kendaraan terbang yangmendapatkan dorongan melalui reaksi roket
terhadap keluarnya secara cepat bahan fluida darikeluaran mesin roket.
http://id.wikipedia.org/wiki/Peluru_kendalihttp://id.wikipedia.org/wiki/Peluru_kendalihttp://id.wikipedia.org/wiki/Mesin_rokethttp://id.wikipedia.org/wiki/Mesin_rokethttp://id.wikipedia.org/wiki/Peluru_kendalihttp://id.wikipedia.org/wiki/Peluru_kendali -
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A solid rocket motor is a system that uses solidpropellants to produce thrust
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Solid rocket motors are used for
Launch vehicles
Ballistic Missiles
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Design involves: Analysis of combustion chamber environment
Stagnation temperature
Stagnation pressure
Propellant gases (material compatibility) Selection of insulation material
Material thickness determination for various areas ofthe motor case
For the cylindrical part of the case, the walls are onlyexposed to hot combustion gases at the end of theburn
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The design of the nozzle follows similarsteps as for other thermodynamic rockets Throat area determined by desired stagnation
pressure and thrust level
Expansion ratio determined by ambientpressure or pressure range to allow maximumefficiency
Major difference for solid propellantnozzles is the technique used for cooling
Ablation Fiber reinforced material used in and near the
nozzle throat (carbon, graphite, silica,phenolic)
http://images.google.com/imgres?imgurl=http://www.kerc.msk.ru/ipg/development/rd3.jpg&imgrefurl=http://www.kerc.msk.ru/ipg/development/srm.shtml&h=411&w=252&sz=12&tbnid=WP7hWectVZcIHM:&tbnh=121&tbnw=74&hl=en&start=7&prev=/images%3Fq%3Dsolid%2Bpropellant%2Bnozzle%26svnum%3D10%26hl%3Den%26lr%3D -
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Meteorite Re-entry speed of 10 - 20 km/sec
Extreme heating in the atmosphere
Ablation and internal energy modes cooled themeteorite through its fall Ablation gas cloud
Dissociation
Internal energy deposition
http://www.dmsweb.org/ -
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Large solid motors typically use a three-stage
ignition system Initiator: Pyrotechnic element that converts electrical
impulse into a chemical reaction (primer)
Booster charge
Main charge: A charge (usually a small solid motor) thatignites the propellant grain. Burns for tenths of asecond with a mass flow about 1/10 of the initialpropellant grain mass flow.
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Two main catagories
Double Base: A homogeneous propellant grain,usually nitrocellulose dissolved in nitroglycerin.
Both ingredients are explosive and act as a combinedfuel, oxidizer and binder
Composite: A heterogeneous propellant grain withoxidizer crystals and powdered fuel held together ina matrix of synthetic rubber binder.
Less hazardous to manufacture and handle
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Fuel 5-22% Powdered Aluminum
Oxidizer 65-70% Ammonium Perchlorate (NH4ClO4 or AP)
Binder 8-14% Hydroxyl-Terminated
Polybutadiene (HTPB)
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Aluminum (Al) Molecular Weight: 26.98 kg/kmol
Density: 2700 kg/m3
Most commonly used Magnesium (Mg)
Molecular Weight: 24.32 kg/kmol
Density: 1750 kg/m3
Clean burning (green) Beryllium (Be)
Molecular Weight: 9.01 kg/kmol
Density: 2300 kg/m3
Most energetic, but extremely toxic exhaust products
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Ammonium Perchlorate (AP) Most commonly used
Cl combining with H can form HCl Toxic
Depletion of ozone
Ammonium Nitrate (AN) Next most commonly used
Less expensive than AP Less energetic
No hazardous exhaust products
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Hydroxyl Terminated Polybutadiene (HTPB)
Most commonly used
Consistency of tire rubber
Polybutadiene Acrylonitrile(PBAN)
Nitrocellulose (PNC)
Double base agent
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Used to promote
Curing
Enhanced burn rate (HMX)
Bonding
Reduced radiation through
the grain (darkening)
Satisfactory aging Reduced cracking
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Advantages High thrust
Simple
Storability
High density Isp
Disadvantages Low Isp (compared to liquids)
Complex throttling Difficult to stop and restart
Safety
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