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Propulsion Booster Concepts and Sizing. Steven Golby. Presentation Outline. Subsystem Overview Requirements Descent Phase Current Propulsion Concepts Solid Rocket Bipropellant Liquid Rocket Comparison Future Work. Sub-System Overview. Cancel orbital velocity
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Propulsion Booster Concepts and Sizing Steven Golby
Presentation Outline • Subsystem Overview • Requirements • Descent Phase • Current Propulsion Concepts • Solid Rocket • Bipropellant Liquid Rocket • Comparison • Future Work Steven Golby
Sub-System Overview • Cancel orbital velocity • Obtain desired impact velocity • Detach from penetrator Steven Golby
Requirements • Propulsion Sub-system shall: • Slow penetrator orbital velocity to ~ 0 m/s • Insure penetrator impact velocity of ~ 300 m/s • Detach from penetrator after satisfying velocity requirements • Not interfere with penetrator after separation Steven Golby
Specific Impulse, Isp • Describes the efficiency of a rocket • Represents change in momentum per unit of propellant • Higher Isp→ more propellant efficient m =10 kg ∆V = 1 km/s Steven Golby
Descent Phase Solid Rocket Liquid Rocket Steven Golby
Solid Rocket • 2 stage solid rocket • 1st stage – cancel orbital velocity • 2nd stage – bring penetrator to desired impact velocity Steven Golby
Solid Rocket Steven Golby
Solid Rocket Sizing • Cylindrical canisters • First Stage Diameter = 20 cm Length = 26.5 cm • Second Stage Diameter = 12 cm Length = 14 cm Steven Golby
Bipropellant Liquid Rocket • Hypergolic rocket • Fuel • Monomethylhydrazine (MMH) • Oxidizer • Dinitrogen Tetroxide (N2O4) Steven Golby
Bipropellant Liquid Rocket Steven Golby
Liquid Rocket Sizing • Spherical tanks • Oxidizer Tank Diameter = 23 cm • Fuel Tank Diameter = 21.5 cm Name
Comparison Steven Golby
Conclusions • Feasible from a propulsion perspective • Can tailor solid rocket grain • Existing bipropellant liquid rockets • 2 burns needed • Solid rocket: different stages Steven Golby
Future Plans Steven Golby