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Team A Propulsion

Team A Propulsion. 1/16/01. Presentation Outline. Chemical Propulsion: Expansion of gases as a result of chemical interaction/combustion Thermonuclear Propulsion: Expansion of gases as a result of heating by a nuclear generator

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Team A Propulsion

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  1. Team A Propulsion 1/16/01

  2. Presentation Outline • Chemical Propulsion: Expansion of gases as a result of chemical interaction/combustion • Thermonuclear Propulsion: Expansion of gases as a result of heating by a nuclear generator • Attitude Adjustment: Enroute course modifications with low thrust levels

  3. Propulsion Systems • First stage • Launch vehicle - ground to LEO • Chemical (Liquid) • Second stage • Departure V - LEO to Mars • Chemical or Thermonuclear • Attitude • Course adjustments - enroute to Mars • Chemical or Thermonuclear

  4. Thermonuclear Propulsion • Cold gas expanded by heat from nuclear fission generator • Uranium used as nuclear fuel, running with a critical core, controlled by poison rods • Shielding in place to protect systems and astronauts

  5. Nuclear Engine Concept

  6. Thermonuclear Advantages • Higher Isp and potentially higher thrust than chemical engines • Can use propellants of low molecular weight • Performance really only limited by core temperature (surrounding materials) • NERVA engine tested by NASA 1956-1973 was proven with full test program, except for an actual space flight test • Reactor could possibly be used to provide power for the spacecraft enroute to Mars

  7. Thermonuclear Disadvantages • No off-the-shelf model available • Radiation hazard (astronauts exposed to a whopping 2.8 rems for mission duration) • Public is frightened of nuclear reactors flying • What would we do with the reactor when we arrive at Mars?

  8. Chemical Propulsion • Since initial stages of launch system will be jettisoned nuclear propulsion is not an option • There have been chemical launch systems built that are capable of lifting payloads required for this mission • Once the high thrust portion of the launch is complete thermonuclear propulsion system can be used

  9. Chemical Propulsion • Launch vehicle chosen is the Russian built Energia • Chosen for heavy lift capability as well as modular construction • Another major factor is that the industrial base to construct this launch vehicle has been preserved

  10. Energia • Height: 60m • Thrust 35 MN • 4 strap on boosters having 4 liquid fueled (LOX/RP-1) engines • 4 liquid fueled (LOX/LH2) central core engines • Capable of delivering a 32 mTon payload to Mars with a chemical upper stage stored in the cargo module or 88 K kg to LEO

  11. Alternatives • Could build a similar launch system using 4 SRB’s and a modified external tank that would have liquid motors mounted as well as a cargo module • Design a entirely new launch vehicle that would be similar in design to the Saturn V • Costs of development as well as time constraints for mission timeline could prohibit second option

  12. Attitude Control System • For reference attitude control on the space shuttle uses three modules which house a total of 38 primary thrusters and 6 secondary • Having the three modules provide redundancy because one module can be used to complete the mission

  13. Attitude Control System • Reaction control system uses MMH and N2O4 as the propellants • The total system propellant is 3300kg • The space shuttle also has orbital maneuvering thrusters which may not be necessary for this mission

  14. Attitude Control System • Alternatively heat from the thermonuclear propulsion system can be used to power thrusters for attitude control • Reactor could also be kept active to produce power • The higher performance would reduce the fuel needed

  15. Casey Kirchner • Hands-on experience in propulsion test and heat transfer experiments • Experience with FEHT (heat transfer software) • Courses taken • AAE 439 – Rocket Propulsion • AAE 590K – Advanced Energy Conversion • ME 315 – Heat and Mass Transfer • Courses taking • AAE 539 – Advanced Rocket Propulsion

  16. Adam Irvine • Can program well in Matlab and use optimization routines • Can use AutoCAD • Taken: AAE590G, AAE439, AAE590K • Currently taking: AAE590C and AAE539

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