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 Second stage Attitude
Launch vehicle - ground to LEO
Chemical (Liquid)
Second stage
Departure V - LEO to Mars
Chemical or Thermonuclear
Attitude
Course adjustments - enroute to Mars

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 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