1. Parachutes Supersonic portion – Hemisflo Ribbon Most practical for velocities up to Mach 3 Subsonic portion – Ringsail Parachutes Historically proven success rate Reefed for a short time to decrease max g- load during deployment and increase parachute stability

2. Parachutes Continued Landing parachute – Volplane Developed for the Pioneer spacecraft, tested with the Gemini capsule (L/D)max = 3.0 Provide softer landing and maneuverability

3. Parachute Code Written by Jeremy Davis for Spring 2001, modified by Jon Edwards Consists of 6 Matlab files subreefeom.m / supereom.m subreefdiam.m / superdiam.m supersubhm.m acceldiff.m

4. Parachute Sample Case Initial Conditions Altitude at Mach 3 = 17.5 km Flight Path Angle = 45 deg Mass = 57520 kg

5. Parachute Sample Case Con’t Supersonic Stage 7 hemisflo ribbon parachutes D = 25 m Total Mass = 278 kg Deployment time = 42 s

6. Parachute Sample Case Con’t Subsonic Reefed Stage 3 reefed ringsail parachutes Reefing factor = 0.3 Inflated area = 0.3 * max inflation area Reefing time = 10 s

7. Parachute Sample Case Con’t Subsonic Un-reefed Stage 3 ringsail parachutes let open to full inflation by cutting the reefing line Total mass = 222 kg D = 38.5 m Deployment time = 39 s Landing Speed = 55.7 m/s

8. Altitude History

9. Velocity History

10. Acceleration History (G-load)

11. Propulsion Systems Shuttle OMS Engine - Retro/Boost F = 6000 lbf Isp = 313 s NTO and MMH propellants (non-cryo) Mass = 134.7 kg

12. Propulsion Systems Cont’d Marquardt R-40A – RCS System F = 500 lbf Isp = 306 s NTO and MMH propellants (non-cryo) Mass = 10 kg 24 R-40A’s – 8 in each plane Also used on Shuttle Orbiter

13. Engine Tank Sizing Code tanksize.m Written by Casey Kirchner for Spring 2001, modified by Jon Edwards Changes No descent or hovering delta v’s No heat shield OMS Isp, expansion ratio and RCS Isp Landing mass Vehicle Dimensions

14. Tank Sizing Sample Case Initial Conditions Mass = 57520 kg Periapsis lowering/raising delta v = 20 m/s Hab length = 16.5 m Hab diameter = 13 m

15. Tank Sizing Sample Case Oxidizer tank (cylindrical w/ hemi ends) Length = 0.90 m Diameter = 1.00 m Fuel tank (cylindrical w/ hemi ends) Length = 0.94 m Diameter = 1.00 m Pressurant Tank (spherical) Diameter = 1.36 m

16. Tank Sizing Sample Case Oxidizer Tank mass = 10.78 kg Propellant mass = 1725.03 kg Fuel Tank mass = 11.00 kg Propellant mass = 1078.14 kg Pressurant Tank mass = 4.70 kg Pressurant mass = 6.07 kg

17. Tank Sizing Sample Case Structural support According to Humble we add 10% of total inert mass for structural support Structural support mass = 4.19 kg Total Mass = 3250.54 kg