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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. Parachutes Continued.

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parachutes
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
parachutes continued
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
parachute code
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
parachute sample case
Parachute Sample Case
  • Initial Conditions
    • Altitude at Mach 3 = 17.5 km
    • Flight Path Angle = 45 deg
    • Mass = 57520 kg
parachute sample case con t
Parachute Sample Case Con’t
  • Supersonic Stage
    • 7 hemisflo ribbon parachutes
      • D = 25 m
      • Total Mass = 278 kg
      • Deployment time = 42 s
parachute sample case con t1
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
parachute sample case con t2
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
propulsion systems
Propulsion Systems
  • Shuttle OMS Engine - Retro/Boost
    • F = 6000 lbf
    • Isp = 313 s
    • NTO and MMH propellants (non-cryo)
    • Mass = 134.7 kg
propulsion systems cont d
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
engine tank sizing code
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
tank sizing sample case
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
tank sizing sample case1
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
tank sizing sample case2
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
tank sizing sample case3
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