Parachutes
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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