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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Case Study: ParaShield• Origin of ParaShield concept • ParaShield flight test • Wind tunnel testing • Future applications • Other people’s applications
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© 2018 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Graduate Design Class: Fall, 1988• Six students in graduate class in Aeronautics and
Astronautics at MIT • Project summary: Design an alternative human
spacecraft to supplement/replace the shuttle in the event of another Challenger-type accident
• Had to be capable of launch on Delta II, Atlas, Titan IIIC (existing ELVs)
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Parametric Analysis of Heating
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Parametric Analysis of Stagnation Temp
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Parametric Analysis of Dynamic Pressure
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Parametric Analysis of Peak Deceleration
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Comparison of Entry Trajectories
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Comparison of Heat Shield Temperatures
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Comparison of Total Heat Loads
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Required Heat Shield Diameter
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Payload Volume Protected from Wake
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Synopsis of Initial Feasibility Study• Ultra-low ballistic coefficient vehicles provide
significant advantages for atmospheric entry – Relief from restriction to conical configurations to avoid
aft wake – Significantly lower peak shield temperatures, allowing the
use of existing COTS materials – Little or no entry ionization creating blackouts for
communications and navigation
• Terminal velocity in lower atmosphere is limited to 15-20 m/sec, requiring only impact attenuation – Aero decelerator deployed and verified before entry
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
ParaShield Flight Test Origins• Discussion with officials of American Rocket
Company (AMROC) in April, 1989 – Single Engine Test (SET-1) vehicle being developed for
suborbital test flight out of Vandenberg AFB – Existing payload compartment was empty and available – Targeted launch date: August, 1989 (four months!)
• Total available funding: $80K • Total available personnel: 3 grad students, 2
undergrads (all volunteers), 1 faculty (part-time) • Facilities: undergrad projects lab shop
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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Early Assembly of Shield Structure
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The Skidbladnir Development Team
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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Shield Structure and Deployment
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ParaShield Stowed and Deployed
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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Launch Vehicle Integration
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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October 5, 1989 - T+2 sec
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October 5, 1989 - T+60 sec
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October 6, 1989 - Aftermath
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ParaShield in GLM Wind Tunnel
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Schlieren Supersonic Flow Visualization
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CFD Model
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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Configurations for Orbital Flight Test
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ParaShield for ISS Crew Rotation Mission
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ParaShield for Human Lunar Return
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ParaShield for Human Mars Return
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
U N I V E R S I T Y O FMARYLAND
Conclusions• Ultralow ballistic coefficient entry vehicles can match
performance of conventional capsule-type vehicles • ParaShield approach provides both entry thermal
protection and aerodynamic deceleration, except for impact attenuation
• Structural mass efficiencies and packing factors are improved by larger volume protected from aft wake
• Separation of entry/descent/landing systems from crew cabin provides additional margin for exploration missions to the moon and beyond
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ParaShield Flight Test – 12/4/2011
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ADEPT Concept (NASA Ames)
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ADEPT for Venus Entry
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ADEPT Prototype
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ADEPT in Arcject Testing
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ADEPT Wind Tunnel Test Model
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ADEPT Suborbital Flight Test
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Case Study: ParaShield ENAE 791 - Launch and Entry Vehicle Design
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ADEPT Flight Test Video
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