Case Study: ParaShield

Transcription

1 Case Study: ParaShield Origin of ParaShield Concept ParaShield Flight Test Wind Tunnel Testing Future Applications U N I V E R S I T Y O F MARYLAND 2012 David L. Akin - All rights reserved Case Study: ParaShield ENAE Launch and Entry Vehicle Design 1

2 Graduate Design Class: Fall, 1988 Six students in graduate class in Aeronautics and Astronautics at MIT Project summary: Design an alternative manned spacecra 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) U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 2

3 Parametric Analysis of Heating U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 3

4 Parametric Analysis of Stagnation Temp U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 4

5 Parametric Analysis of Dynamic Pressure U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 5

6 Parametric Analysis of Peak Deceleration U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 6

7 Comparison of Entry Trajectories U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 7

8 Comparison of Heat Shield Temperatures U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 8

9 Comparison of Total Heat Loads U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 9

10 Required Heat Shield Diameter U N I V E R S I T Y O F MARYLAND 10 Case Study: ParaShield ENAE Launch and Entry Vehicle Design

11 Payload Volume Protected from Wake U N I V E R S I T Y O F MARYLAND 11 Case Study: ParaShield ENAE Launch and Entry Vehicle Design

12 Synopsis of Initial Feasibility Study Ultra-low ballistic coefficient vehicles provide significant advantages for atmospheric entry Relief from restriction to conical configurations to avoid a 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 m/sec, requiring only impact attenuation Aero decelerator deployed and verified before entry U N I V E R S I T Y O F MARYLAND 12 Case Study: ParaShield ENAE Launch and Entry Vehicle Design

13 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 U N I V E R S I T Y O F MARYLAND 13 Case Study: ParaShield ENAE Launch and Entry Vehicle Design

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53 Early Assembly of Shield Structure U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 53

54 The Skidbladnir Development Team U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 54

55 Shield Structure and Deployment U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 55

56 ParaShield Stowed and Deployed U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 56

57 Launch Vehicle Integration U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 57

58 October 5, T+2 sec U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 58

59 October 5, T+60 sec U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 59

60 October 6, Aftermath U N I V E R S I T Y O F MARYLAND Case Study: ParaShield ENAE Launch and Entry Vehicle Design 60

61 ParaShield in GLM Wind Tunnel U N I V E R S I T Y O F MARYLAND 61 Case Study: ParaShield ENAE Launch and Entry Vehicle Design

62 Schlieren Supersonic Flow Visualization U N I V E R S I T Y O F MARYLAND 62 Case Study: ParaShield ENAE Launch and Entry Vehicle Design

63 CFD Model U N I V E R S I T Y O F MARYLAND 63 Case Study: ParaShield ENAE Launch and Entry Vehicle Design

64 Configurations for Orbital Flight Test U N I V E R S I T Y O F MARYLAND 64 Case Study: ParaShield ENAE Launch and Entry Vehicle Design

65 ParaShield for ISS Crew Rotation Mission U N I V E R S I T Y O F MARYLAND 65 Case Study: ParaShield ENAE Launch and Entry Vehicle Design

66 ParaShield for Human Lunar Return U N I V E R S I T Y O F MARYLAND 66 Case Study: ParaShield ENAE Launch and Entry Vehicle Design

67 ParaShield for Human Mars Return U N I V E R S I T Y O F MARYLAND 67 Case Study: ParaShield ENAE Launch and Entry Vehicle Design

68 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 a wake Separation of entry/descent/landing systems from crew cabin provides additional margin for exploration missions to the moon and beyond U N I V E R S I T Y O F MARYLAND 68 Case Study: ParaShield ENAE Launch and Entry Vehicle Design

69 ParaShield Flight Test 12/4/2011 U N I V E R S I T Y O F MARYLAND 69 Case Study: ParaShield ENAE Launch and Entry Vehicle Design