Griebel Reaching High Altitudes on Mars With an Inflatable Hypersonic Drag Balloon

2010
ISBN: 978-3-8348-9911-8
Verlag: Vieweg & Teubner
Format: PDF
Kopierschutz: 1 - PDF Watermark

E-Book, Englisch, 236 Seiten, eBook

Hannes Griebel studies space applications for the hypersonic drag balloon (ballute), specifically emergency low Earth orbit recovery and delivering payloads to high altitude landing sites on Mars. The author discusses the theory behind such a mission along with experience gained during its practical implementation, such as mission design, manufacturing, packing and deployment techniques as well as ground and flight tests.

Dr. Hannes Griebel completed his doctoral thesis under the supervision of Prof. Dr. Bernd Häusler at the Department of Aerospace Engineering at the Universität der Bundeswehr, München. He was ARCHIMEDES Chief Engineer and Programme Manager and is currently working as a Senior Spacecraft Operations Engineer for Mars Express.

Zielgruppe

Research

Autoren/Hrsg.

Griebel, Hannes Stephan

Inhaltsverzeichnis

1;Acknowledgements;7
2;Table of Contents;8
3;List of Figures;11
4;List of Tables;21
5;List of Symbols;22
6;List of Constants;24
7;Acronyms and Abbreviations;25
8;1 Introduction;27
8.1;1.1 Scientific Background;27
8.2;1.2 Engineering Background;28
9;2 Related Technologies and State of the Art;29
9.1;2.1 About Planetary Aeroplanes and Balloons;29
9.2;2.2 About Automatie Inflatables;30
9.2.1;2.2.1 Gas Generator Systems;30
9.2.2;2.2.2 Compressed Gas Systems;31
9.2.3;2.2.3 Cryogenic Gas Storage Systems;32
9.2.4;2.2.4 General Motors' Air Cushion Restraint Syatem from 1973 to 1976;32
9.3;2.3 About Space Inflatableas;34
9.4;2.4 About Hypersonic InflatabIe Drag Devices;35
9.4.1;2.4.1 TM Goodyear Ballute;36
9.4.2;2.4.2 The Gemini Ejection Seat Recovery System;37
9.4.3;2.4.3 IRDT;38
9.5;2.5 State of the Art;39
10;3 Basic Considerations on Probes with Low Ballistic Coefficients;41
10.1;3.1 The Spacecraft Elements;41
10.1.1;3.1.1 The Ballute Spacecraft;41
10.1.2;3.1.2 The Service Spacecraft and Mission Infrastructure;42
10.1.3;3.1.3 Basic Simplification;42
10.2;3.2 Basic Equations of Motion;43
10.3;3.3 About Atmosphere Models and Their Suitability;44
10.4;3.4 The BaUistic Coefficient and Its Impact on Mission Design;48
10.5;3.5 Entry Angle and Entry Altitude;52
11;4 Ballute Spacecraft Configuration Options;58
11.1;4.1 General Ballute Shapes and Attachment Options;58
11.2;4.2 Final Configuration;59
11.3;4.3 Mission Design Options;60
11.3.1;4.3.1 Descending to a Flotation Altitude;61
11.3.2;4.3.2 Descending to the Surface of Mars;66
11.3.3;4.3.3 Aerobreaking before Descending Deeper into the Atmosphere;67
12;5 Flight Dynamics Analysis;69
12.1;5.1 Overview;69
12.2;5.2 Mission and Sensitivity Analysis with the Radio Science Simulator;69
12.2.1;5.2.1 Atmospheric Entry Trajectories;70
12.2.2;5.2.2 Mission Design Analysis;72
12.3;5.3 Aerothermodynamics and Aeroelasticity;74
12.3.1;5.3.1 Computational Fluid Dynmnics Analysis of Critical Trajectory Points;74
12.3.2;5.3.2 FEM Stress and Modal Analyaes;78
12.4;5.4 Thermal Analysis;83
12.4.1;5.4.1 Overview and Coordinate System;83
12.4.2;5.4.2 Basic Equations;84
12.4.3;5.4.3 Radiative Beat Exchange;85
12.4.4;5.4.4 Example Results;89
13;6 Material Analysis;91
13.1;6.1 Material Selection;91
13.2;6.2 Test and Rasults;93
13.2.1;6.2.1 UPILEX®;93
13.2.1.1;6.2.1.1 Mechanical Tests;93
13.2.1.2;6.2.1.2 Outgassing Tests;95
13.2.1.3;6.2.1.3 Thermo-Optical Properties;95
13.2.2;6.2.2 PBO;97
13.3;6.3 Conclusion;101
14;7 Ballute;102
14.1;7.1 System Design;102
14.2;7.2 Theory of Operation (Ballute Theory);103
14.2.1;7.2.1 An Approximate Analytical Method to Determine the Desired Ballistic Coefficient and Ballute Performance;105
14.2.1.1;7.2.1.1 Basic Simplifications;105
14.2.1.2;7.2.1.2 The Velocity as a Function of Altitude;108
14.2.1.3;7.2.1.3 Maximum Deceleration;109
14.2.1.4;7.2.1.4 Maximum Hypersonie Heating Rate;114
14.2.1.5;7.2.1.5 Maximum Stagnation Point Pressure;117
14.2.2;7.2.2 Determination of the Required Inflation Pressure Range;119
14.2.3;7.2.3 Accessible Landing Terrain, Usable Altitude Range and Usable Descent Time;124
14.2.3.1;7.2.3.1 Transition Through Mach 1;124
14.2.3.2;7.2.3.2 Final Descent of a Super Pressurized Ballute;128
14.2.3.3;7.2.3.3 Final Descent of a Collapsing Ballute;132
14.2.4;7.2.4 Sizing the Ballute;139
14.2.5;7.2.5 Sizing the Fittings;147
14.3;7.3 Design Considerations;149
14.3.1;7.3.1 General Layout Considerations;149
14.3.2;7.3.2 Envelope Production Patterns and Segments;150
14.3.2.1;7.3.2.1 The FootbaIl (Soccer) Pattern;152
14.3.2.2;7.3.2.2 Geodesic Sphere;153
14.3.2.3;7.3.2.3 The Beach Ball (Orange Peel) Pattern;154
14.3.2.4;7.3.2.4 The Necessary Number of Segments;155
14.3.3;7.3.3 Fittings and Reinforcements;158
14.3.4;7.3.4 Seams;159
14.3.4.1;7.3.4.1 Seam Geometry;159
14.3.4.2;7.3.4.2 Seams with Adhesive Tapes;161
14.3.4.3;7.3.4.3 Heat Bonded (Welded) Seams;167
14.3.5;7.3.5 Ballute Instrumentation;170
14.4;7.4 Manufacturing Considerations;174
14.4.1;7.4.1 Envelope Parts;174
14.4.2;7.4.2 Envelope Assembly;176
15;8 TransportatIon and Deployment System;178
15.1;8.1 Statement of Purpose;178
15.2;8.2 System Design;178
15.3;8.3 Theory of Operation;179
15.3.1;8.3.1 General Principle;179
15.3.2;8.3.2 Protective Atmosphere;179
15.4;8.4 Ballute Packaging;181
15.4.1;8.4.1 General Principle;181
15.4.2;8.4.2 Packaging Efficiency and Trapped Gas;181
15.5;85 Deployment Tests;187
15.5.1;8.5.1 Parabolic Flight Deployment Test;187
15.5.2;8.5.2 REGINA In Space Deployment Test;189
16;9 Inflation Control and Gas Storage System (lGSS);192
16.1;9.1 System Design;192
16.2;9.2 Theory of Operation;196
16.2.1;9.2.1 General Overview;196
16.2.2;9.2.2 Mathematical Description and Simulation;197
17;10 Mission and Spacecraft Design for Ballute Applications;201
17.1;10.1 Principal Mission and Spacecraft Design Guide;201
17.2;10.2 The MIRIAM Spaceflight Test;203
17.2.1;10.2.1 General Mission and Spacecraft Overview;203
17.2.2;10.2.2 Instrumentation and Methods to Achieve the Mission Goals;208
17.2.3;10.2.3 Instrument Pod;209
17.2.4;10.2.4 Trajectory and Aerothermodynamic Analysis;211
17.2.5;10.2.5 Ballute;213
17.2.6;10.2.6 Deplayment and Inflation Subsystems;216
17.2.6.1;10.2.6.1 IGSS System Design Overview;218
17.2.6.2;10.2.6.2 The Inflation Control Command sequeece;221
17.2.7;10.2.7 Filght Report and Conclusion;226
17.3;10.3 Tbe ARCHIMEDES Mars Balloon Probe;230
17.3.1;10.3.1 Scientific Mission and Payload Instruments;230
17.3.2;10.3.2 Mars Mission System Elements;231
17.3.2.1;10.3.2.1 The ARCHIMEDES Ballute Spacecraft;232
17.3.2.2;10.3.2.2 The Joint Propulsion System (ARCHlMEDES' Service Spacecraft);234
17.3.3;10.3.3 Mission Design;236
17.3.3.1;10.3.3.1 Trajectory;236
17.3.3.2;10.3.3.2 Telecommunication and Power Budgets;240
17.3.3.3;10.3.3.3 Thermal Environment and Hypersonic Flow;245
17.3.4;10.3.4 Concluaion;247
17.4;10.4 Other Applications;248
17.4.1;10.4.1 The ARCHIMDES-V Venus Ballute Probe;248
17.4.2;10.4.2 Sky Raft: Recovery from Earth Orbit;248
18;11 Conclusion and Outlook;251
19;Bibliography;252

Related Technologies and State of the Art.- Basic Considerations on Probes with Low Ballistic Coefficients.- Ballute Spacecraft Configuration options.- Flight Dynamics Analysis.- Material Analysis.- Ballute.- Transportation and Deployment System.- Inflation Control and Gas Storage System (IGSS).- Mission and Spacecraft Design for Ballute Applications.- Conclusion and Outlook.

Über Autor(innen)

Dr. Hannes Griebel completed his doctoral thesis under the supervision of Prof. Dr. Bernd Häusler at the Department of Aerospace Engineering at the Universität der Bundeswehr, München. He was ARCHIMEDES Chief Engineer and Programme Manager and is currently working as a Senior Spacecraft Operations Engineer for Mars Express.