Reaching High Altitudes on Mars With an Inflatable Hypersonic Drag Balloon

✍ Scribed by Hannes Stephan Griebel

• Publisher: Vieweg+Teubner
• Year: 2011
• Tongue: English
• Leaves: 267
• Edition: 2010
• Category: Library

✦ Synopsis

В книге «Высотные полеты на Марсе посредством надувных тормозящих сфер (НТС)» описывается практическое применение НТС для проведения аварийных и спасательных работ на околоземной орбите и доставки грузов на высотные высадочные площадки на Марсе. В книге дана теоретическая основа выполнения подобных полетов, а также рассказывается об уже имеющемся опыте, в т.ч. планах полетов, производстве, развертывании, равно как и о проведении наземных и атмосферных испытаний.

✦ Table of Contents

Cover......Page 1
Reaching High Altitudes
on Mars with an Inflatable
Hypersonic Drag Balloon
(Ballute)......Page 4
ISBN 9783834814258......Page 5
Acknowledgements......Page 8
Table of Contents......Page 10
List of Figures......Page 14
List of Tables......Page 24
List of Symbols......Page 26
List of Constants......Page 28
Acronyms and Abbreviations......Page 30
1.1 Scientific Background......Page 32
1.2 Engineering Background......Page 33
2.1 About Planetary Aeroplanes and Balloons......Page 34
2.2.1 Gas Generator Systems......Page 35
2.2.2 Compressed Gas Systems......Page 36
2.2.4 General Motors' Air Cushion Restraint Syatem from 1973 to 1976......Page 37
2.3 About Space Inflatableas......Page 39
2.4 About Hypersonic InflatabIe Drag Devices......Page 40
2.4.1 TM Goodyear Ballute......Page 41
2.4.2 The Gemini Ejection Seat Recovery System......Page 42
2.4.3 IRDT......Page 43
2.5 State of the Art......Page 44
3.1.1 The Ballute Spacecraft......Page 46
3.1.3 Basic Simplification......Page 47
3.2 Basic Equations of Motion......Page 48
3.3 About Atmosphere Models and Their Suitability......Page 49
3.4 The BaUistic Coefficient and Its Impact on Mission Design......Page 53
3.5 Entry Angle and Entry Altitude......Page 57
4.1 General Ballute Shapes and Attachment Options......Page 64
4.2 Final Configuration......Page 65
4.3 Mission Design Options......Page 66
4.3.1 Descending to a Flotation Altitude......Page 67
4.3.2 Descending to the Surface of Mars......Page 72
4.3.3 Aerobreaking before Descending Deeper into the Atmosphere......Page 73
5.2 Mission and Sensitivity Analysis with the Radio Science Simulator......Page 76
5.2.1 Atmospheric Entry Trajectories......Page 77
5.2.2 Mission Design Analysis......Page 79
5.3.1 Computational Fluid Dynmnics Analysis of Critical Trajectory Points......Page 81
5.3.2 FEM Stress and Modal Analyaes......Page 85
5.4.1 Overview and Coordinate System......Page 90
5.4.2 Basic Equations......Page 91
5.4.3 Radiative Beat Exchange......Page 92
5.4.4 Example Results......Page 96
6.1 Material Selection......Page 98
6.2.1.1 Mechanical Tests......Page 100
6.2.1.3 Thermo-Optical Properties......Page 102
6.2.2 PBO......Page 104
6.3 Conclusion......Page 108
7.1 System Design......Page 110
7.2 Theory of Operation (Ballute Theory)......Page 111
7.2.1.1 Basic Simplifications......Page 113
7.2.1.2 The Velocity as a Function of Altitude......Page 116
7.2.1.3 Maximum Deceleration......Page 117
7.2.1.4 Maximum Hypersonie Heating Rate......Page 122
7.2.1.5 Maximum Stagnation Point Pressure......Page 125
7.2.2 Determination of the Required Inflation Pressure Range......Page 127
7.2.3.1 Transition Through Mach 1......Page 132
7.2.3.2 Final Descent of a Super Pressurized Ballute......Page 136
7.2.3.3 Final Descent of a Collapsing Ballute......Page 140
7.2.4 Sizing the Ballute......Page 147
7.2.5 Sizing the Fittings......Page 155
7.3.1 General Layout Considerations......Page 157
7.3.2 Envelope Production Patterns and Segments......Page 158
7.3.2.1 The FootbaIl (Soccer) Pattern......Page 160
7.3.2.2 Geodesic Sphere......Page 161
7.3.2.3 The Beach Ball (Orange Peel) Pattern......Page 162
7.3.2.4 The Necessary Number of Segments......Page 163
7.3.3 Fittings and Reinforcements......Page 166
7.3.4.1 Seam Geometry......Page 167
7.3.4.2 Seams with Adhesive Tapes......Page 169
7.3.4.3 Heat Bonded (Welded) Seams......Page 175
7.3.5 Ballute Instrumentation......Page 178
7.4.1 Envelope Parts......Page 182
7.4.2 Envelope Assembly......Page 184
8.2 System Design......Page 186
8.3.2 Protective Atmosphere......Page 187
8.4.2 Packaging Efficiency and Trapped Gas......Page 189
8.5.1 Parabolic Flight Deployment Test......Page 195
8.5.2 REGINA In Space Deployment Test......Page 197
9.1 System Design......Page 200
9.2.1 General Overview......Page 204
9.2.2 Mathematical Description and Simulation......Page 205
10.1 Principal Mission and Spacecraft Design Guide......Page 210
10.2.1 General Mission and Spacecraft Overview......Page 212
10.2.2 Instrumentation and Methods to Achieve the Mission Goals......Page 217
10.2.3 Instrument Pod......Page 218
10.2.4 Trajectory and Aerothermodynamic Analysis......Page 220
10.2.5 Ballute......Page 222
10.2.6 Deplayment and Inflation Subsystems......Page 225
10.2.6.1 IGSS System Design Overview......Page 227
10.2.6.2 The Inflation Control Command sequeece......Page 230
10.2.7 Filght Report and Conclusion......Page 235
10.3.1 Scientific Mission and Payload Instruments......Page 239
10.3.2 Mars Mission System Elements......Page 240
10.3.2.1 The ARCHIMEDES Ballute Spacecraft......Page 241
10.3.2.2 The Joint Propulsion System (ARCHlMEDES' Service Spacecraft)......Page 243
10.3.3.1 Trajectory......Page 245
10.3.3.2 Telecommunication and Power Budgets......Page 249
10.3.3.3 Thermal Environment and Hypersonic Flow......Page 254
10.3.4 Concluaion......Page 256
10.4.2 Sky Raft: Recovery from Earth Orbit......Page 257
11 Conclusion and Outlook......Page 260
Bibliography......Page 262