https://ntrs.nasa.gov/search.jsp?R=19940020540 2020-06-16T16:27:43+00:00Z N94-25022 Unclas G3/15 0204256 _-_ The University of Michigan PRESENTS l '--'_"_.....: : .......;: Air Launched Space Booster -.j'.......'" .... June, 1993 NASA/USRA Preface - Table of Contents Table of Contents Pr"_ce Foreword iV Class Organization Structure Class Photograph \:i Technical Team Specialties Symbol List ix References xiii Chapter 1: Introduction 1.1 History of the Air Launched Space Booster 1.2 Design Process 1.3 Overview of the Gryphon Chapter 2: Spacecraft Integration ii i i 111111 iii 2.1 Introduction 14 2.2 The Bottom Line: Cost 14 2.3 Vehicle Configuration 17 2.4 Saftey Precautions 27 2.5 Conclusion 27 C h,apter 3: _ Analysis 3.1 Introduction 29 3.2 Mission Definition 29 3.3 Ascent Trajectory 30 3.4 Geosynchronous Missions 40 3.5 Spin Rates 45 3.6 Vehicle Aerodynamics 45 3.7 Mission Timeline 53 3.8 Future Work 54 Chapter 4: Propulsion 4.1 Introduction 57 4.2 Engines 57 4.3 Staging 65 4.4 Propellants 73 4.5 Propellant Tanks and Insulation 79 4.6 Future Work 89 4.7 Conclusion 91 Chapter 5: Payloads 5.1 Introduction 93 5.2 Payload Goals 93 5.3 Payload Market 94 5.4 Determination of Payload Bay Dimensions 97 5.5 Payload Limitations 99 5.6 Structural Considerations 100 5.7 Space Station Freedom Options 102 ii The University of Michigan Project Gryphon 5.8 Conclusions 104 Chapter 6:: Mission Control 6.1 Introduction 6.2 Guidance, Navigation, and Control 1_7 6.3 On-Board Computer System 113 6.4 Communications Systems llS 6.5 Conclusion 121 Chapter 7: Structures 7.1 Structures Group Responsibilities 7.2 Main Booster Structure 124 7.3 Design of Payload Shroud and Solid Booster Fairings t36 7.4 Payload Interface 166 7.5 Engine Mounts 176 7.6 lnterstage Rings 184 7.7 Conclusion/Future Work 186 Chapter 8: Power/Thermal/Attitude g.l Introduction 189 8.2 The Attitude Control System 189 8.3 Power System 195 8.4 Thermal Control System 200 8.5 Venting System 201 Chapter: 9: Aircraft Integration 9.1 Introduction 208 9.2 Gryphon Assembly Building 208 9.3 Transporting the Gryphon 213 9.4 Ground Fueling 216 9.5 Aircraft/Booster Interface 229 9.6 Power and Fuel Connections 233 9.7 Placement of Support System on Eclipse 234 9.8 Future Work 236 Chapter 10: Conclusion and Future Work 10.1 Introduction 239 10.2 Summary 239 10.3 Design Status 239 10.4 Future Work 240 Appendicies : 242 Appendix A Spacecraft Integration 249 Appendix B Mission Analysis 259 Appendix C Propulsion Appendix D Payloads 263 Appendix E Mission Control 268 Appendix F Structures 274 Appendix G Power/Thermal/Attitude 305 Appendix H Aircraft Integration 315 iii Preface - Class Organization Foreword Tile project chosen/or the winter semester Aero 483 class was the design of a next generation Air Launched Space Booster. Based on Orbital Sciences Corporation's Pegasus concept, the goal of Aero 483 was to design a 500,000 pound air launched space booster capable of delivering 17,000 pounds of payload to Low Earth Orbit and 8,000 pounds of payload to Geosynchronous Earth Orbit. The resulting launch vehicle was named the Gryphon. The class was led by ProJect Manager Brad King and Assistant Manager Mike Fisher. The class of forty senior aerospace engineering students was broken down into eight interdependent groups. Each group was assigned a subsystem or responsibility which then became their field of ,,pecialization. Spacecraft Integration was responsible for ensuring compatibility between subsystems. This group kept up to date on subsystem redesigns and informed those parties affected by the changes, monitored the vehicle's overall weight and dimensions, and calculated the mass properties of the booster. This group also performed the cost/profitability analysis of the Gryphon and obtained cost data for competing launch systems. The Mission Analysis Group was assigned the task of determining proper orbits, calculating the vehicle's flight trajectory for those orbits, and determining the aerodynamic characteristics of the vehicle. The Propulsion Group chose the engines that were best suited to the mission. This group also set the staging configurations for those engines and designed the tanks and fuel feed system. The commercial satellite market, dimensions and weights of typical satellites, and method of deploying satellites was determined by the Payloads Group. In addition, Payloads identified possible resupply packages for Space Station Freedom and identified those packages that were compatible with the Gryphon. The guidance, navigation, and control subsystems were designed by the Mission Control Group. This group identified required tracking hardware, communications hardware, telemetry systems, and ground sites for the location of the Gryphon's mission control center. The Structures group was responsible for ensuring the structural integrity of the vehicle. Their designs included the payload shroud, payload support structure, exterior hull, and engine support struts. The Gryphon's power requirements were determined by the Power/Thermal/Attitude Control Group. This group then selected suitable batteries and other components to meet these requirements. The group also designed heat shielding and cooling systems to ensure subsystem performance. In addition to these responsibilities this group designed the attitude control methods and RCS components for the vehicle. The Aircraft Integration Group was responsible for all aspects of the booster- aircraft connection. This included the design of the connection structure and the drop mechanism. This group also designed the vehicle assembly facility and identified possible ground bases for the plane. iv Preface - Class Organization Structure I ::. -" 'L31 -_ ,,I _q L ?. a.a -_ _E .,..4 <_ _ Z_. _q L.. i I _2_ > I ! g A _._ e',wj L_ L_ < ! "_. V Preface - Class Photograph z •j....:, _ _" _. _-- _Z _._= : ..,_ ¢ g _ _'_ _. ._ ._ =_'=o 2= • ._ ! ! ( ,._ -: 0 o- University of Michigan Aerospace Project Gryphon The following lists each member's area of technical expertise within the University of Michigan's Aerospace Space System Design Project Gryphon. Project Manager Brad King Daily Agenda Assistant Project Manager Mike Fisher Administration Spacecraft Integration Leader - Elizabeth Hilbert Overall Configuration Tim Ballew Cost and Financing David Cortright Saftey Todd Mueller Cost and Financing Dan Potter Axis System Mission Analysis Leader - Alan Ristow Trajectory Rick Draper Mission Timeline Sean Fifield Orbits Scott Mullison Spin Rates Vince Wiltse Aerodynamics Propulsion Leader - Krista Campbell Solid Fuel Engines Chad Hoggard Cryogenic Fuels Adam Nagaj Tank/Staging Design Bilal Rathur LR91 s/Storable Fuels John Vandenberg Stage Optimization Payloads Leader - Kari Jacobson Space Station Options Chris Bernard Weights and Sizing James Dice Market Kevin Whalen Payload Limitations Craig Litherland Structural Aspects Mission Control Leader - Scott Egbert GPS/Air Support Kah-Wai Aw On-board Computer Brian Smith Inertial Guidance Chris Yee Communications vii Preface - Technical Team Specialties Structures Leader- Joe Ruddy Shroud Design Scott Huggins lnterstage Design Wolfgang Schubert Dynamic Analysis Ron Shin>hock Fairing Analysis Phil Wojcik Payload Interface Power/Thermal/Attitude Leader- Joc Rcgner Release Analysis Josh Baron Power Systems Tom Godfrov Venting System Kcvin Kilburn Thermal Control Romy Shaneff Attitude Control Aircraft Integration Leader- Mike Hindley Aircraft Interface Jon Albert Auxiliary Connections Adam Koziel Attachment Design Chris Vegter Production Site Wind Tunnel Model Leader - Chad Hoggard Flow Visualization Tom Godfroy Model Construction Chris Yee Technical Presentation Mike Hindley Data Recording CAD Leader- Mike Fisher System Coordination Kevin Whalen Integration Adam Koziel Attachment Structure Joe Ruddy Shroud & Fairings Adam Nagaj Propulsion System Display Model Leader - Mike Fisher Component Integration Lee Ann Bird Detailing Elizabeth Hilbert Technical Support Final Report Publication Leader- Mike Fisher Editor in Chief Krista Campbell Technical Integration Elizabeth Hilbert Technical Editing Scott Egbert Processing Support Vince Wiitse Technical Editing viii Universityof MichiganAerospaceProject Gryphon Symbol List $ Dollar A Area C_ ,Angle of attack a Speed of sound AC 41lernating Current Acl Area of clean room AKM Apogee Kick Motor AI Launch azitnuth anz]c ANC Aft Nozzle Co,,cr Orbit semi-ma/or axis A_a ,Area of stage assembly room Asi Area of Stage Integration room Yaw angle BER Bit Rate Error c Speed of light CAD Computer Aided Design Col Cost of clean room CD Coefficient of drag Cdo Zero lift coefficient of drag CG Center of gravity CL Coefficient of lift CM Center of Mass Cm Coefficient of pitching moment Cn Coefficient of yaw moment CP Center of pressure Cp Coefficient of sideforce CPU Central Processing Unit Cr Coefficient of rolling moment Cs Cost of stage room D Drag d Diameter d;u-m Distance of lever arm dB Decible DC Direct Current Dc Drag at cruise launch doom Distance of connectors on lever arm DDAS Digital Data Acquisition System Df Diameter of Fireball dT Fuel tank diameter AV Change in velocity E Modulus of elasticity E Emissivity e Orbit eccentricity ECEF Earrth-centered, earth-fixed Es Structural coefficient °F Degrees Fahrenheit 0 Angle between body and inertial axis f Frequency of signal ix Preface - Symbol List FCC Federal Communications Commision FCS Flight Control System Fhydraulic Hydraulic force Fpin Forces on a pin fs Sample rate FT Thrust ft Foot FTS Flight Tcrmination Sv ,,tern Fx Aerodynamic