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Applications Technology Satellite Advanced Missions Study NASA CR 120873 APPLICATIONS TECHNOLOGY SATELLITE ADVANCED MISSIONS STUDY CASE FILE FINAL REPORT COPY VOLUME I OF II SPACE & ELECTRONICS DIVISION prepared for NATIONAL AERONAUTICS AND SPACE ADMINISTRATION NASA Lewis Research Center Contract NAS 3-14360 NASA CR 120873 APPLICATIONS TECHNOLOGY SATELLITE ADVANCED MISSIONS STUDY FINAL REPORT VOLUME I OF II SPACE & ELECTRONICS DIVISION prepared for NATIONAL AERONAUTICS AND SPACE ADMINISTRATION NASA Lewis Research Center Contract NAS 3-14360 APPLICATIONS TECHNOLOGY SATELLITE ADVANCED MISSIONS STUDY CONTRACT NO. NAS 3-14360 NASA LEWIS RESEARCH CENTER 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA CR 120873 4. Title and Subtitle 5. Report Date Applications Technology Satellites Advanced Mission Study 6. Performing Organization Code 7. Author(s) 8. Performing Organization Report No. D. L. Robinson et. al. 10. Work Unit No. 9. Performing Organization Name and Address Fairchild Industries 11. Contract or Grant No. Space and Electronics Division NAS 3-14360 Germantown, Maryland 20767 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington, D. C. 20546 15. Supplementary Notes Project Manager, Robert E. Alexovich, Division, NASA Lewis Research Center, Cleveland, Ohio 16. Abstract Four different spacecraft configurations were developed for geostationary service as a high power communications satellite. The first configuration is a Thor-Delta launch into a low orbit with a spiral ascent to synchronous altitude by ion engine propulsion. The spacecraft is earth oriented with rotating solar arrays. Configuration #2 is a direct injection Atlas/Centaur/Burner n vehicle which when in orbit is sun-oriented with a rotating transponder tower. Configurations #3 and #4 are Titan ETC launches, and are therefore larger and heavier than Configuration #2. They are both sun-oriented, with rotating transponder towers and are directly injected into orbit. Technology discussed in this report includes high power (up to 2 kW) transmitters with collectors radiating heat directly into space, and contoured antenna patterns designed to illuminate partic- ular earth regions. There is also a review of potential users of the services which can be per- formed by this type satellite in such areas as information networking, Public Broadcasting and Educational Television. 17. Key Words (Suggested by Author(s)) 18. Distribution Statement Communication Satellite Unclassified - Unlimited Contoured Antenna Patterns High Power Transmitters 19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price* Unclassified Unclassified ' For sale by the National Technical Information Service, Springfield. Virginia 22151 NASA-C-lnS (Rev. 6-71) TABLE OF CONTENTS Section Subject Page Summary 1 Introduction 1-1 1.1 Mission Objectives 1-1 1.2 Study Objectives 1-1 1.3 Constraints 1-2 1.4 Reactor-Thermoelectric Power Systems 1-7 2 High Power Communication Satellite Missions 2-1 2.1 Missions and Requirements 2-1 2.2 Baseline Information Networking Experiments 2-3 3 Ascent Trajectories and Launch Sequences 3-1 3.1 Titan IHC Trajectory and Launch Sequence 3-1 3.2 Atlas/Centaur/Burner II Trajectory and Launch Sequences 3-10 3. 3 Delta/Ion Engine Launch and Injection Sequences 3-18 4 Spacecraft Description 4-1 4.1 Summary of Spacecraft Characteristics 4-1 4.2 Spacecraft Configuration 4-16 4. 3 Antennas and Feeds 4-35 4.4 Communications Transponder Subsystem 4-52 4.5 Power Supply Subsystem 4-66 4. 6 Attitude Control Subsystem 4-90 4.7 Orbit Control Subsystem 4-118 4.8 Thermal Control Subsystem 4-122 4. 9 Telemetry and Command Subsystem 4-133 TABLE OF CONTENTS (Cont'd.) Section Subject Page 4.10 Structures 4-138 5 Tradeoffs and Analysis 5-1 5.1 Spacecraft - Ground Station 5-1 5. 2 Spacecraft System and Subsystem Interrelation Tradeoffs 5-24 5.3 Antenna and Feeds 5-29 5.4 Communications Subsystem Analysis and Tradeoffs 5-97 5.5 Power Supply Subsystem 5-107 5.6 Attitude Control 5-121 5.7 Orbit Control 5-143 5.8 Thermal Control Analysis 5-145 5. 9 Telemetry and Command System Tradeoffs 5-161 5.10 Structural Analysis 5-162 6 Critical Research and Development 6-1 6.1 Spacecraft Technology Critical R & D 6-1 6. 2 Earth Terminal Technology Critical R & D 6-5 6. 3 Communication System Technology Required R & D 6-5 6.4 Recommended Future Studies 6-9 7 Additional Experiments 7-1/7-2 7.1 Operational Experiments 7-1/7-2 7.2 Technology Experiments 7-25 8 Manufacturing, Testing and Support 8-1 8.1 Manufacturing and Assembly 8-1 8.2 Testing and Support 8-2 11 TABLE OF CONTENTS (Cont'd.) Subject Page Ground Support System 9-1 9.1 Earth Terminals 9-1 9.2 Spacecraft Performance Evaluation 9-9 10 Launch Through Orbit Injection 10-1 10.1 Ground Support Equipment 10-1 10.2 Launch Site Support 10-1 11 Implementation Schedule and Requirements 11-1 11.1 Work Breakdown Structure (WBS) 11-1 11.2 Gross Resources Required 11-1 11. 3 Implementation Schedule 11-1 12 Conclusions and Recommendations 12-1 12.1 Small Terminal Information Networking Systems 12-1 12.2 Demonstration of High Power Satcom Technology 12-2 12. 3 Assessment of Technical Feasibility 12-2 12.4 Selection of Spacecraft Approach 12-3 12.5 Recommended Additional Experiments 12-4 12. 6 Recommended Research and Development 12-4 12.7 Recommended Future Studies 12-5 iii LIST OF ILLUSTRATIONS Figure Title Page 1.3.2-1 ATS-Advanced Mission Spacecraft m (Direct Ascent-Titan me Launch) 1-3 1.3.2-2 ATS-Advanced Mission Spacecraft n (Direct Ascent-SLVSD/Centaur D-lA/Burner n Launched) 1-4 1.3.2-3 ATS-Advanced Mission Spacecraft I (Spiral Ascent-Delta 2910/30 Cm Ion Engine Launched) 1-5 2.2-1 ATS-AMS HI Baseline PBS Information Networking Experiment 2-4 2.2-2 ' ATS-AMS m Baseline Special Interest Areas Information Networking Experiment 2-6 2.2-3 ATS-AMS Baseline Rainfall Attenuation Information Networking Experiment . 2-7 2.2-4 ATS-AMS HI Baseline of Regional Interactive TV Information Networking Experiment 2-9 3.1-1 Titan me (T HIC-26), Pay load Weight vs. Characteristic Velocity, ETR 3-3 3.1-2 Titan IHC Payload Fairing 3-4 3.1-3 Titan HIC Profile . 3-5 3.1-4 Titan EEC Ascent Trajectory Ground Trace 3-6 3.1-5 Positioning of S/C Over USA Obtained by Eastward Drift After Injection into Orbit 3-9 3.2-1 Atlas/Centaur Configuration 3-11 3.2-2 Spacecraft Envelope for Centaur D-1A 3-12 3.2-3 Burner D/Centaur Physical Interface 3-13 3.2-4 Synchronous Transfer Orbit Payload Capability 3-15 3.2-5 Spacecraft Positioning Over Final Station Will be Obtained by a"CombinatioiTof Multiple^ "Equatorial ~ Crossings in either the Parking Orbit or the Transfer Orbit and Eastward Drift 3-17 iv LIST OF ILLUSTRATIONS (Cont'd.) Figure Title Page 3.3-1 Delta Outboard Profile 3-20 3.3-2 Pay load Envelope, Two Stage, 5414 Attach Fitting 3-21 3.3-3 5414 Conical Attach Fitting Detailed Dimensions 3-22 3.3-4 Delta 2910 Capabilities 3-23 3.3-5 Delta 2910 Load vs. Altitude 3-24 3.3-6 During the Final Stage of the Spiral Ascent, the Necessary Adjustment to Obtain Final Orbit Position will be made 3-29 3.3-7 Typical Orbit Radius vs. Time 3-30 3.3-8 Typical Thrust Profile 3-32 4.2-1 ATS-AMS niA Sun Oriented Spacecraft 25 ft. Fairing Titan Booster 4-17/4-18 4.2-2 Equipment Module Structure ATS-AMS HI 4-21/4-22 4.2-3 ATS-AMS HIA Sun Oriented Spacecraft Equipment Layout 4-25/4-26 4.2-4 Layout of ATS-AMS H 4-29/4-30 4.2-5 Earth Oriented Spacecraft Rotating Arrays Delta Booster 2910 4-33/4-34 4.3.1-1 ATS-AMS HLA Multibeam Contoured Coverage for PBS Experiment 4-36 4.3.1-2 ATS-AMS El Alaska Coverage from Two Satellite Locations 4-37 4.3.1-3 ATS-AMS IE Multibeam Contoured Coverage for ITV Experiment 4-39 4.3.1-4 ATS-AMS IE Antennas 4-40 4.3.1-5 ATS-AMS El Conceptual Feed Layout 4-43 4.3.2-1 Small Antenna Dimensions 4-47 4.3.2-2 Large Antenna Dimensions 4-50 4.4.1.3-1 Typical Frequency Plan (ATS-AMS EIA) 4-53 LIST OF ILLUSTRATIONS (Cont'd.) Figure Title Page 4.4.2-1 ATS-AMS m Communications Transponder 4-55/4-56 4.4.3.1-1 Satellite Repeater Block Diagram ATS-AMS 1/H 4-63 4.5-1 ATS-AMS IE Power Subsystem Block Diagram 4-70 4.5-2 Low Voltage Power Subsystem Block Diagram-AMS-n 4-74 4.5-3 High Voltage Solar Array - Power Supply Subsystem Functional Block Diagram ATS-AMS-I 4-77 4.5-4 Solar Array Design ATS-AMS I and II 4-81/4-82 4.5-5 Simplified Schematic High Voltage Power Supplies 4-86 4.5-6 Typical TWT Load Interface Circuit , 4-89 4.6.1-1 Reference Frames for the ATS-AMS m and n Configurations 4-92 4.6.1-2 Reference Frames for the ATS-AMS I Configuration 4-93 4.6.2-1 Back-Up Hydrazine Thruster Matrix 4-97 4.6.2-2 ACS Configuration, ATS-AMS H and AMS HI 4-98 4.6.4-1 ACS Configuration, ATS-AMS I 4-111 4.8.1-1 ATS-AMS HI Thermal Configuration 4-124 4.8.1-2 Power Amplifier Tube Insulation Support Design 4-126 4.8.2-1 Thermal Control Sun Oriented S/C 4-129/4-130 4.8.2-2 Thermal Control System Delta Launched Earth Oriented Spacecraft 4-131/4-132 4.9-1 T&C Subsystem Block Diagram 4-134 5.1-1 Downlink TV Performance with Area Coverage 5-2 5.1-2 Distribution of Rainfall Attenuation, New Jersey 5-4 5.1-3 Earth Station Antenna Size vs.
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