5 March 1979 NAS8-3247 DPD558 OR MA-04 SSD 79-0010-4 NASA-CR-l61222) SATSLLIT POWER SYSTEMS V79-23488- (323) CONCEPT DEFINITION STUDY, EXHIBIT C. VOLUME' 4: TBANSPORTATION ANALYSIS Final Report (Eocklell International Corp., Unclas yDowne,Calif.)- 268 p HC A12/Fl -A,01 G3/44 20832 sit Satellite Power Systems (SPS) Concept Definition Study FINAL REPORT (EXHIBIT C) VOLUME IV TRANSPORTATION ANALYSIS 0 Rockwell International Satellite Systems Division Space Systems Group 12214 Lakewood Boulevard Downey, CA 90241 SSD 79-0010-4 Satellite Power Systems (SPS) Concept Definition Study FINAL REPORT (EXHIBIT C) VOLUME IV TRANSPORTATION ANALYSIS CONTRACT NAS8-32475 DPD 558 MA-04 March 1979 Approved G. H VLY C.H. GUTTMAN Programn Ma r SPS Study Team Manager,NASA/MSFC Prepared for: National Aeronautics and Space Administration George C. Marshall Space Flight Center Marshall Space Flight Center Alabama 35812 Er Rockwell International Satellite Systems Division Space Systems Group 12214 Lakewood Boulevard Downey CA 90241 Satellite Systems Division Rockwell Space Systems Group International FOREWORD This is Volume IV - Transportation Analyses, of the SPS Concept Definition Study final report as submitted by Rockwell International through the Satellite Systems Division. In addi­ tion to effort conducted in response to the NASA/MSFC Contract NAS8-32475, Exhibit C, dated March 28, 1978, company sponsored effort on a Horizontal Take-Off, Single-Stage-to-Orbit concept is included. The SPS final report will provide the NASA with additional information on the selection of a viable SPS concept and will furnish a basis for subsequent technology advancement and veri­ fication activities. Other volumes of the final report are listed as followst Volume Title I Executive Summary II Systems Engineering III Experimentation/Verification Element Definition V Special Emphasis Studies VI In-Depth Element Investigations VII Systems/Subsystems Requirements Data Book The SPS Program Manager, G. M. Hanley, may be contacted on any of the technical or management aspects of this report. He may he reached at 213/594-3911, Seal Beach, California. iii SSD 79-0010-4 Satellite Systems Division Rockwell Space Systems Group International CONTENTS Section Page 1.0 INTRODUCTION. -- - 1-1 2.0 'TRANSPORTATION SYSTEM ELEMENTS . 2-1 3.0 -TRANSPORTATION SYSTEM REQUIREMENTS 3-1 4.0 'HEAVY LIFT LAUNCH VEHICLE . 4-1 4.1 HLLV REQUIREMENTS/GROUND RULES 4-1 4.2 HLLV CONFIGURATION- . 4-2 4.2.1 HLLV First Stage (Booster) 4-3 4.2.2 HLLV Second Stage (Orbiter) 4-3 4.3 HLLV PERFORMANCE ... 4-6 4.4 TRADE STUDY OPTIONS . 4-20 5.0 -LEO-TO-GEO TRANSPORTATION - EOTV .. 5-1 5.1 ELECTRIC ORBITAL TRANSFER VEHICLE CONCEPT 5-1 5.1.1 EOTV Sizing Assumptions . 5-2 5.1.2 EOTV Sizing Approach . 5-2 5.1.3 EOTV Sizing Logic . 5-3 5.1.4 EOTV Weight/Performance Summary 5-5 5.2 ELECTRIC ORBITAL TRANSFER VEHICLE TRADE STUDIES 5-7 5.2.1 Solar Array Voltage, Grid Temperature, Numbers of Thrusters . 5-7 5.2.2 Power Distribution and Control Weight . 5-7 5.2.3 Gallium Arsenide Versus Silicon Solar Cells 5-9 5.2.4 Attitude Control System . 5-10 5.2.5 Trip-Time Optimization Analysis .. 5-13 6.0 -ON-ORBIT MOBILITY SYSTEMS . 6-1 7.0 -PERSONNEL TRANSFER SYSTEMS . 7-1 7.1 PERSONNEL LAUNCH VEHICLE (PLV) . 7-1 7.1.1 Liquid Rocket Booster (LRB) . 7-2 7.1.2 Liquid Rocket Booster Engine (SSME-35) 7-5 7.1.3 Liquid Rocket Booster Recovery Concept 7-5 7.2 PERSONNEL ORBITAL TRAISFER VEHICLE (POTV) 7-7 7.2.1 Personnel Orbital Transfer Vehicle Configuration . 7-8 7.2.2 Personnel Module (PM) . 7-11 8.0 NCOST AND PROGA1,RATICS__ - -- 8-1 APPENDIX A - HORIZONTAL TAKEOFF - SINGLE STAGE TO ORBIT TECHNICAL SUMMARY . A-I APPENDIX B - HLLV REFERENCE VEHICLE TRAJECTORY AND TRADE STUDY DATA. B-I APPENDIX C - ELECTRIC ORBITAL TRANSFER VEHICLE SIZING .. C-1 SSD 79-0010-4 Satellite Systems Division Rockwell Space Systems Group Y'Y International ILLU STRATIONS Figure Page 1.0-1 Transportation System Options - Vehicle Size 1-1 2.0-1 . HTO/SSTO HLLV Concept 2-1 2.0-2 VTO/HL HLLV Concept . 2-2 2.0-3 STS-HLLV Configuration . 2-2 2.0-4 Growth Shuttle PLV . 2-3 2.0-5 EOTV Configuration . 2-4 2.0-6 POTV Configuration . 2-4 3.0-1 SPS LEO Transportation Operations 3-1 3.0-2 SPS GEO Transportation Operations 3-2 4.2-1 Reference HLLV Launch Configuration . 4-3 4.2-2 HLLV First Stage (Booster) - Landing Configuration 4-4 4.2-3 HLLV Second Stage (Orbiter) - Landing Configuration 4-5 4.3-1 First Stage Thrust vs Time . 4-9 4.3-2 First Stage Specific Impulse vs Time 4-9 4.3-3 First Stage Relative Velocity vs Time 4-10 4.3-4 First Stage Flight Path Angle vs Time 4-10 4.3-5 First Stage Altitude vs Time . 4-10 4.3-6 First Stage Weight and Range vs Time 4-10 4.3-7 Second Stage Thrust vs Time . 4-11 4.3-8 Mach Number vs Time . • . 4-11 4.3-9 Normal and Total Load Factor vs Time 4-11 4.3-10 Q and QV vs Time . im. 4-11 4.3-11 Lift and Drag vs Time . 4-12 4.3-12 a, e and cQ vs Time . 4-12 4.3-13 Relative Velocity and Q vs Altitude 4-12 4.3-14 Body Attitude vs Time . 4-12 4.3-15 Inertial Velocity vs Time 4-13 4.3-16 Flight Path Angle vs Time 4-13 4.3-17 Altitude vs Time 4-13 4.3-18 Total Load Factor vs Time 4-13 4.3-19 Weight vs Time 4-14 4.3-20 Thrust Attitude vs Time . 4-14 4.3-21 Total Thrust vs Time . 4-14 4.3-22 Dynamic Pressure vs Time 4-14 4.3-23 Altitude vs Range 4-15 4.3-24 Total Thrust vs Weight 4-15 4.3-25 Inertial Velocity vs Time 4-16 4.3-26 Flight Path Angle vs Time 4-16 4.3-27 Altitude vs Time . 4-16 4.3-28 Total Load Factor vs Time . 4-16 4.3-29 Weight vs Time . 4-17 4.3-30 Thrust Attitude vs Time . 4-17 4.3-31 Total Thrust vs Time 4-17 4.3-32 Dynamic Pressure vs Time 4-17 vii SSD 79-0010-4 Satellite Systems Division A Rockwell Space Systems Group International Figure Page 4.3-33 Altitude vs Range . 4-18 4.3-34 Total Thrust vs Weight . 4-18 4.3-35 First Stage Flyback Trajectory . 4-19 5.1-1 EOTV Configuration . .. ..- 5-1 5.1-2 Plasma Power Losses from a 15 kW Solar Array with 90% Insulating Surface . 5-4 5.1-3 Selected EOTV Configuration . 5-6 5.2-1 EOTV Power Distribution Simplified Block Diagram 5-8 5.2-2 EOTV Power Distribution and Control Weight Comparisons. 5-9 5.2-3 EOTV Solar Array Comparisons (GaAs versus Si Solar Cells) 5-10 5.2-4 Typical Gravity Gradient Torque Curves 5-12 5.2-5 Alternative Thruster Configurations . 5-13 5.2-6 Partial Solar Pointing . 5-14 5.2-7 Apportioned Resupply and Operations Cost/kg of EOTV Payload 5-17 5.2-8 Electric EOTV Fleet Sizes and Program Buys 5-18 5.2-9 EOTV Capital Investment Streams ... -5-18 . 5.2-10 Time-Value of Money Impact on Cost Comparisons 5-19 5.2-11 Electric EOTV Cost Comparisons . 5-20 7.1-1 Baseline Space Shuttle Vehicle . 7-1 7.1-2 LOz/L1 2 SSME Integral Twin Ballistic Booster 7-2 7.1-3 STS HLLV Configuration _ . 7-3 7.1-4 Liquid Rocket Booster Main Engine (SSME-35) 7-5 7.1-5 Integral Booster Recovery Concept 7-6 7.1-6 Booster Recovery System . 7-7 7.2-1 POTV Operations Scenario . 7-8 7.2-2 Recommended POTV Configuration 7-8 7.2-3 Advanced Space Engine . 7-9 7.2-4 POTV/PM Configuration Options 7-11 8.0-1 SPS Transportation System DDT&E Program Schedule (Technology Advancement Phase) .. 8-6 8.0-2 SPS Transportation Systems-DDT&E, Technology Advancement Phase 8-7 viii SSD 79-0010-4 Satellite Systems Division Rockwell Space Systems Group international TABLE Table Page 3.0-1 TFU Transportation Requirements . .. 3-3 3.0-2 SPS Program Transportation Requirements, 30-Year Construction Phase . 3-3 3.0-3 Total Transportation Requirements, 60-Year Program 3-4 4.1-1 "HLLV Sizing - Ground Rules/Assumptions . 4-1 4.1-2 Technology Advancement - Weight Reduction 4-2 4.2-1 HLLV Mass Properties x 10- . 4-3 4.2-2 HLLV Weight Statement kgxlO- 3 (lbxlO - 3 ) 4-4 4.2-3 HLLV Propellant Weight Summary x 10- 6 4-5 4.3-1 Engine Performance Parameters .. 4-6 4.3-2 Vehicle Characteristics (Nominal Mission) 4-7 4.3-3 Summary Weight Statement CNominal. Mission) 4-8 5.1-1 EOTV Sizing Assumptions 5-2 5.1-2 EOTV Sizing Approach 5-3 5.1-3 EOTV Sizing Logic 5-3 5.1-4 EOTV Thruster Characteristics 5-5 5.1-5 EOTV Weight/Performance Summary (kg) 5-5 5.2-1 EOTV Configuration Trades . 5-8 5.2-2 GaAIAs and Silicon Powered EOTV Weight Comparison (kg) 5-11 5.2-3 Preliminary Moments of Inertia . 5-11 5.2-4 Thruster Requirements in Shadow 5-12 5.2-5 ACS Trade Study Results .