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Power and Propulsion Element (PPE) Spacecraft Reference Trajectory Document NASA/TM—2020-220481 Power and Propulsion Element (PPE) Spacecraft Reference Trajectory Document Melissa L. McGuire, Steven L. McCarty, and Laura M. Burke Glenn Research Center, Cleveland, Ohio March 2020 NASA STI Program . in Profi le Since its founding, NASA has been dedicated • CONTRACTOR REPORT. Scientifi c and to the advancement of aeronautics and space science. technical fi ndings by NASA-sponsored The NASA Scientifi c and Technical Information (STI) contractors and grantees. Program plays a key part in helping NASA maintain this important role. • CONFERENCE PUBLICATION. Collected papers from scientifi c and technical conferences, symposia, seminars, or other The NASA STI Program operates under the auspices meetings sponsored or co-sponsored by NASA. of the Agency Chief Information Offi cer. It collects, organizes, provides for archiving, and disseminates • SPECIAL PUBLICATION. Scientifi c, NASA’s STI. The NASA STI Program provides access technical, or historical information from to the NASA Technical Report Server—Registered NASA programs, projects, and missions, often (NTRS Reg) and NASA Technical Report Server— concerned with subjects having substantial Public (NTRS) thus providing one of the largest public interest. collections of aeronautical and space science STI in the world. Results are published in both non-NASA • TECHNICAL TRANSLATION. English- channels and by NASA in the NASA STI Report language translations of foreign scientifi c and Series, which includes the following report types: technical material pertinent to NASA’s mission. • TECHNICAL PUBLICATION. Reports of For more information about the NASA STI completed research or a major signifi cant phase program, see the following: of research that present the results of NASA programs and include extensive data or theoretical • Access the NASA STI program home page at analysis. Includes compilations of signifi cant http://www.sti.nasa.gov scientifi c and technical data and information deemed to be of continuing reference value. • E-mail your question to [email protected] NASA counter-part of peer-reviewed formal • Fax your question to the NASA STI professional papers, but has less stringent Information Desk at 757-864-6500 limitations on manuscript length and extent of graphic presentations. • Telephone the NASA STI Information Desk at 757-864-9658 • TECHNICAL MEMORANDUM. Scientifi c and technical fi ndings that are preliminary or of • Write to: specialized interest, e.g., “quick-release” reports, NASA STI Program working papers, and bibliographies that contain Mail Stop 148 minimal annotation. Does not contain extensive NASA Langley Research Center analysis. Hampton, VA 23681-2199 NASA/TM—2020-220481 Power and Propulsion Element (PPE) Spacecraft Reference Trajectory Document Melissa L. McGuire, Steven L. McCarty, and Laura M. Burke Glenn Research Center, Cleveland, Ohio National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio 44135 March 2020 Acknowledgments The authors wish to thank the contributions of the NASA Glenn Research Center electric propulsion experts, Dr. Daniel Herman and Timothy Gray, without who’s work these missions would not be possible. This report contains preliminary fi ndings, subject to revision as analysis proceeds. Level of Review: This material has been technically reviewed by technical management. Available from NASA STI Program National Technical Information Service Mail Stop 148 5285 Port Royal Road NASA Langley Research Center Springfi eld, VA 22161 Hampton, VA 23681-2199 703-605-6000 This report is available in electronic form at http://www.sti.nasa.gov/ and http://ntrs.nasa.gov/ PREFACE National Aeronautics and Space Administration’s (NASA’s) proposed Gateway concept would provide a crew-tended outpost in orbit near the Moon, which could be used as a staging point for exploration of the Moon and, eventually, Mars. The first piece of the Gateway to be deployed is the Power and Propulsion Element (PPE). This document captures example reference trajectories for the PPE including a reference delivery orbit and orbit maintenance, an example cislunar orbit transfer and end-of-mission (EOM) disposal trajectory. The flexibility of electric propulsion offers, by its low thrust nature, multiple different trajectory options to transfer from one orbit to another. The trajectories captured in this document are representative examples of a low thrust transfer from the NRHO and to multiple cislunar orbits. This document provides a consistent set of data from mission design to be used in the design of the vehicle capable of flying the trajectory described. NASA/TM—2020-220481 iii CONTENTS PREFACE .................................................................................................................................... iii 1.0 INTRODUCTION ..................................................................................................................1 1.1 Purpose ...................................................................................................................1 1.2 Scope ......................................................................................................................1 1.3 Mission Overview ..................................................................................................1 2.0 MISSION DESIGN GROUND RULES AND ASSUMPTIONS ..........................................2 2.1 Ion Propulsion System Assumptions ......................................................................2 2.2 Reaction Control System Assumptions ..................................................................3 2.3 Power System Assumptions ...................................................................................4 2.4 Duty Cycle Assumptions ........................................................................................4 2.5 Spacecraft Mass Assumptions ................................................................................4 2.6 Thrust Direction Assumptions ...............................................................................5 3.0 REFERENCE NEAR RECTILINEAR HALO ORBIT .........................................................5 3.1 NRHO Description .................................................................................................5 4.0 NRHO ORBIT MAINTENANCE .........................................................................................6 4.1 Orbit Maintenance Strategy ....................................................................................6 4.2 Uncrewed Operations .............................................................................................8 4.3 Crewed Operations .................................................................................................9 4.4 Orbit Maintenance Propulsion Allocation ..............................................................9 5.0 REPRESENTATIVE CISLUNAR ORBIT TRANSFER: NRHO TO DRO .......................12 5.1 NRHO to DRO Transfer Summary ......................................................................12 5.2 Reference Trajectory Events ................................................................................13 5.3 Eclipse Avoidance ................................................................................................14 5.4 Reference Trajectory Plots ...................................................................................14 6.0 REPRESENTATIVE NRHO TO DRO DISPOSAL TRAJECTORY .................................18 6.1 Trajectory Events ..................................................................................................18 6.2 Trajectory Plots ....................................................................................................19 APPENDIX A. ACRONYMS AND ABBREVIATIONS ...........................................................23 APPENDIX B. DEFINITIONS....................................................................................................25 APPENDIX C. ADDITIONAL FILES ........................................................................................27 C.1 Scope ....................................................................................................................27 C.2 Reference Trajectory Excel File(s) .......................................................................27 C.3 SPK File(s) ...........................................................................................................27 APPENDIX D. DOCUMENT HISTORY LOG ..........................................................................29 APPENDIX E. SIGNATURE PAGE ...........................................................................................31 REFERENCES .............................................................................................................................32 NASA/TM—2020-220481 v FIGURES Figure 1-1—NASA Gateway Notional Illustration ........................................................................2 Figure 3-1—15-Year 9:2 NRHO in the Earth-Moon Rotating Frame ...........................................6 Figure 4-1—Orbit Maintenance Maneuver and Target Locations in the Earth-Moon Rotating Frame .......................................................................................................... 8 Figure 4-2—Orbit Maintenance Xe propellant usage over Gateway 15-year lifetime .................10 Figure 4-3—Orbit Maintenance hydrazine propellant usage over Gateway 15-year lifetime ......11 Figure 5-1—Initial 9:2 NRHO and Target 70,000 km DRO in the Earth-Moon Rotating Frame ........................................................................................................12
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