Information to Users

A quantitative figure-of-merit approach for optimization of an unmanned Mars Sample Return mission Item Type text; Thesis-Reproduction (electronic) Authors Preiss, Bruce Kenneth, 1964- Publisher The University of Arizona. Rights Copyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author. Download date 11/10/2021 06:15:49 Link to Item http://hdl.handle.net/10150/278010 INFORMATION TO USERS This manuscript has been reproduced from the microfilm master. UMI films the text directly from the original or copy submitted. Thus, some thesis and dissertation copies are in typewriter face, while others may be from any type of computer printer. The quality of this reproduction is dependent upon the quality of the copy submitted. Broken or indistinct print, colored or poor quality illustrations and photographs, print bleedthrough, substandard margins, and improper alignment can adversely affect reproduction. In the unlikely event that the author did not send UMI a complete manuscript and there are missing pages, these will be noted. Also, if unauthorized copyright material had to be removed, a note will indicate the deletion. Oversize materials (e.g., maps, drawings, charts) are reproduced by sectioning the original, beginning at the upper left-hand corner and continuing from left to right in equal sections with small overlaps. Each original is also photographed in one exposure and is included in reduced form at the back of the book. Photographs included in the original manuscript have been reproduced xerographically in this copy. Higher quality 6" x 9" black and white photographic prints are available for any photographs or illustrations appearing in this copy for an additional charge. Contact UMI directly to order. University Microfilms International A Bell & Howell Information Company 300 North Zeeb Road, Ann Arbor, Ml 48106-1346 USA 313/761-4700 800/521-0600 Order Number 1346428 A quantitative figure-of-merit approach for optimization of an unmanned Mars Sample Return mission Preiss, Bruce Kenneth, M.S. The University of Arizona, 1991 U MI 300 N. Zeeb Rd. Ann Arbor, MI 48106 A QUANTITATIVE FIGURE-OF-MERIT APPROACH FOR OPTIMIZATION OF AN UNMANNED MARS SAMPLE RETURN MISSION by Bruce Kenneth Preiss A Thesis Submitted to the Faculty of the DEPARTMENT OF AEROSPACE AND MECHANICAL ENGINEERING In Partial Fulfillment of the Requirements For the Degree of MASTER OF SCIENCE WITH A MAJOR IN AEROSPACE ENGINEERING In the Graduate College THE UNIVERSITY OF ARIZONA 1991 STATEMENT BY AUTHOR This thesis has been submitted in partial fulfillment of requirements for an advanced degree at The University of Arizona and is deposited in the University Library to be made available to borrowers under rules of the library. Brief quotations from this thesis are allowable without special permission, provided that accurate acknowledgment of source is made. Requests for permission for extended quotation from or reproduction of this manuscript in whole or in part may be granted by the head of the major department or the Dean of the Graduate College when in his or her judgment the proposed use of the material is in the interests of scholarship. In all other instances, however, permission must be obtained from the author. SIGNED: ^ APPROVAL BY THESIS DIRECTOR This thesis has been approved on the date shown below: r. U-^-—iQ-CjC- °( I K.N.R. Ramohalli Date Professor of Aerospace Engineering Ill ACKNOWLEDGMENTS I would like to express my deepest gratitude to: Dr. Kumar Ramohalli for his guidance and extreme patience. Without his influence and extensive knowledge, this project could not have succeeded. Tom Pan for his dedicated help in many areas. His tireless research and comprehensive computer graphics work enabled the project to be completed on time. Mario Rascon for his propellant background advice and extensive computer support. Heidi Ruffner, my wife, for her infinite understanding and resolute moral support. Her excellent proofreading skills and merciless editing talent helped keep the writing on track. I have yet to figure out how she found the time to help me and still maintain her own technical research. My parents for their support from the beginning. This research was sponsored by NASA as part of the UA/NASA Space Engineering Research Center. The author gratefully acknowledges the support provided by Dr. Murray Hirschbein and Dr. Gordon Johnston through the grant NAGW-1332. V TABLE OF CONTENTS LIST OF ILLUSTRATIONS VI LIST OF TABLES VIII LIST OF VARIABLES IX ABSTRACT 1 Chapter 1: BACKGROUND 2 Chapter 2: INTRODUCTION 12 Chapter 3: DEVELOPMENT OF SPREADSHEET 23 Chapter 4: SPREADSHEET ORGANIZATION 31 Chapter 5: PRIMARY SPREADSHEET EQUATIONS 38 Chapter 6: PROPELLANT DATABASE 67 Chapter 7: SURFACE SUPPORT COMPONENTS .. 75 Chapter 8: IN-SITU RESOURCE UTILIZATION 82 Chapter 9: MODULAR ENGINE COMPONENTS 92 Chapter 10: APPLICATION TO A MARS SAMPLE RETURN MISSION 99 Chapter 11: SUMMARY OF OPTIMUM MISSION PLAN 104 Chapter 12: PROJECT SUMMARY 123 Appendix A: FIGURE-OF-MERIT SPREADSHEET 128 Appendix B: SPREADSHEET EQUATIONS 214 VI LIST OF ILLUSTRATIONS Figure 1: FoM Concept 13 Figure 2: Historical Flyby Missions 16 Figure 3: Historical Orbiter Missions 16 Figure 4: Historical Lander Missions 17 Figure 5: Historical Sample Return Missions 17 Figure 6: Lander Missions with Linear Fit 19 Figure 7: Lander Missions with Power Fit 19 Figure 8: Sample Return Missions with Linear Fit 21 Figure 9: Sample Return Missions with Power Fit 21 Figure 10: MSR Mission Date Schematic 26 Figure 11: Refrigeration Unit Heat Transfer 41 Figure 12: Pressure Feed System Schematic 50 Figure 13: Pump Feed System Schematic 51 Figure 14: Feed System Design Selection 53 Figure 15: Pressure Feed Rocket Mass Breakdown 54 Figure 16: Pump Feed Rocket Mass Breakdown — 54 Figure 17: Propulsion Unit Weight Comparison 57 Figure 18: Turbopump Feed System Coefficient 59 Figure 19: Nozzle Geometry 61 Figure 20: Oxygen Plant Test Bed 85 Figure 21: Oxygen Plant Flight Hardware 86 VII Figure 22: Plant Mass Breakdown 90 Figure 23: Modular Engine Staging 93 Figure 24: Advanced Modular Engine Staging 98 Figure 25: MSR Mission Trajectory 103 Figure 26: MSR Staging Schematic 105 Figure 27: Initial Staging Masses 107 Figure 28: Payload Constraints 108 Figure 29: Mission Variations 109 Figure 30: Mission Mass Breakdown 110 Figure 31: FoM Correlation 112 Figure 32: Sample Mass Variations 115 Figure 33: Return Payload Variations 116 Figure 34: ISRU Comparison 117 Figure 35: Plant Mass Variations 119 Figure 36: Fuel Ratio Effects 120 Figure 37: Nozzle Area Ratio Effects 121 Figure 38: Technology Benefits 122 Figure 39: Technology Mass Savings 123 VIII LIST OF TABLES Table 1 - Possible Figure-of-Merit Definitions 15 Table 2 - Distance Factors 18 Table 3 - FoM Program Sheet Outline 31 Table 4 - Initial Mass Component Breakdown 39 Table 5 - Structural Coefficient Dependencies 56 Table 6 - Fixed coefficients 56 Table 7 - Variable Coefficients 57 Table 8 - Pump Feed System Coefficients 58 Table 9 - Pressure Feed System Coefficients 59 Table 10 - Database Propellant Combinations 68 Table 11 - Stoichiometric Combustion Reactions 70 Table 12 - System Chamber Pressures 71 Table 13 - Nozzle Expansion Area Ratios 71 Table 14 - Oxidizer to Fuel Mass Ratio Multipliers 72 Table 15 - Propellant Data Record Fields 74 Table 16 - Modular Engine Masses 97 Table 17 - R-factor Comparison 114 Table 18 - Mission Variation Summary 123 IX LIST OF VARIABLES VARIABLE UNITS IDENTIFICATION Ac Aeroshell Coefficient m2 Area of Nozzle Exit Plane Ap m2 Projected Area A; m2 Surface Area A, m2 Area of Nozzle Throat A1 Cubic Equation Coefficient A2 Cubic Equation Coefficient A3 Cubic Equation Coefficient • c m/s Characteristic Velocity COEFtl Total sum of Coefficients D Determinant for Cubic Equation CIT m Tank Diameter EC Engine Coefficient F kg Rocket Stage Design Thrust FA Fraction of Tank Area Exposed to Solar Radiation FAF Fraction of Fuel Tank Exposed to Solar Radiation FAQX Fraction of Oxidizer Exposed to Solar Radiation FSC Feed System Coefficient FTC Fuel Tank Coefficient FTSF Fuel Tank Design Safety Factor Gc Guidance Coefficient 2 Gs W/m Solar Flux in Low Earth Orbit g m/s2 Gravitational Acceleration h W/m2-K Convection Coefficient I>P sec Specific Impulse Asp(vac) sec Vacuum Specific Impulse k W/m-K Thermal Conductivity MA kg Aeroshell Mass Me kg Engine Mass Mf kg Fuel Mass ^FS kg Feed System Mass Mpr kg Fuel Tank Mass MG kg Guidance Mass ML kg Payload Mass Mn kg Nozzle Mass MOX kg Oxidizer Mass M0XT kg Oxidizer Tank Mass MP kg Propellant mass MRATIO Mass Ratio MRF kg Fuel Refrigeration Unit Mass X Mrox kg Oxidizer Refrigeration Unit Mass MRP kg/W Refrigeration Unit Specific Power MRPF kg/W Fuel Refrigeration Unit Specific Power Mrpox kg/W Oxidizer Refrigeration Unit Specific Power Mse kg Structural Mass - Engine Mss kg Structural Mass - Secondary kg Tank Mass M.TP kg Turbopump Mass M,0 kg Initial Mass M1 kg Final Mass kgl/3 MRPRE Refrigeration Unit Mass Intermediate Coefficient NC Nozzle Coefficient Npp Number of Fuel Tanks Noxt Number of Oxidizer Tanks ^SF Nozzle Safety Factor NT Number of Tanks Nu Nusselt Number OXTc Oxidizer Tank Coefficient OXT,SF Oxygen Tank Design Safety Factor O/F Oxidizer to Fuel Mass Ratio Pc Psia Chamber Pressure PpT Psia Fuel Tank Internal Pressure ^OXT Psia Oxidizer Tank Internal

Load more