[{"data":1,"prerenderedAt":-1},["ShallowReactive",2],{"doc-detail-228453-en":3,"doc-seo-228453-105":30,"detail-sidebar-cat-0-en-105":97},{"code":4,"msg":5,"data":6},0,"success",{"doc_id":7,"user_id":8,"nickname":9,"user_avatar":10,"doc_module":4,"category_id":11,"category_name":12,"doc_title":13,"doc_description":14,"doc_content":15,"file_id":16,"file_url":17,"file_type":18,"file_size":19,"view_count":20,"is_deleted":4,"is_public":20,"is_downloadable":20,"audit_status":20,"page_count":21,"language":22,"language_code":23,"site_id":24,"html_lang":23,"table_of_contents":25,"faqs":26,"seo_title":27,"seo_description":14,"update_tm":28,"read_time":29},228453,962085564549,"Aditya","https://ap-avatar.wpscdn.com/davatar_085a072bc5b1113ac321206ff7593b45",8,"Research & Report","Final Report - Fabrication Feasibility Study of a 20 Watt Per Pound Solar Cell Array - NASA Mars Orbiter","Final report covering JPL Contract 951132 on the fabrication feasibility of a 20 watt per pound solar cell array intended to power electric propulsion engines for unmanned spacecraft traveling to a Mars orbit. The work establishes criteria and requirements, performs data collection and parametric evaluations, and conducts configuration trades using state-of-the-art components and processes as of January 1966. Baseline configuration and both 10 and 50 kilowatt prototype preliminary designs are developed, with fabrication of small 1-square-foot sample panels and small-scale model arrays.","CR70582  \nNASA  \nBOEING  \nN66-18325  \n(THRD)  \n(ACCESSION NUMBER)8/  \n   \n(PAGES)  \nCe70582  \n03  \nFACILITY FORM 602  \n(NASA CR OR TMX OR AD NUMBER)  \n(CATEGORY)  \n3/144X750  \n阳圈10000000  \n$.           \nGPO PRICE  \nCFSTI PRICE(S)$                  \n507/25  \nHard copy(HC)  \nMicrofiche(MF)  \nff653 July 65  \n●  \n●  \nTHE BOEIIYFcoMPANY  \nREV LTR  \nCODE IDENT.NO.81205  \nNUMBER___   D2-23942-5         \nTITLE:.FINAL REPORT-FABRICATION FEASIBILITY STUDY OF A 20 WATT PER POUND SOLAR CELL ARRAY  \nFOR LIMITATIONS IMPOSED ON THE USE OF THE INFORMATIONCONTAINED IN THIS DOCUMENT AND ON THE DISTRIBUTIONOF THIS DOCUMENT,SEE LIMITATIONS SHEET.  \nMODEL                    \n  951132       \nCONTRACT  \n       iSSUED TO:                  \nISSUE NO.  \nPREPARED BY         厂   2-19-W.RatchesonREVIEWED BY  ar        9nv.1965K.MartinezAPPROVED BY.乡. CCw.G.Willis/91APPROVED BY                          W.I.Ratcheson171  \nThis work was performed for the Jet Propulsion LaboratoryCalifornia Institute of Technology,sponsored by theNational Aeronautics and Space Administration underContract NAS7-100  \nD2-23942-5LIST OF CONTRIBUTORS  \nS.ChampDynamic AnalysisT.DaltonPrototype Test Plan  \nL.HartleyWeightsT.HaynieMechanisms DesignW.KetchumProgram Plan Staff  \nE.MilesElectrical Conductor DesignS.MitsuiStructural Design  \nH.O'HareReliabilityR.OramGround Support Equipment  \nC.ReifelManufacturing Development  \nJ.TallentElectrical Module Design  \nK.WiedekampMaterials and Processes  \nE.ZapelStress Analysis  \n●  \nThe contract was begun on February 22,1965,and completed in December,1965.  \nCriteria and RequirementsPanel Configuration TradesArray Configuration TradesParametric EvaluationsSolar Photovoltaic CellsCover GlassesDielectricBussesFolding Modular Array  \n●  \nABSTRACT  \nThis document is the final report on efforts conducted under JPL Contract951132,\"Fabrication Feasibility Study of a 20 Watt Per Pound Solar Array\".The solar arrays under study are to be used to power electric propulsionengines on unmanned spacecraft enroute to a Mars orbit.  \nThe study includes development of Criteria and Requirements,data collec-tion,parametric evaluations and configuration trades of arrays using com-ponents and materials and processes that are considered I'state-of-the-art!as of January 1966.After establishment of a baseline configuration,botha 10 and a 50 kilowatt prototype preliminary design were developed andsmall,1 square foot,sample panels and small scale model arrays were fab-ricated.  \nKEY WORDS  \nPanel SubstrateRigid PanelsSemi-Rigid PanelFlexible(Rollup)PanelsDeployment MechanismsRelease MechanismsInterconnectorsRollup Arrays  \nCONTENTS  \nPAGE  \n1.0 INTRODUCTION AND SUMMARY  \n1  \n1.1 Introduction  \n1.2 Summary  \n1.3 Problems10  \n1.4    Conclusions12  \n1.5 Study Program Plan132.0 CRITERIA AND REQUIREMENTS15  \n2.1 Definitions15  \n2.2 Mission Assumptions  \n2.3 Spacecraft Envelope Requirements23  \n2.4 Structural &Environmental Design Criteria  \n2.5Material Selection Criteria  \n2.6Electrical Power Criteria  \n2.7Mechanism Restraints  \n2.8Reliability  \n2.9Interfaces41  \n2.10 Manufacturing Restraints42  \n2.11 Ground Handling Requirements43  \n3.0 PANEL TRADE SUMMARIES45  \n3.1 Solar Cell Module Evaluations45  \n3.2 Electrical Bus Evaluations52  \n3.3 Structural Evaluations564.0 ARRAY TRADE STUDIES67  \n4.1 Saturn IB/Centaur Configuration Studies71  \n4.2 Atlas/Centaur Configuration Studies99  \n4.3 Electrical Bus Trades107  \n4.4 Material Evaluations111  \n4.5 Reliability Evaluations113  \n4.6 Manufacturing Feasibility Evaluation1155.0 PRELIMINARY DESIGN SYSTEM DEFINITION119  \n5.1 Baseline Configuration119  \n5.2 Major Subsystems119  \n5.3 Major Array -Spacecraft Interfaces122  \nD2-23942-5CONTENTS(Cont'd)  \n123  \n6.0 PRELIMINARY DESIGN AND ANALYSIS SUMMARY  \n6.1 Saturn IB/Centaur Array123  \n6.2 Atlas/Centaur Array202  \n229  \n# 7.0 PROGRAM PLAN\n\n229  \n# 7.1 Master Phasing Schedule\n\n235  \n# 7.2 Engineering Plan\n\n239  \n# 7.3 Test Plan\n\n249  \n# 7.4 Ground Support Equipment Requirements\n\n269  \n# 7","cbCaiuUXDe4lprsl","https://ap.wps.com/l/cbCaiuUXDe4lprsl","pdf",10986044,1,315,"English","en",105,"# INTRODUCTION AND SUMMARY\n## Introduction\n## Summary\n## Problems\n## Conclusions\n## Study Program Plan\n# CRITERIA AND REQUIREMENTS\n## Definitions\n## Mission Assumptions\n## Spacecraft Envelope Requirements\n## Structural & Environmental Design Criteria\n## Material Selection Criteria\n## Electrical Power Criteria\n## Mechanism Restraints\n## Reliability\n## Interfaces\n## Manufacturing Restraints\n## Ground Handling Requirements\n# PANEL TRADE SUMMARIES\n## Solar Cell Module Evaluations\n## Electrical Bus Evaluations\n## Structural Evaluations\n# ARRAY TRADE STUDIES\n## Saturn IB/Centaur Configuration Studies\n## Atlas/Centaur Configuration Studies\n## Electrical Bus Trades\n## Material Evaluations\n## Reliability Evaluations\n## Manufacturing Feasibility Evaluation\n# PRELIMINARY DESIGN SYSTEM DEFINITION\n## Baseline Configuration\n## Major Subsystems\n## Major Array - Spacecraft Interfaces\n# PRELIMINARY DESIGN AND ANALYSIS SUMMARY\n## Saturn IB/Centaur Array\n## Atlas/Centaur Array\n# PROGRAM PLAN\n## Master Phasing Schedule\n## Engineering Plan\n## Test Plan\n## Ground Support Equipment Requirements\n## Manufacturing Plan\n## Facility Requirements\n## Costs\n# SAMPLE PANELS AND MODELS\n## Sample Panels\n## Array Models","[{\"question\":\"What is the main purpose of this final report?\",\"answer\":\"It presents the final results of a JPL study focused on fabrication feasibility for a 20 watt per pound solar cell array for electric propulsion on unmanned Mars-orbit spacecraft.\"},{\"question\":\"What types of analyses and planning work are included?\",\"answer\":\"The report includes criteria and requirements development, data collection, parametric evaluations, configuration trades, and preliminary design system definition with program plan elements such as test and manufacturing plans.\"},{\"question\":\"Which prototype designs and test artifacts were developed?\",\"answer\":\"After establishing a baseline configuration, preliminary designs for both 10 kW and 50 kW prototypes were produced, alongside fabrication of 1-square-foot sample panels and small-scale model arrays.\"}]","Final Report - 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