[{"data":1,"prerenderedAt":-1},["ShallowReactive",2],{"detail-sidebar-cat-0-en-105":3,"doc-seo-503721-105":59,"doc-detail-503721-en":130},{"code":4,"msg":5,"data":6},0,"success",[7,13,18,23,28,33,38,43,48,51,55],{"id":8,"doc_module":4,"doc_module_name":9,"category_name":10,"show_sort_weight":11,"slug":12},1,"Document","Story & Novel",90,"story-novel",{"id":14,"doc_module":4,"doc_module_name":9,"category_name":15,"show_sort_weight":16,"slug":17},2,"Literature",80,"literature",{"id":19,"doc_module":4,"doc_module_name":9,"category_name":20,"show_sort_weight":21,"slug":22},4,"Exam",70,"exam",{"id":24,"doc_module":4,"doc_module_name":9,"category_name":25,"show_sort_weight":26,"slug":27},5,"Comic",60,"comic",{"id":29,"doc_module":4,"doc_module_name":9,"category_name":30,"show_sort_weight":31,"slug":32},6,"Technology",50,"technology",{"id":34,"doc_module":4,"doc_module_name":9,"category_name":35,"show_sort_weight":36,"slug":37},7,"Healthcare",40,"healthcare",{"id":39,"doc_module":4,"doc_module_name":9,"category_name":40,"show_sort_weight":41,"slug":42},8,"Research & Report",30,"research-report",{"id":44,"doc_module":4,"doc_module_name":9,"category_name":45,"show_sort_weight":46,"slug":47},9,"Religion & Spirituality",20,"religion-spirituality",{"id":46,"doc_module":4,"doc_module_name":9,"category_name":49,"show_sort_weight":46,"slug":50},"World Cup","world-cup",{"id":52,"doc_module":4,"doc_module_name":9,"category_name":53,"show_sort_weight":52,"slug":54},10,"Lifestyle","lifestyle",{"id":56,"doc_module":4,"doc_module_name":9,"category_name":57,"show_sort_weight":24,"slug":58},19,"General","general",{"code":4,"msg":60,"data":61},"ok",{"site_id":62,"language":63,"slug":64,"title":65,"keywords":66,"description":67,"schema_data":68,"social_meta":123,"head_meta":125,"extra_data":127,"updated_unix":129},105,"en","project-casper-critical-design-reviewpsp-sl-2020","Project Casper - Critical Design ReviewPSP-SL 2020","","Project Casper critical design review for PSP-SL 2020 outlines mission goals, derived requirements, and current status across multiple engineering areas. The mission includes designing, building, testing, and flying a student-crafted launch vehicle to a predetermined altitude, carrying a UAS payload for lunar ice sample collection, and ensuring effective high power rocketry teaching. Requirements focus on a robust retention system with verification plans, FEA completion, and full-scale demonstration flight validation.",{"@graph":69,"@context":122},[70,84,105],{"@type":71,"itemListElement":72},"BreadcrumbList",[73,77,79,82],{"item":74,"name":75,"@type":76,"position":8},"https://docshare.wps.com","Home","ListItem",{"item":78,"name":9,"@type":76,"position":14},"https://docshare.wps.com/document/",{"item":80,"name":40,"@type":76,"position":81},"https://docshare.wps.com/document/research-report/",3,{"item":83,"name":65,"@type":76,"position":19},"https://docshare.wps.com/document/project-casper-critical-design-reviewpsp-sl-2020/503721/",{"url":83,"name":65,"@type":85,"image":86,"author":91,"headline":65,"publisher":94,"fileFormat":97,"inLanguage":63,"description":67,"dateModified":98,"datePublished":99,"encodingFormat":97,"isAccessibleForFree":100,"interactionStatistic":101},"DigitalDocument",{"url":87,"@type":88,"width":89,"height":90},"https://docshare.wps.com/thumbnails/project-casper-critical-design-reviewpsp-sl-2020/503721.png","ImageObject",300,407,{"name":92,"@type":93},"asda1da","Person",{"url":74,"name":95,"@type":96},"DocShare","Organization","application/pdf","2026-10-08","2026-10-03",true,{"@type":102,"interactionType":103,"userInteractionCount":81},"InteractionCounter",{"@type":104},"ViewAction",{"@type":106,"mainEntity":107},"FAQPage",[108,114,118],{"name":109,"@type":110,"acceptedAnswer":111},"What are the three mission goals of Project Casper?","Question",{"text":112,"@type":113},"The mission goals are to design, build, test, and fly a student-crafted launch vehicle to a predetermined altitude; carry a UAS payload capable of collecting a lunar ice sample and moving it a set distance; and ensure proper teaching in all aspects of High Power Rocketry.","Answer",{"name":115,"@type":110,"acceptedAnswer":116},"What does the retention system requirement specify and how will it be verified?",{"text":117,"@type":113},"The retention system must be robust enough to endure flight forces in both typical and atypical flights. Verification includes testing to validate the design and construction, designing structurally critical components with a safety factor of at least 2, and confirming effectiveness during a full-scale demonstration flight.",{"name":119,"@type":110,"acceptedAnswer":120},"What is the current status of the derived requirement shown in the document?",{"text":121,"@type":113},"The table indicates the status for the retention-system-related derived requirement is Incomplete, with the associated verification test ID listed as N/A.","https://schema.org",{"og:url":83,"og:type":124,"og:title":65,"og:site_name":95,"og:description":67},"article",{"robots":126,"canonical":83},"index,follow",{"doc_id":128,"site_id":62},503721,1791445919,{"code":4,"msg":5,"data":131},{"doc_id":128,"user_id":132,"nickname":92,"user_avatar":133,"doc_module":4,"category_id":39,"category_name":40,"doc_title":65,"doc_description":67,"doc_content":134,"file_id":135,"file_url":136,"file_type":137,"file_size":138,"view_count":81,"is_deleted":4,"is_public":8,"is_downloadable":8,"audit_status":8,"page_count":139,"language":140,"language_code":63,"site_id":62,"html_lang":63,"table_of_contents":141,"faqs":142,"seo_title":143,"seo_description":67,"update_tm":144,"read_time":145},3985747861852,"https://ap-avatar.wpscdn.com/davatar_155a257f0dc6eb9ab79c44ca47cae57d","# Project Casper\n\nCritical Design ReviewPSP-SL 2020  \n## Mission Statement\n\nOur mission statement can be broken into three distinct goals:  \n● Design, build, test, and fly a student-crafted launch vehicle to apredetermined altitude  \n● To carry a payload consisting of an unmanned aerial system (UAS) capable ofcollecting a lunar ice sample and moving it a set distance  \n● To ensure proper teaching in all aspects of High Power Rocketry  \n\n| | | |\n| --- | --- | --- |\n\n# 2020 Executive Board\n\nLuke Perrin  \nProject Manager  \nJosh BinionPayload TeamColead  \nMichael RepellaAssistant ProjectManager  \nHicham BelhseinePayload TeamColead  \nNoah Stover  \nSafety Team Lead  \nKatelin ZichittellaAvionics TeamLead  \nNatalie KeeferBusiness TeamLead  \nLauren SmithConstruction TeamLead  \nSkyler HarlowSocial & OutreachTeam Lead  \nZach CarrollConstruction TeamMentor  \n## Derived Requirements\n\n4  \n## Derived Requirements & Current Status\n\n\n| A   | Requirement ID: 4.3.7.2Description:  \u003Cbr>The retention system will be robust enoughto successfully endure flight forcesexperienced during both typical andatypical flights.   | Verification Plan: The retention system will be tested tovalidate a robust design and construction, and anystructurally critical components will be designed with asafety factor of at least 2.   |\n| --- | --- | --- |\n| T   |  |  |\n|  |  | Comments: FEA has been completed for all structuralcomponents to ensure a minimum FOS of 2. Effectivenessof the payload retention system will be validated duringthe full-scale demonstration flight.   |\n| Status: Incomplete   |  | Verification Test ID: N/A   |\n\n\n| Inspection   | Demonstration   |\n| --- | --- |\n| Analysis   | Test   |\n\n\n| Test Type   | Completed   | In Progress   | To Be Completed   |\n| --- | --- | --- | --- |\n| NASA Derived   | 62   | 27   | 20   |\n| Team Derived   | 3   | 20   | 14   |\n\n5  \n## Construction Team\n\nTeam Lead: Lauren Smith  \nTeam Mentor: Zach Carroll  \nTeam Members: Ben Hausch | Dimitrios Michalaros | Justin Bagdan |Josiah Campbell | Martin Degener | Jason Hickman | Baoxuan Tao |Boyu Zhou | Hamza Fakhruddin  \n6  \n## Launch Vehicle Topology\n\n● Designed to carry a payload to aaltitude of 4325’ while meetingaerodynamic stability, speed, andlanding kinetic energy requirements  \n● Dual deployment landing system isutilized for safe landing  \n\n| Overall Length   | 125”   |\n| --- | --- |\n| Body Tube Inner Diameter   | 6”   |\n| Estimated Weight   | 53.2 lbm   |\n| Estimated Average LaunchPad Stability   | 3.04 cal   |\n\n7  \nLower  \nAirframe  \nAvionicsBay  \nUpper  \nAirframe  \nPayloadBay  \nNosecone  \nFin Design Avionics Bay  \nFunction: Designed to reduce drag,increase stability, enable streamlining  \n\n| Fin Count   | 3   |\n| --- | --- |\n| Total Weight   | 48.32 oz   |\n| Max Height   | 6.25”   |\n\n8  \nTip chord of 4”, root chord of 12”, fin sweep angle of 50.5°  \nFunction: House primary and redundantaltimeter systems, house camerapayload, initiate vehicle recovery system  \n\n| System Weight   | 6.34 lbm   |\n| --- | --- |\n| Outer Diameter   | 5.975 in   |\n| Total Length   | 14 in   |\n\n## Nose cone Payload Bay\n\nFunction: Designed to reduce drag,features an increased interior volumefor future payloads or electronics, andinterfaces with upper payload coupler  \n\n| System Weight   | 2.8 lbm   |\n| --- | --- |\n| Total Length   | 36 in   |\n| Nosecone Shape   | Von Karman   |\n\n9  \nFunction: Designed to hold the payloadUAS and its retention and deploymentsystem  \n\n| System Weight   | 11.7 lbm   |\n| --- | --- |\n| Total Length   | 18”   |\n| Max Outer Dia.   | 5.775”   |\n\n## Lower Airframe & Fin Set Flow Analysis\n\nGoal: Understand fluiddynamics around aft portion ofvehicle  \nAssumptions: no slip condition,ideal gas (air), standard sealevel conditions, steady state  \nResults: smooth airflow aroundlower airframe, velocitydistribution as expected,pressure at expected levels, nopressure build-ups exceeding  \n10 17.89 psi according to isolines  \n\n| Air Velocity   | 560 ft/s   |\n| --- | --- |\n| Angle of Attack   ","cbCaifmp5AhKgCjJ","https://ap.wps.com/l/cbCaifmp5AhKgCjJ","pdf",13069608,74,"English","# Mission Statement\n# 2020 Executive Board\n## Derived Requirements\n## Construction Team\n## Launch Vehicle Topology\n## Lower Airframe & Fin Set Flow Analysis","[{\"question\":\"What are the three mission goals of Project Casper?\",\"answer\":\"The mission goals are to design, build, test, and fly a student-crafted launch vehicle to a predetermined altitude; carry a UAS payload capable of collecting a lunar ice sample and moving it a set distance; and ensure proper teaching in all aspects of High Power Rocketry.\"},{\"question\":\"What does the retention system requirement specify and how will it be verified?\",\"answer\":\"The retention system must be robust enough to endure flight forces in both typical and atypical flights. Verification includes testing to validate the design and construction, designing structurally critical components with a safety factor of at least 2, and confirming effectiveness during a full-scale demonstration flight.\"},{\"question\":\"What is the current status of the derived requirement shown in the document?\",\"answer\":\"The table indicates the status for the retention-system-related derived requirement is Incomplete, with the associated verification test ID listed as N/A.\"}]","Project Casper - Critical Design ReviewPSP-SL 2020 | PDF",1791059715,186]