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BEGIN:VCALENDAR VERSION:2.0 METHOD:PUBLISH CALSCALE:GREGORIAN PRODID:-//WordPress - MECv6.5.5//EN X-ORIGINAL-URL:https://oursymposium.sites.unlv.edu/ X-WR-CALNAME:Office of Undergraduate Research (OUR) Fall 2021 Virtual Undergraduate Research Symposium X-WR-CALDESC: REFRESH-INTERVAL;VALUE=DURATION:PT1H X-PUBLISHED-TTL:PT1H X-MS-OLK-FORCEINSPECTOROPEN:TRUE BEGIN:VEVENT CLASS:PUBLIC DTSTART;TZID=UTC:20211115T000000 DTEND;TZID=UTC:20211120T000000 DTSTAMP:20211028T000000 UID:MEC-e6af401c28c1790eaef7d55c92ab6ab6@oursymposium.sites.unlv.edu CREATED:20211028 LAST-MODIFIED:20211110 PRIORITY:5 TRANSP:OPAQUE SUMMARY:HNSE-O1-4. Development of Experimental Rocket for Component and Payload Acceleration Load Testing DESCRIPTION:\n\nDrew Nemeth1\nJake Pettitt1\nFaculty Mentor: Brendan O’Toole, Ph.D.1\n1Howard R. Hughes College of Engineering, Department of Mechanical Engineering\nABSTRACT\nWith a burgeoning commercial space industry in the United States, more reliable and cost effective methods for qualifying critical flight components are required in order to reduce the costs of spacecraft development programs. Electronic payloads designed to undergo high acceleration loading during military and civil rocket flight have proven especially difficult to properly flight test prior to operational use. This paper describes the design, construction, flight testing, and post-flight analysis of a single stage launch vehicle with an intended apogee of 50,000 feet and maximum velocity in excess of Mach 2 with a simulated electronic payload. Software suites including OpenRocket, RasAero, and AeroFinSim were utilized in order to confirm rocket stability, a projected flight outline, and structural integrity of the airframe and fin composition/attachment that commonly fail during supersonic flight regimes. The airframe was primarily constructed of G12 filament wound fiberglass tubing in addition to a composite fin can centered around CNC’d G10 fiberglass cores with a wet carbon fiber layup by hand. Flight roll control was achieved via the onboard reaction wheel, which was constructed of 3D printed components and inertial measurement sensors. The completed vehicle experienced a successful flight to 42,000 ft, maximum velocity of Mach 2.2, and maximum acceleration of 16 G. The airframe and all components were safely recovered and in working order post-flight. A successful test of the simulated electronic payload was performed and a low cost flight verification method was established.\n URL:https://oursymposium.sites.unlv.edu/program/development-of-experimental-rocket-for-component-and-payload-acceleration-load-testing/ ORGANIZER;CN=The Office of Undergraduate Research:MAILTO:our@unlv.edu CATEGORIES:Health & Natural Sciences & Engineering END:VEVENT END:VCALENDAR