Maseeh Summer Undergraduate Research Experience

Funding Source

Undergraduate Research and Mentoring Program (URMP)

Document Type

Poster

Publication Date

2024

Abstract

This project presents the airframe stability analysis and recovery system design for Launch Vehicle No. 3.1 (LV3.1) at the Portland State Aerospace Society. Rocket stability relies on maintaining the center of gravity (CG) above the center of pressure (CP). Component masses were modeled in Onshape CAD and simulated in OpenRocket, yielding a stability margin of 2.7 cal for LV3.1. This meets the minimum stability requirement of 2 cal or greater for reaching Mach 1.041 and an apogee of 14,584 ft. Airframe weight was minimized using lightweight materials—including carbon fiber, 3D-printed parts, and aluminum modules machined with an isogrid pattern. For recovery, a three-stage non-pyrotechnic Electromechanical Recovery System (ERS) was implemented to safely execute stage separation and parachute deployment.

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