The high-powered model rocket (HPMR) is designed for an apogee of 457 m, with clustered engines, staged propulsion, actively controlled stabilizing fins, a deployable autorotating rotor recovery system, three cameras, an inertial measurement unit and three strain gauges. This project involves component design and fabrication, HPMR integration, structural, aerodynamic, and thermal analysis as well as functionally testing. SolidWorks is used for component design and integration. ANSYS simulations provide the structural loads on HPMR components and safety factors. FLUENT simulations and analytical modeling determine the drag forces during ascent. COMSOL simulations provide component temperatures using heat loads expected from the solid motors. Flight test analysis is presented.

• This report represents the work of one or more WPI undergraduate students submitted to the faculty as evidence of completion of a degree requirement. WPI routinely publishes these reports on its website without editorial or peer review.

Creator

• Foster, Kyle Francis
• Lapierre, Nicholas Jon
• Fennick, Jacob Hance
• George, Eve Marie
• Moquin, Ty F
• Dings, Amanda
• Cooper, Colin Yuen-Lim
• Dohn, Peter David

Publisher

• Worcester Polytechnic Institute

Identifier

• E-project-031519-135821

Advisor

• Gatsonis, Nikolaos A.
• Yang, Jun

Year

• 2019

Date created

• 2019-03-15

Resource type

• Major Qualifying Project

Major

• Aerospace Engineering

Rights statement

• In Copyright