Development of a vertically landed rocket design challenge for expanding the pipeline and enhancing education of students pursuing careers in space

Trom, Courtney

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https://hdl.handle.net/2142/116292 Copy

Description

Title

Development of a vertically landed rocket design challenge for expanding the pipeline and enhancing education of students pursuing careers in space

Author(s)

Trom, Courtney

Issue Date

2022-07-22

Director of Research (if dissertation) or Advisor (if thesis)

Lembeck, Michael F

Department of Study

Aerospace Engineering

Discipline

Aerospace Engineering

Degree Granting Institution

University of Illinois at Urbana-Champaign

Degree Name

M.S.

Degree Level

Thesis

Keyword(s)

• Rocket
• Reusability
• Engineering
• Design Challenge

Abstract

As part of the DOD funded grant, “Expanding the Pipeline and Enhancing Education of Students Pursuing Careers in Space,” a design challenge was formulated to attract students to careers in aerospace by exposing them to an integrated set of educational resources. As part of the program undertaken to achieve this objective, a student aerospace design challenge was formulated, focused on vertically landing a previously lofted model rocket, hereafter called the vertically landed rocket (VLR). This thesis describes the processes, analyses, and testing undertaken to satisfy this objective. A modified model rocket was developed to be carried aloft by an unmanned aerial vehicle (UAV), released from the UAV, and allowed to descend under the control of a gimballed solid rocket motor to an upright landing. To accomplish this, the rocket incorporated an avionics package, including software and sensors to track and monitor orientation, and a pair of servos to gimbal the model rocket motor slowing the descending rocket to a landing on an extended set of legs mounted circumferentially around the rocket base. This concept is designed to be packaged as a project with assembly instructions and educational videos that student teams could work on in either a moderated classroom or at home in a self-paced environment. To validate design choices, a series of verification tests were conducted. A simulation has been created to find optimal flight parameters and predict the VLR’s performance. The motor’s thrust output and performance had been tested and verified and fed back into the simulation to refine parameters and performance predictions. A closed loop test was conducted to examine the effect sensor noise would have on the rocket and to verify even in its presence, that the VLR could successfully land. A thrust test stand was created and tested on to verify that the avionics and power were capable of igniting the motor and maintaining control over the gimbal while remaining powered and in contact with the ground station. A mode verification test was conducted to verify the software’s capability of stepping through the different modes of flight and to ensure data collection and unhindered connection with the ground station. Finally, a series of drop tests were conducted to verify the passive stability of the rocket and to verify the landing legs’ ability to accept and disperse energy of landing. This series of tests validated the design choices and led to the approval to test powered VLRs.

Graduation Semester

2022-08

Type of Resource

Thesis

Copyright and License Information

Copyright 2022 Courtney Trom

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