Download

Download Full Text (2.5 MB)

Description

Annular spike nozzle engines have long been the holy grail of rocket engine design, promising superior performance in a smaller footprint when compared to conventional bell nozzles. However, flaws inherent to the design of spike nozzles have prevented widespread adoption and testing. As a result, research on potential applications has been quite sparse. This project aims to further spike nozzle research by investigating rarely tested materials that literature suggests have potential for use in a spike nozzle design. The goal of the overall research project is to examine 3D printed polycarbonate component longevity under conditions representative of a small satellite in orbit. A literature review concluded that spike nozzle overheating challenges might be less relevant in situations that value availability and safety over peak efficiency. A series of computational fluid dynamic simulations were performed to compare the theoretical performance of equivalently massed 50% hydrogen peroxide catalytic aerospike and DeLaval thrusters under low Earth orbit conditions. It was found that polycarbonate aerospikes might present mass savings over conventional DeLaval nozzles in these conditions.

Publication Date

Spring 2021

Language

English

Keywords

Rocketry; Aerospace; Spike nozzle; Catalytic thruster

Disciplines

Mechanical Engineering | Physics

File Format

pdf

File Size

2518 KB

Comments

Faculty Mentor: Yi-Tung Chen, Ph.D.

Spike Nozzle Design For Use In Nanosat Orbital Maneuvering


Share

COinS