Development of a Concept Hybrid Rocket Demonstrator

Dustin Birch

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Conference: 2022 ASEE Annual Conference & Exposition
Location: Minneapolis, MN
Publication Date: August 23, 2022
Start Date: June 26, 2022
End Date: June 29, 2022
Conference Session: Aerospace Division Technical Session: New and Innovative Technologies in Aerospace
Page Count: 16
DOI: 10.18260/1-2--40393
Permanent URL: https://peer.asee.org/40393
Download Count: 509

Paper Authors

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Dustin Birch Weber State University

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Dustin Birch possesses a Doctor of Philosophy in Systems Engineering from Colorado State University, a Master of Science in Mechanical Engineering from the University of Utah, a Bachelor of Science in Mechanical Engineering from the University of Utah, and an Associate of Science in Design and Drafting Engineering Technology from Ricks College. Dustin teaches in the Department of Mechanical Engineering at Weber State University in Ogden, Utah.

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Abstract

Most conventional rockets are of an either solid fuel or liquid fuel configuration. Nearly all production rocket motors produced throughout modern history are one of these two types. Conversely, a hybrid rocket utilizes a solid fuel grain and liquid oxidizer, thus capitalizing on the inherent advantages of both designs. A hybrid rocket exploits the power density (power per unit volume) of a solid fuel rocket, and the start-stop and throttling capability of a liquid fuel rocket. To date, only a few hybrid rocket designs have been developed to a production level configuration. This type of rocket motor technology remains largely in the experimental domain. The Concept Hybrid Rocket Demonstrator (CHRD) is a small scale, modular, low-cost hybrid rocket design, for use in hybrid rocket research as well as educational applications in senior capstone curriculum for an undergraduate Mechanical or Aerospace Engineering or Engineering Technology program. Basic research activities include investigations of rocket fuel types and fuel grain port configurations, ignition systems, oxidizer delivery systems, rocket nozzle materials and aerodynamics, instrumentation schemes, and analytic modeling of rocket performance using computational software. The first generation of CHRD has been designed, fabricated, and tested successfully. A small rocket motor approximately two inches in diameter and ten inches long was fired multiple times during the spring of 2021, with preliminary results of rocket performance being documented. The current rocket prototype was the product of two consecutive academic years of senior capstone teams’ efforts. The design, fabrication, and testing was supervised by a Mechanical Engineering faculty, who assumed the role of project manager and chief investigator. The rocket system, as currently designed, was produced for under $3000 USD, and met most of the initial operational and performance goals. The current design includes a modular approach to fuel grain replacement, greatly simplifying and expediting the tasks related to multiple test firings in quick succession. Additionally, the design utilizes several Commercially Available Off-the-Shelf (COTS) components to simplify the design and reduce costs. The current configuration operates using Hydroxyl Terminated Polybutadiene (HTPB) as the solid fuel grain, and Nitrous Oxide (N2O) as the liquid oxidizer. Both of these substances are individually inert, and safe, thus rendering the rocket components very safe for storage, transport, and handling, making this approach attractive for student involvement in an informal environment. To date, the CHRD has been developed to the point of demonstrating a functioning hybrid fuel rocket motor that produces thrust at a level comparable to the values predicted in the associated analytical model. Future development is intended to improve system reliability. Specifically, ignition system and converging-diverging nozzle performance and durability are being addressed in the current design iteration. Additionally, an improved instrumentation suite to better measure key motor performance characteristics such as oxidizer flow rate as well as combustion chamber temperature and pressure.

Citation
Format

Birch, D. (2022, August), Development of a Concept Hybrid Rocket Demonstrator Paper presented at 2022 ASEE Annual Conference & Exposition, Minneapolis, MN. 10.18260/1-2--40393

TY - CPAPER
AB - Most conventional rockets are of an either solid fuel or liquid fuel configuration. Nearly all production rocket motors produced throughout modern history are one of these two types. Conversely, a hybrid rocket utilizes a solid fuel grain and liquid oxidizer, thus capitalizing on the inherent advantages of both designs. A hybrid rocket exploits the power density (power per unit volume) of a solid fuel rocket, and the start-stop and throttling capability of a liquid fuel rocket. To date, only a few hybrid rocket designs have been developed to a production level configuration. This type of rocket motor technology remains largely in the experimental domain.
The Concept Hybrid Rocket Demonstrator (CHRD) is a small scale, modular, low-cost hybrid rocket design, for use in hybrid rocket research as well as educational applications in senior capstone curriculum for an undergraduate Mechanical or Aerospace Engineering or Engineering Technology program. Basic research activities include investigations of rocket fuel types and fuel grain port configurations, ignition systems, oxidizer delivery systems, rocket nozzle materials and aerodynamics, instrumentation schemes, and analytic modeling of rocket performance using computational software.
The first generation of CHRD has been designed, fabricated, and tested successfully. A small rocket motor approximately two inches in diameter and ten inches long was fired multiple times during the spring of 2021, with preliminary results of rocket performance being documented. The current rocket prototype was the product of two consecutive academic years of senior capstone teams’ efforts. The design, fabrication, and testing was supervised by a Mechanical Engineering faculty, who assumed the role of project manager and chief investigator.
The rocket system, as currently designed, was produced for under $3000 USD, and met most of the initial operational and performance goals. The current design includes a modular approach to fuel grain replacement, greatly simplifying and expediting the tasks related to multiple test firings in quick succession. Additionally, the design utilizes several Commercially Available Off-the-Shelf (COTS) components to simplify the design and reduce costs. The current configuration operates using Hydroxyl Terminated Polybutadiene (HTPB) as the solid fuel grain, and Nitrous Oxide (N2O) as the liquid oxidizer. Both of these substances are individually inert, and safe, thus rendering the rocket components very safe for storage, transport, and handling, making this approach attractive for student involvement in an informal environment.
To date, the CHRD has been developed to the point of demonstrating a functioning hybrid fuel rocket motor that produces thrust at a level comparable to the values predicted in the associated analytical model. Future development is intended to improve system reliability. Specifically, ignition system and converging-diverging nozzle performance and durability are being addressed in the current design iteration. Additionally, an improved instrumentation suite to better measure key motor performance characteristics such as oxidizer flow rate as well as combustion chamber temperature and pressure.

AU - Dustin Birch
CY - Minneapolis, MN
DA - 2022/08/23
PB - ASEE Conferences
TI - Development of a Concept Hybrid Rocket Demonstrator
UR - https://peer.asee.org/40393
DO - 10.18260/1-2--40393
ER -