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Rotating Detonation Engine for Rocket Propulsion

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9300-22-C-6003
Agency Tracking Number: F182-063-1439
Amount: $750,000.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: AF182-063
Solicitation Number: 18.2
Timeline
Solicitation Year: 2018
Award Year: 2022
Award Start Date (Proposal Award Date): 2021-12-14
Award End Date (Contract End Date): 2023-12-14
Small Business Information
2629 Townsgate Road Suite 105
Westlake Village, CA 91361-2981
United States
DUNS: 005100560
HUBZone Owned: No
Woman Owned: Yes
Socially and Economically Disadvantaged: Yes
Principal Investigator
 jason Hamilton
 (805) 371-7556
 jch@hypercomp.net
Business Contact
 Vijaya Shankar
Phone: (805) 371-7556
Email: vshankar@hypercomp.net
Research Institution
N/A
Abstract

We propose here a series of advancements leading to the design of robust and efficient rotating detonation engines (RDE) for rocket propulsion. We will begin with appropriate model upgrades to existing high-fidelity computational modeling tools for accurate modeling of RDE injector with liquid propellants. We will then perform a comparative study of existing test data and perform detailed computational simulations of RDE design variants, focusing on improvements in performance - primarily mixing, followed by combustion efficiency, pressure drop, nozzle geometry, heat transfer, and others. Team members at HyPerComp Inc. have extensive experience in RDE development from computational to experimental perspectives with access to state-of-the-art tools and facilities. There is abundant worldwide interest in RDEs at the present time. This effort seeks to extend existing knowledge, using newer tools and techniques and develop a high-performance device with a strong foundation in design methodology. In Phase II, we aim to understand and quantify efficiency and scaling of rocket RDEs, by high-fidelity modeling and analysis. Physical mechanisms in rocket RDE injectors will be developed and characterized. Numerical simulations will be used to drive design variants of the liquid RDE injectors. High-fidelity computational models will be upgraded with state-of-the-art models including conjugate heat transfer, adaptive mesh refinement, accurate flux scheme for supercritical combustion etc. Conjugate heat transfer in conjunction with LES will aid in understanding heat loads on the hardware which will be utilized for designing an efficient cooling system. Adaptive mesh refinement will help in accurate detonation wave resolution while minimizing overall computational costs.

* Information listed above is at the time of submission. *

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