Multimode Detonation for Small Scale In-Space Propulsion

Abstract

The overall objective of this proposed effort is to characterize multimode detonation, detonability limits, and performance of small-scale, detonation-based rocket thrusters for versatile in-space propulsion. This proposed study will address the underlying basic physics knowledge gaps required for exploring detonation-based combustion in small-scale thrusters for in-space applications using both gaseous hydrogen (H2) and methane (CH4) as fuel, with gaseous oxygen (O2) as the oxidizer.

Document Details

Document Type
DoD Grant Award
Publication Date
Mar 06, 2024
Source ID
FA95502310371

Entities

People

  • John Bennewitz

Organizations

  • Air Force Office of Scientific Research
  • United States Air Force
  • University of Alabama in Huntsville

Tags

Fields of Study

  • Physics

Readers

  • Aerospace Propulsion Engineering.
  • Optical Physics and Photonics.
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster