Feasibility Test of Rotating Detonation Rocket Engine Using Storable Hypergolic Bipropellants

Under a recently completed Phase I SBIR project, GHKN Engineering, LLC (GHKN) designed and built an entirely new, laboratory rotating detonation rocket engine (RDRE) for use with hypergolic bipropellants. GHKN then loaned this engine to a major supplier of conventional hypergolic engines, Aerojet Rocketdyne (AR), who successfully conducted a first-of-its kind vacuum test of this engine using MON3/MMH. Having demonstrated the ability to design and test several configurations of this modular engine, GHKN herein proposes a test-oriented Phase II program, using the modular engine developed in Phase I, to further explore the trade space to identify the configurations and operating conditions that most favor stable rotating detonation with liquid hypergolic bipropellants. The proposal includes three separate test series to be conducted in vacuum chambers at AR’s Redmond, WA facility, spaced to allow analysis of results of each series, as well as design and fabrication of hardware for the next test series. Each test series will allow multiple configurations to be tested. Configuration variables to be explored include start techniques, injector type, and annular width, length, diameter and constriction. Based on the test results, the GHKN/AR team will then assess the potential of hypergolic bipropellant RDRE technology for in-space application.