Experimental Study of a Hypergolically Ignited Liquid Bipropellant Rotating Detonation Rocket Engine
Wesly S. Anderson, Stephen D. Heister, Brandon Kan, Carl Hartsfield
Abstract
A liquid bipropellant rotating detonation rocket engine was successfully test fired. The 6.5-in.-diam engine operates on a mixture of rocket-grade hydrogen peroxide and triglyme. Ignition is accomplished hypergolically, with the addition of a promoter to the fuel. Eight cases of spontaneously initiated, single-wave, rotating detonations were observed. Detonation wave speeds were near or exceeding Chapman–Jouguet calculations. Evidence of condensed-phase reactions was also seen, damaging hardware in short order. Both a rotating detonation and a bulk-slapping mode characterized the engine operation.
Topics & Concepts
DetonationRocket engineIgnition systemRocket (weapon)Materials scienceLiquid-propellant rocketDeflagration to detonation transitionAerospace engineeringCombustionPropellantHydrogen peroxideNuclear engineeringMechanicsEngineeringPhysicsChemistryExplosive materialOrganic chemistryCombustion and Detonation ProcessesEnergetic Materials and CombustionRocket and propulsion systems research