Experimental Investigation of the Constant-Volume Pulsed Rocket Concept (PREPRINT)

摘要

Constant-volume combustion pulsed rocket systems may offer significant operational advantages over traditional constant-pressure rocket systems, including the reduced weight and complexity of low pressure propellant feed systems. A novel sub-scale facility has been built and tested at AFRL to assess the merits and feasibility of a constant-volume pulsed combustion rocket motor. Initial hotfire testing has been performed and those results are compared with a simple transient numerical model to assess performance. In initial testing with nitromethane based monopropellants, little modulation in chamber pressure has been achieved. Some substantial chamber pressure modulation has been achieved in partially pulsed bi-propellant operation, but this behavior is still significantly below ideal levels. Further modification of test hardware and use of more volatile monopropellants may enable a more operable cycle.