Performance Validation of a Single-Tube Pulse Detonation Rocket System

Abstract

A pulse detonation engine (PDE) can be operated even if there are no compression mechanisms such as compressors or pistons, and a rocket engine with an extremely low combustor fill pressure (pulse detonation rocket, PDR) thus becomes possible. In this research, we made a model PDR system with increased specific impulse by partial fill. The performance predicted by this model was then confirmed experimentally. The thrust can be calculated by using the simplified PDE model of Endo et al. and the partial filling effect models of Sato et al. The mass flow rate of the propellant supplied from the pressurized cylinders is considered in this calculation. As a result, the thrust performance can be determined by the kind of propellant, the initial conditions of the gas in the cylinders, the supply-valve orifice and PDE-tube volume, and the operation frequencies. We fabricated a pulse detonation rocket (PDR) named “TODOROKI” and verified the thrust calculation model via a horizontal sliding test. We confirmed that the stability of the PDE operation depends on the ratio between the purge-gas thickness and the tube diameter. The thrust predicted by the model was identical to experimental results within 4%.