Thrust Measurement of a Split-Path, Valveless Pulse Detonation Engine

摘要

Theory predicts ideal pulse detonation technology offers significant fuel efficiency advantages over ramjet/scramjet architecture within a range from high subsonic to low hypersonic velocities. In practice, Pulse Detonation Engines (PDE) require implementation of loss-inducing techniques such as turbulence-generation devices to achieve and sustain detonation events, which effectively narrows the efficiency gap between the two technologies. Pressure losses associated with such obstacles lower system specific thrust (Isp) and reduce overall system performance. Although fundamental PDE research has been ongoing at NPS for seven years, no dedicated attempt has been made to accurately measure the experimental performance. Fuel-based Isp is a function of the ratio of thrust produced to fuel mass flow rate; thus, accurate computation requires precise knowledge of both thrust and input fuel. This thesis focused on creating an accurate thrust collection system incorporating an existing, uncalibrated rocket thrust stand. An in depth, axial component thrust calibration was conducted for the stand itself, then with the engine mounted in the firing configuration. As expected, harmonic responses of the stand during detonation experimentation were experienced which required creation and implementation of filtering algorithms to successfully extract useful thrust values.