LASER PROPULSION 10-KW THRUSTER TEST PROGRAM RESULTS

This article summarizes the results of the first-ever experimental tes ts of a 10-kW laser-powered rocket engine. The rocket engine used high -temperature laser-sustained plasmas to heat flows of argon and hydrog en propellants, which were then exhausted through a rocket nozzle to g enerate thrust. The design of the thruster and test support equipment is described in detail, followed by a summary of performance data, par ticularly specific impulse and thruster efficiency. Specific impulse v alues of up to 350 s at efficiencies near 40% were obtained using hydr ogen propellant. A low-velocity stability limit for laser-sustained pl asmas was also discovered, which may have important implications for t he design of future laser propulsion systems.