Laser-powered multi-newton thrust space engine with variable specific impulse

Claude R. Phipps; James R. Luke; Wesley Helgeson

doi:10.1117/12.786459

12 May 2008 Laser-powered multi-newton thrust space engine with variable specific impulse

Claude R. Phipps, James R. Luke, Wesley Helgeson

Author Affiliations +

Proceedings Volume 7005, High-Power Laser Ablation VII; 70051X (2008) https://doi.org/10.1117/12.786459
Event: High-Power Laser Ablation 2008, 2008, Taos, New Mexico, United States

Abstract

Recently we became interested in applying previous work with liquid fueled laser powered minithrusters for spacecraft orientation to the conceptual design of a multi-newton thruster based on the same principles. Solid-fuel configurations (such as the fuel tapes used in the Photonic Associates microthruster) are not amenable to the range of mass delivery rates (g/s to g/s) necessary for such an engine. We will discuss problems for this design which have been solved, including identifying a practical method of delivering liquid fuel to the laser focus, avoiding splashing of liquid fuels under pulsed laser illumination, and avoiding optics clouding due to ablation backstreaming on optical surfaces from the laser-fuel interaction region. We have already shown that I_sp = 680 seconds can be achieved by a viscous liquid fuel based on glycidyl azide polymer and an IR-dye laser absorber. The final problem is mass: we will discuss a notional engine design which fits within a 10-kg "dry mass" budget. This engine, 80kg mass with fuel, is designed to fit within a 180-kg spacecraft, and use 3kW of prime power to deliver a Δv of 17.5 km/s to the spacecraft in sixteen months. Its specific impulse will be adjustable over the range 200sp<3,600 seconds and maximum thrust will be 6N, based on performance which has been demonstrated in the laboratory. Such an engine can put small satellites through demanding maneuvers in short times, while generating the optimum specific impulse for each mission segment. We see no reason why I_sp = 10,000 seconds cannot be achieved with liquid fuels.

Citation Download Citation

Claude R. Phipps, James R. Luke, and Wesley Helgeson "Laser-powered multi-newton thrust space engine with variable specific impulse", Proc. SPIE 7005, High-Power Laser Ablation VII, 70051X (12 May 2008); https://doi.org/10.1117/12.786459

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