We discuss the requirements for developing a lightweight laser‐powered space engine with specific impulse range seconds and 6N maximum thrust. Operating parameters which can achieve this have been demonstrated separately in the laboratory. We review earlier solid fuel data. Such an engine can put small satellites through demanding maneuvers in short times, while generating the optimum specific impulse for each mission segment.
We will address specific problems which have been solved. The first of these is fuel delivery to the laser focus. A pulsed laser format is required for reasons we will discuss. Solid‐fuel configurations (such as the fuel tapes used in the Photonic Associates μLPT microthruster) are not amenable to the range of mass delivery rates (μg/s to mg/s) necessary for such an engine. Liquid fuels are suggested. However, liquids with ordinary viscosities splash under pulsed laser illumination, ruining engine performance by causing the majority of fuel mass to be ejected at low We have shown that seconds can be achieved by a viscous fuel based on glycidyl azide polymer and an IR‐dye laser absorber. The second problem is optics clouding from ablated material. This can be handled actively by a flowing gas system. The final problem is mass: we will present an engine design which fits within a 10‐kg “dry mass” budget.
The engine, 80 kg mass with fuel, is designed to fit within a 180‐kg spacecraft, and use up 3 kW of prime power to deliver a Δv of 17.5 km/s to the spacecraft in sixteen months.
Liquid‐fueled, Laser‐powered, N‐class thrust Space Engine with Variable Specific Impulse
BEAMED ENERGY PROPULSION: Fifth International Symposium on Beamed Energy Propulsion ; 2007 ; Kailua‐Kona (Hawaii)
AIP Conference Proceedings ; 997 , 1 ; 222-231
2008-04-28
10 pages
Conference paper
Electronic Resource
English
Liquid-fueled, Laser-powered, N-Class Thrust Space Engine with Variable Specific Impulse
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