Conical solar absorber/thruster for space propulsion
- AlliedSignal Aerospace Equipment Systems, Torrance, CA (United States)
Solar-powered space propulsion uses solar heating of a propellant such as hydrogen to impart thrust to a rocket when the hydrogen exists through an appropriately designed nozzle. Because of the low molecular weight of hydrogen, exhaust velocities, and hence specific impulses, can potentially be much greater than for chemical combustion of fuel. A very efficient solar thermal absorber design has been developed. The design consists of two interwound helical coils of rhenium tubing, through which the propellant flows to be heated before being exhausted out a rhenium nozzle. The conical absorbing surface is configured to conform to the extreme solar rays from a solar concentrator; i.e., the receiver apex angle is designed to match the concentrator apex angle. This shape helps to minimize the amount of reflected or emitted energy lost through the receiver aperture.
- OSTI ID:
- 116229
- Report Number(s):
- CONF-950336-; ISBN 0-7918-1300-2; TRN: IM9545%%196
- Resource Relation:
- Conference: American Society of Mechanical Engineers/Japanese Society of Mechanical Engineers/Japan Solar Energy Society international solar energy conference, Lahaina, HI (United States), 19-24 Mar 1995; Other Information: PBD: 1995; Related Information: Is Part Of Solar engineering 1995: Proceedings. Volume 2; Stine, W.B. [ed.] [California Polytechnic Univ., Pomona, CA (United States)]; Tanaka, Tadayoshi [ed.] [Electrotechnical Lab., Ibaraki (Japan)]; Claridge, D.E. [ed.] [Texas A and M Univ., College Station, TX (United States)]; PB: 582 p.
- Country of Publication:
- United States
- Language:
- English
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