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Laser rocket system analysisThe laser rocket systems investigated in this study were for orbital transportation using space-based, ground-based and airborne laser transmitters. The propulsion unit of these systems utilizes a continuous wave (CW) laser beam focused into a thrust chamber which initiates a plasma in the hydrogen propellant, thus heating the propellant and providing thrust through a suitably designed nozzle and expansion skirt. The specific impulse is limited only by the ability to adequately cool the thruster and the amount of laser energy entering the engine. The results of the study showed that, with advanced technology, laser rocket systems with either a space- or ground-based laser transmitter could reduce the national budget allocated to space transportation by 10 to 345 billion dollars over a 10-year life cycle when compared to advanced chemical propulsion systems (LO2-LH2) of equal capability. The variation in savings depends upon the projected mission model.
Document ID
19790013166
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Jones, W. S.
(Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Forsyth, J. B.
(Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Skratt, J. P.
(Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Date Acquired
September 3, 2013
Publication Date
March 15, 1979
Subject Category
Lasers And Masers
Report/Patent Number
LMSC-D564671-A
NASA-CR-159521
Accession Number
79N21337
Funding Number(s)
CONTRACT_GRANT: NAS3-20372
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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