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Analysis of beamed-energy ramjet/scramjet performanceA study has been performed on a laser-heated ramjet/scramjet vehicle concept for propulsion during the air-breathing portion of an orbital launch trajectory. The concept considers axisymmetric, high-thrust vehicles with external inlets and nozzles. Conceptual design and ramjet/scramjet cycle analysis are emphasized, with propulsive energy provided by combustion of on-board fuel. The conventional ramjet/scramjet combustion chamber is replaced by a laser energy absorption chamber. The elimination of on-board propellant can result in very high thrust-to-weight ratios and payload fractions, in a vehicle with a relatively small degree of mechanical complexity. The basic vehicle has a weight of 12,250 lbf, and a diameter of 5 meters, which is close to the size of the Apollo command module. The ramjet calculations are based on a Mach 3 isentropic inlet with a 13.7 degree half-angle conical tip. The scramjet analysis considers conical inlets with 10, 15, and 30 degree half-angles. Flight Mach numbers from 2 to 20 are considered in the calculations.
Document ID
19870034251
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Myrabo, L. N.
(Rensselaer Polytechnic Institute, Troy, NY, United States)
Powers, M. V.
(Rensselaer Polytechnic Inst. Troy, NY, United States)
Zaretzky, C. L.
(Rensselaer Polytechnic Inst. Troy, NY, United States)
Date Acquired
August 13, 2013
Publication Date
June 1, 1986
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 86-1761
Accession Number
87A21525
Distribution Limits
Public
Copyright
Other

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