An investigation was conducted to determine the performance and feasibility of a single-stage-to-orbit shuttlecraft (SSTO) utilizing laser-heated air-breathing propulsion modes. External Radiation-Heated (ERH) thruster, ramjet, scramjet and laser-heated rocket modes were analyzed in depth along a variety of orbital launch trajectories, with flight Mach numbers ranging from 0 to 20. Propulsive energs is provided by an external laser source and delivered by a relay satellite in low-earth orbit, rather than by the combustion of on-board propellants. The result is a vehicle with a large payload fraction (9.0 %), capable of very high thrust-to-weight ratios. Possible launch trajectories were analyzed to determine the optimum trajectory taking into consideration the total laser energy required, pilot acceleration tolerance, dynamic pressure limitations, and amount of propellant used by the laser-heated rocket for final orbital insertion. The basic vehicle is axisymmetric, 9.5 meters long and 6 meters in diameter, with a design weight of approximately 5555 kg and a design payload of 500 kg. The vehicle forebody was modeled after a Mach 3 isentropic-spike inlet, and payload considerations were based on the Apollo Command Module. The importance of real gas effect was recognized but no incorporated in this analysis.
Performance annalysis of a laser-heated single-stage-to-orbit shuttlecraft
Untersuchung des Verhaltens von mittels Lasererhitzung in einer Stufe in die Umlaufbahn gebrachten Raumfaehren
AIAA-Papers ; Jul ; 1-19
1987
19 Seiten, 32 Bilder, 1 Tabelle, 11 Quellen
Conference paper
English
Single-Stage-to-Orbit Versus Two-Stage-to-Orbit Airbreathing Systems
Online Contents | 2010
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