| 摘要 |
A two-stage space vehicle is provided for achieving low earth orbit that includes a carrier and an orbiter. The carrier has a large airfoil area relative to its dry weight, and the thrust of the rocket engine is controlled such that the carrier achieves a launch altitude and speed for the orbiter without exceeding a wingloading pressure beyond 3,500 Pa., which allows the carrier to be inexpensively constructed. Liquid propellant for the rocket engine is advantageously stored within the relatively large airfoil of the carrier, which is preferably a delta wing. The ratio of airfoil area to dry weight is about 33 m2 per ton, which allows the carrier to descend and land after launching the orbiter with low wingloading on the order of 300 Pa.
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