초록 ▼

A recoverable/reusable booster stage has air-breathing jet engines mounted on the inter-tank ring in alignment with the center axis of the booster body. The jet engines provide supplemental lift on ascent, power the booster on a return flight, and hover the spent booster for a vertical, tail-down la

A recoverable/reusable booster stage has air-breathing jet engines mounted on the inter-tank ring in alignment with the center axis of the booster body. The jet engines provide supplemental lift on ascent, power the booster on a return flight, and hover the spent booster for a vertical, tail-down landing at the launch site.

대표청구항 ▼

1. A reusable launch vehicle comprising:a first stage comprising a first engine and a second engine, said first engine comprising a rocket engine, said second engine comprising an air breathing engine, the first stage comprising fuel and control systems for the first and second engines, the first st

1. A reusable launch vehicle comprising:a first stage comprising a first engine and a second engine, said first engine comprising a rocket engine, said second engine comprising an air breathing engine, the first stage comprising fuel and control systems for the first and second engines, the first stage adapted to lift off with thrust from both the first and second engines; anda second stage comprising a third engine, said third engine comprising a rocket engine, the second stage releasably coupled to the first stage and adapted to carry a payload, the second stage adapted to release from the first stage at a selected time, the second engine adapted to propel the first stage in atmospheric flight to a selected landing site, the second engine adapted to support the first stage in a hover so that the first stage lands in a substantially vertical condition whereby the first stage is recovered for re-use in a manner that does not substantially reduce ascent performance with drag and weight penalties from wings and landing gear. 2. The launch vehicle of claim 1, wherein said second engine comprises a turbojet engine. 3. The launch vehicle of claim 1, wherein said second engine comprises a plurality of airbreathing engines attached symmetrically to the first stage whereby two or more smaller engines generate a balanced thrust.