| 摘要 |
A system for supplying a space station or satellite comprises a low cost expendable single-stage to orbit launch vehicle having a moderate reliability in the range of about 0.5 to 0.8 for launching a payload of consumable items to low earth orbit. For propulsion, the launch vehicle includes a pressure-fed rocket engine, preferably with a nozzle for aiming products of combustion in a direction away from the launch vehicle and having a fixed orientation relative to the launch vehicle. A pressurant tank contains an inert pressurant gas under pressure. A conduit system serves to introduce the inert pressurant gas from the pressurant tank to a fuel tank and thence to the rocket engine and also to introduce the inert pressurant gas from the pressurant tank to an oxidizer tank and thence to the rocket engine for combustion with the fuel. The initial pressure in the pressurant tank is maintained at a level in excess of about 100 bar; the initial pressure in the fuel tank and in the oxidizer tank is maintained at a level in the range of about 8.5 to 20.0 bar; and the initial pressure in the rocket engine is maintained at a level in the range of about 5 to 10 bar. Additional conduits are provided for adding inert pressurant gas to the pressurant tank or for removing pressurant gas therefrom, for adding fuel to the fuel tank or for removing fuel therefrom, and for adding oxidizer to the oxidizer tank or for removing oxidizer therefrom.
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