Patent ID: 6488237
Filing Date: 2002-12-03
Classification: B64G,F02K

Abstract:
A two-stage rocket having a booster and an orbiter, the two-stage rocket capable of supplying propellant simultaneously to both the booster and the orbiter,the rocket comprising:a booster and orbiter propellant tanks each configured to contain a reservoir of the propellant; a booster and orbiter engines each configured to burn the propellant and produce thrust; a booster supply line connecting in fluid communication the booster propellant tank to the booster engine and supplying the propellant to the booster engine; an orbiter supply line connecting in fluid communication the orbiter propellant tank to the orbiter engine and supplying the propellant at a flow rate to the orbiter engine; and a cross-feed system comprising: a cross-feed line connecting the booster supply line and the orbiter supply line in fluid communication, the cross-feed line having a first pressure at its booster end and a second pressure at its orbiter end, the cross-feed line including a low pressure drop check valve configured to begin closing as the second pressure exceeds the first pressure; and a switch-over valve connected to the orbiter supply line and operable to increase the flow rate of the propellant in the orbiter supply line resulting in an increase of the second pressure so as to cause the low pressure drop check valve to close and inhibit flow of the propellant from the orbiter supply line to the booster supply line.