초록 ▼

A launch system is provided which includes a secondary payload. The secondary payload includes a propellant tank and at least one module that is supported by an adapter ring that is commonly used to secure an upper stage to a primary payload. The propellant tank is launched empty and subsequently fi

A launch system is provided which includes a secondary payload. The secondary payload includes a propellant tank and at least one module that is supported by an adapter ring that is commonly used to secure an upper stage to a primary payload. The propellant tank is launched empty and subsequently filled with residual propellant from the upper stage.

대표청구항 ▼

1. A method of fueling a secondary payload delivery system that is launched into orbit or beyond in association with a primary payload delivery system, comprising: a) providing primary payload delivery system comprising a launch vehicle with a booster stage, an upper stage interconnected to the boos

1. A method of fueling a secondary payload delivery system that is launched into orbit or beyond in association with a primary payload delivery system, comprising: a) providing primary payload delivery system comprising a launch vehicle with a booster stage, an upper stage interconnected to the booster stage, the upper stage including a first tank for holding a propellant and a secondary payload delivery system including a second tank for holding the propellant;b) providing the first tank with propellant prior to launch and providing the second tank without or substantially without propellant prior to launch;c) when the upper stage and secondary payload delivery system are in space, directing flow of the propellant from said first tank to said second tank;d) filling said second tank in space with a predetermined amount of propellant;e) ceasing the flow of propellant from said first tank to said second tank in space; andf) separating said upper stage and said secondary payload delivery system in space. 2. The method of claim 1, further comprising: venting a portion of the propellant through an outlet associated with the second tank; anddirecting the vented propellant so as to locate a liquid portion thereof adjacent to a feed line that directs the propellant from said first tank to the second tank. 3. The method of claim 1, wherein the separating occurs after the secondary payload delivery system is used to ferry the upper stage to a predetermined orbit. 4. The method of claim 3, wherein the second tank receives propellant from the first tank subsequent to delivery to said predetermined orbit and prior to the separating. 5. The method of claim 1, wherein the secondary payload delivery system is comprised of the second tank that is positioned with a ring that is associated with the upper stage, the ring including ports for at least one of a propulsion module, a control module and a data module. 6. The method of claim 5, wherein the ring is separable from the upper stage. 7. The method of claim 1, further comprising at least one of transferring the upper stage and the secondary payload delivery system to a second orbit and providing sufficient velocity to the upper stage and secondary payload delivery system to escape a gravitational pull of a body in space. 8. The method of claim 1, further comprising transferring the upper stage and the secondary payload delivery system to a second orbit and separating the secondary payload delivery system from the upper stage. 9. The method of claim 1, further comprising separating the secondary payload delivery system from the upper stage. 10. The method of claim 2, wherein said directing further comprises filling the second tank a predetermined amount. 11. The method of claim 2, wherein said directing further comprises ceasing the flow of propellant into the second tank.