Patent ID: 8807485

Claim:
A system for launching dual manifested spacecraft into outer space, the system comprising: a launch vehicle for placing spacecraft in orbit; a first spacecraft housed within the launch vehicle for being launched to outer space; a second spacecraft housed within the launch vehicle for being launched into outer space together with the first spacecraft; a coupling mechanism configured to selectively and securely couple the first spacecraft to the second spacecraft, wherein the coupling mechanism has an uncoupled configuration, in which the coupling mechanism is configured to permit the second spacecraft to become mated with the first spacecraft, and a coupled configuration, in which the coupling mechanism is configured to restrict the second spacecraft from being demated from the first spacecraft, wherein the coupling mechanism is spring-biased to the coupled configuration, and wherein the coupling mechanism is configured to utilize a pneumatic pressure for transitioning from the coupled configuration to the uncoupled configuration and spring force for transitioning from the uncoupled configuration to the coupled configuration; wherein the first spacecraft and the second spacecraft each include an interstage adapter, and wherein the coupling mechanism is operatively coupled to the interstage adapter of the first spacecraft; wherein one of the first spacecraft and the second spacecraft defines a channel and the other of the first spacecraft and the second spacecraft defines a collar configured to be positioned within the channel when the second spacecraft is mated with the first spacecraft; wherein the interstage adapter of one of the first spacecraft and the second spacecraft defines the collar and the interstage adapter of the other of the first spacecraft and the second spacecraft defines the channel; wherein the first spacecraft defines at least one bore and the second spacecraft defines at least one bore that is positioned to be aligned with the at least one bore of the first spacecraft when the second spacecraft is mated with the first spacecraft; wherein the coupling mechanism includes at least one pin configured to extend through the at least one bore of the first spacecraft and the at least one bore of the second spacecraft when aligned and when the coupling mechanism is in the coupled configuration; and wherein the at least one bore of one of the first spacecraft and the second spacecraft extends through the collar, and wherein the at least one bore of the other of the first spacecraft and the second spacecraft extends through structure that defines the channel.