A separation device for a spacecraft or launcher comprising a nut divided into at least two nut portions locked to each other by a locking device in a locking position. A releasing device is arranged to switch the locking device from the locking position to a releasing position. The separation device comprises at least two bearing elements arranged between the locking device and the nut. The nut comprises an outer envelope surface which comprises as many indentations as the number of bearing elements and locking surfaces between the indentations. In the locked state each bearing element is jammed between the locking surface and an inner envelope surface of the locking device and in the released state each bearing element is positioned facing the indentations.

This disclosure provides a joint assembly that thermally isolates a warm structure, such as a payload, from a cold structure, such as a cryogenic fuel tank, in a space vehicle while maintaining structural interconnection within the joint assembly. The joint assembly includes a primary joint that is capable of separating, and a secondary joint connected to and adjacent to the primary joint. The secondary joint includes an inflatable annulus structure and one or more restraining members, where separation of the primary joint causes the inflatable annulus structure to be in compression and the one or more restraining members to be in tension.

Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.

A combined launch vehicle and satellite system relates to the satellite combined with the launch vehicle's upper stage to provide a more efficient system that includes tank separation technology which allows the satellite system to shed tanks that have used up all the propellants stored therein. The method separation of the tank set is enabled by using a merman band or pneumatic type of separation system; wherein the three bottom tanks are emptied first during the process, followed by the separation of the emptied tanks herein the fuel is completely filled in the second set of tanks. The first pair of tanks is then separated after the fuel is emptied. Similarly, the plumbing lines are also separated. The separation of the used components is achieved herein and the satellite is ready for orbit insertion.