Abstract: An adapter arrangement includes a first adapter ring for interfacing with a launch vehicle payload interface ring, a second adapter ring for interfacing with a payload launch vehicle interface ring, and a plurality of vibration isolation devices disposed between and attached to each of the first adapter ring and the second adapter ring. The first adapter ring has a first standard interface with the launch vehicle payload interface ring and the second adapter ring has a second standard interface with the payload launch vehicle interface ring.

Abstract: A spacecraft comprises a first module including a first assembly of components and a second module including a second assembly of components and a thermal radiator. The second module is movable between a stowed position proximate the first module whereat the thermal radiator is only partially operative and a deployed position distant from the first module whereat the thermal radiator means is fully operative for dissipating waste heat to deep space for at least one of the first and second assemblies of components. In one embodiment, the first module includes a housing defining an interior cavity, the second module including a casing so shaped and dimensioned as to be telescopically received within the internal cavity of the first module and the second module being translationally movable along a deploying axis between the stowed position and the deployed position but incapable of mutual rotation about the deploying axis.