Support and load alleviation system for space vehicles

Claim 1

In a cradle system for supporting a space vehicle in a cargo bay of a reusable launch vehicle during launch and for deploying the space vehicle in outer space through a top bay opening, said cradle having a generally tubular configuration consisting of two longitudinally divided sections, hinged together so that an upper section can be rotated to deploy a space vehicle secured thereto, the lower section being secured to the space launch vehicle said cradle section constructed as closed box structures including inner and outer skins, radial frames and integrally machined edge closing beams; the improvement wherein said lower section is secured to said launch vehicle by six point support system comprising: two lateral support fittings attached to the lower section at the lower centerline of said lower section, at the forward and aft edges, each lateral support fitting including a downwardly extending tongue fitting within a corresponding socket in the cargo bay surface, whereby loads in the transverse direction are reacted; two aft attachment fittings located at the aft upper edges of said lower section include outwardly extending pins which engage corresponding sockets in the cargo bay surface, whereby loads in vertical and longitudinal directions are reacted; and two forward attachment fittings located at the upper, forward edge of said lower section including trunnions mounting outwardly extending pins adapted to engage corresponding sockets in the cargo bay surface, said trunnions being hingedly mounted on said lower section for rotation about a line substantially perpendicular to the cradle centerline, said forward attachment fitting further including liquid spring means connected between said trunnions and said lower section to restrain said rotation; whereby loads in the vertical direction are reacted.