Abstract A spacecraft specifically adapted for launch from the space shuttle by means of a cradle having locking and ejection mechanisms mounted therein. The cradle fastens into the payload bay of the space shuttle and returns therewith for reuse in subsequent launches. The spacecraft mounts at three points to the cradle, and the cradle mounts at three points to the shuttle such that a plane through the attachment points passes through the roll axis of the spacecraft at approximately the center of mass thereof. The cradle utilizes the truss structure of the spacecraft to produce the required stiffness by providing a structural tie between the two ends and the bottom of the cradle. At launch, the spacecraft is ejected with both linear and angular momentum, the spin providing gyroscopic stability. The locking mechanisms in the cradle can be remotely controlled to relock the spacecraft to the cradle in the event of an unsuccessful deployment attempt. The spacecraft includes a safety circuit employing acceleration sensing switches which sense spin-up of the spacecraft and prevent premature ignition of the perigee boost motor. The spacecraft has imbedded within its envelope a solid-propellant perigee boost motor surrounded by a liquid-propellant apogee motor. By employing apogee and perigee propulsion stages internal to the spacecraft, the storage length in the space shuttle is minimized, and the geometry and mass characteristics of the spacecraft make for a stable spinning vehicle during both the perigee and apogee boost phases.
A locking device for use in a spacecraft deployment system wherein a cradle in a space shuttle is used for gyroscopically launching the spacecraft and wherein said spacecraft has at least one trunnion adapted for engaging at least one mating surface on the cradle and with said trunnion and said mating surface each having an opening formed therein such that when said spacecraft is mounted in the cradle said openings are in alignment, said locking device comprising: a rack and pinion gear combination; a bolt on one end of said rack; a differential gear arrangement coupled to drive said pinion gear such that said bolt may be moved into and out of said opening in said mating surface and said opening in said trunnion; and first and second reversible motors coupled to drive said differential gear arrangement; whereby either or both motors may drive said bolt so as to either lock or unlock said trunnion and said mating surface.
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Dependent Claim
159 words
A locking device for use in a spacecraft deployment system wherein a cradle in a space shuttle is used for gyroscopically launching the spacecraft and wherein said spacecraft has at least one trunnion adapted for engaging at least one mating surface on the cradle and with said trunnion and said mating surface each having an opening formed therein such that when said spacecraft is mounted in the cradle said openings are in alignment, said locking device comprising: a rack and pinion gear combination; a bolt on one end of said rack; a differential gear arrangement coupled to drive said pinion gear such that said bolt may be moved into and out of said opening in said mating surface and said opening in said trunnion; and first and second reversible motors coupled to drive said differential gear arrangement; whereby either or both motors may drive said bolt so as to either lock or unlock said trunnion and said mating surface.