Richard W Lingley

40449742, Aug 30, 1977

Aug 23, 1976

5/716735

Richard C. Lingley - San Diego CA
Milburn R. Smith - La Mesa CA

General Dynamics Corporation - San Diego CA

B64D 900

244161

A cradle for supporting a space vehicle such as an upper stage in a reusable launch vehicle (such as a space shuttle orbiter) cargo bay. The cradle includes means for supporting the space vehicle and any satellite attached thereto against launch loads and against abort landing loads. The cradle consists of two radial sections of a tube which, when closed, surrounds the space vehicle. One section is secured within the cargo bay. The second section is latched to the first edge of the second section and is hinged along the second edge. When the cargo bay doors are opened, the space vehicle is deployed by unlatching said latch and activating a first actuation means to rotate the second section about the hinge to move the second section outwardly of the cargo bay. A deployment probe connects the space vehicle to the second section. When the first section is fully rotated, a second actuation means rotates the deployment probe to move the space vehicle from the position in contact with the inner surface of the second section to an extended position extending away from the orbitor.

40822400, Apr 4, 1978

Aug 23, 1976

5/716419

John H. Heathman - San Diego CA
Richard C. Lingley - San Diego CA

General Dynamics Corporation - San Diego CA

B64G 100

244158

A cradle for supporting a space vehicle such as an upper stage in a reusable launch vehicle (such as a space shuttle orbiter) cargo bay. The cradle includes means for supporting the space vehicle and any satellite attached thereto against launch loads and against abort landing loads. The cradle consists of two radial sections of a tube which, when closed, surrounds the space vehicle. One section is secured within the cargo bay. The second section is latched to the first edge of the second section and is hinged along the second edge. When the cargo bay doors are opened, the space vehicle is deployed by unlatching said latch and activating a first actuation means to rotate the second section about the hinge to move the second section outwardly of the cargo bay. A deployment probe connects the space vehicle to the second section. When the first section is fully rotated, a second actuation means rotates the deployment probe to move the space vehicle from the position in contact with the inner surface of the second section to an extended position extending away from the orbiter.