Abstract: A momentum wheel (14, 142) for compensating for the adverse effects of disturbing torques on stabilized spacecraft is mounted on a base (12, 124) on the spacecraft by three circumferentially spaced supports which include at least two linear actuators (26, 118) that tilt the wheel (14, 142) in any desired direction. One end of each actuator (26) is mounted to a base (38, 154) supporting the wheel by a spherical connection (32, 34, 36) which allows freedom of motion about multiple axes. The other end of each actuator (26) is mounted to the base (12) by either a pair of spaced hinges (22, 24, 46) and a support bracket (18) which is secured to the actuator (26) or a flexible bracket (78). The wheel base (12,124) may also be mounted on the actuators by flexible members (150) which allow tilting of the wheel.

Abstract: An ejection mechanism for imparting an ejection force to substantially constant locus of points on a payload ejected from a spacecraft is disclosed. The ejection mechanism includes a rod having a contact end for abutting contact with the locus of points. The rod is slideably mounted within a housing defining a first aperture from which the rod is driven toward the locus of points. Means are provided for driving the rod toward the payload to eject the payload, and means are provided for securing the housing to the spacecraft. The ejection mechanism also includes means for permitting the contact end of the rod to substantially maintain abutting contact with the locus of points as the rod is driven toward the locus and the payload is ejected from the spacecraft.