Abstract: An ejection apparatus (19) for spinning and propelling objects (17) for ejection from a spacecraft (11) at a desired velocity and rotational speed. The apparatus includes a launch cradle (23) on which the space object (17) to be ejected rests. The cradle (23) is rotatably supported by a central hub (37) secured to upper end of pneumatic cylinder piston shaft (25). Release mechanisms (29) consisting of a retractable pin (75) and locking lug (72) is utilized to hold the cradle and object to be ejected. The release mechanism (29) has a fixed barrier member (76) which holds the retractable pin (75) in engagement with the locking lug (72) until release by upward movement of the launch cradle (23) beyond the barrier height.

Abstract: FIG. 1 shows the adjustable indicating device (11) that is adapted to be mounted to the plate (13) defining a load compartment. The device has a central housing (23) with two wing structures (25, 27) on each side which support conventional switch means (29, 31) having cantilevered arms (61). Extending through the housing (23) is a movable shaft (43) that is spring biased to a forward extended position and adapted to respond against a load being positioned. The read end of the movable shaft (43) has an adjustable cam means (55) which acts upon the cantilevered arms (61) to cause a switching action upon shifting of the movable shaft (42) by a load.