Components on spacecraft frequently are mounted on flexible isolator devices (damper struts), like the one in U.S. Pat. No. 6,003,849, configured in a hexapod arrangement in U.S. Pat. No. 5,305,981, or some other strut/truss support system. However, when a spacecraft is launched the components are sometimes restrained on a launch retention mechanism for many reasons, including decreasing deflections of the isolation systems beyond design limits. The launch retention mechanism can be an integral part of the isolation struts or a separate supporting structure. Current launch restraints pull the isolator into a fixed latch position away from the isolator""s neutral in-orbit position, known as isolator bias. The bias can present difficulties when precise alignment between the isolator mounted payload and the base structure, to which the isolator is attached, is important for pre-launch preparations. Alignment adjustments between the payload and spacecraft are made on earth, where gravity sags the isolator away from the zero-gravity orientation that it will assume in outer space. This makes accurate payload positioning prior to launch problematic.
A device is included in the isolator strut for locking the isolator in either a zero bias position (the damper is not loaded at either of its two extreme possible positions) or known/predetermined bias position and electronically overcome to unlock the strut. Another mechanical element is included to temporarily unlock the isolator without disturbing the other devices.
Objects, benefits and features of the invention will apparent to one of ordinary skill in the art from the drawing and following description.