Variable angle latching mechanism for spacecraft

Details Variable angle latching mechanism for spacecraft Variable angle latching mechanism for spacecraft

1993-04-26

1995-03-28

Barefoot, Galen L.

Aeronautics and astronautics

Spacecraft

With payload accommodation

292113, 292219, 29234118, B64G 144

Patent

active

054009871

ABSTRACT:
A variable angle latching mechanism is provided which readily permits adjustment of the deployment angle of a solar array mechanism or other spacecraft deployable. Latch engagement is possible over a wide angular range with virtually zero backlash. In one embodiment a movable portion (20) of the latching mechanism is pivotally mounted to a stationary portion (26) of the latching mechanism and carries a catch element (10) that is adapted to move into latching engagement with a latch element (30) pivotally mounted on the stationary element. The latch element is linearly positioned on the movable portion by a single shim element(30) to thereby establish the angle of deployment of the movable member and thus the deployable. The angle of deployment of the mechanism is set at assembly by selection of shim thickness. In a second embodiment of the invention, the catch arm is an integral part of a slider which is linearly positioned by a motor. The motor may be controlled from an earth station and thereby permits adjustment of the deployment angle after deployment in space.

REFERENCES:
patent: 1229709 (1917-06-01), Brinckerhaff
patent: 4538843 (1985-09-01), Harris
patent: 4880188 (1989-11-01), Roth et al.
patent: 4884464 (1989-12-01), Grattarola
patent: 5319905 (1994-06-01), Szirtes

Affiliated with

Also associated with

Rating

Variable angle latching mechanism for spacecraft does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Variable angle latching mechanism for spacecraft, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Variable angle latching mechanism for spacecraft will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-2245406