US 5,400,987 AGranted

Variable angle latching mechanism for spacecraft

AssigneeHughes Aircraft Company

InventorJohn Ziavras

Life of this patent

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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.

Claims7

Dependent claims

A variable angle latching mechanism comprising a stationary portion and a movable portion, means pivotally mounting said movable portion to said stationary portion about a mechanism pivot axis,

a latch element pivotally mounted to said stationary portion about a latch pivot axis, spring means for biasing said latch element about said latch pivot axis toward a latched position, said latch element having an inner latch surface which is a radius concentric with said latch pivot axis,
said stationary portion having a first stop surface which is a radius concentric with said latch pivot axis,
a catch element adapted to be mounted to the movable portion of said latching mechanism, said catch element including a catch pin movable therewith and defining a catch pin axis, said catch element having a second stop surface which is a radius concentric with said catch pin axis,
said latch element having an outer surface in the path of travel of said catch pin and effective upon engagement by said catch pin to cause said latch element to pivot out of the path of travel of said catch pin to permit said second stop surface to engage said first stop surface, whereupon said latch element returns to said latched position capturing said catch pin against said inner surface of said latch element,
means for adjusting the location of said catch pin on said movable portion to control the pivotal position of the movable portion at which the catch element captures and secures the catch pin.

2 more elements

Dependencies are inferred from the claim text.

Facts

Application: 08/052,883Filed 26 Apr 1993
Granted: 28 Mar 1995
Term ends: Not estimatedThe source records don’t support an estimate.

Classification9 codes

B64G 1/64
Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles: systems for coupling or separating cosmonautic vehicles or…
B64G 1/2229
For deploying structures between a stowed and deployed state: characterised by the deployment actuating mechanism
B64G 1/443
Using radiation, e.g. deployable solar arrays: photovoltaic cell arrays
B64G 1/641
Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements: interstage or payload connectors