Abstract: An adjustable suspension system includes a torsion spring, four Scott-Russell linkages for each wheel of the vehicle, and a worm gear for rotating the torsion spring. At least one of the Scott-Russell linkages for each wheel is responsive to the torsion spring to adjust the ride height of the vehicle while maintaining a substantially constant camber angle for the wheel. In one exemplary method for adjusting the ride height of a vehicle, a dynamic parameter of the vehicle is sensed and, based on the sensed dynamic parameter, the torsion spring is automatically rotated to change the orientation of the Scott-Russell linkages and thereby adjust the ride height of the vehicle. The dynamic parameter may be the speed of the vehicle, the pitch and body roll of the vehicle, or the lateral acceleration of the vehicle. The operation of automatically rotating the torsion spring may be controlled by a microprocessor.

Abstract: A hold down device is provided using a drive knob having a clutch therein which turns a drive shaft for moving a pawl shaft in and out with respect to the drive shaft. A pawl on the end of the pawl shaft is provided with a cam-like surface which engages a cam-like aperture in a pawl receptacle. The pawl shaft has a cam follower which rides within a cam surface in a cam bracket that surrounds the shaft. Under the urging of a spring, the position of the pawl is controlled from its fully extended, unlocked position to a pre-capture position where the pawl is oriented at approximately 45.degree. to an aperture within the pawl receptacle. Insertion of the pawl into the pawl receptacle forces the pawl to rotate an additional 45.degree. against the urging of the spring. After full insertion of the pawl into the receptacle, the pawl rotates back to its 45.degree. position where it is captured therein.

Abstract: An externally accessible, clutching adjustable latching mechanism is provided having an adjusting assembly which permits the latching mechanism to be mounted over a greater range of depths than conventional adjusting mechanisms and controls the amount of pre-load which is possible by the adjustment feature, and protects the aircraft skin from being damaged during such adjustment. An internal clutching mechanism insures the accomplishment of proper, minimum preload on the structures connected by the latching mechanism. The adjusting assembly includes a two-part driver (14a, 14b) and a drive unit (15) which translates rotational movement of the driver into linear movement of a connecting element (10), allowing infinitely small, non-incremental adjustment of the position of the connecting element (10) relative to the structures joined by the mechanism.

Abstract: The present invention relates to a low profile latch for joining two members of an aircraft having a keeper mounted upon one member. The latch is rotatably mounted about a mounting bushing at one end of a pair of compression links whose opposite end pivotally mounts a hook that engages the keeper. Mounted at the pivot point between the hook and compression links is a first part of a two part handle whose second part is attached from the first handle part to a pair of side plates that form a further linkage. The side plates rotate about the mounting bushing, while the opposite ends thereof are connected by control links to the hook. The further linkage formed by the cover, side plates, and control links stabilizes the handle and hook and provides a smooth, controlled movement of the hook as the handle is opened and closed.

Abstract: A low-profile, over-center tension latch assembly is provided which has a handle (20) which opens fully for inspection or adjustment of the assembly while under load, and which may be indexed into a position with a link mechanism (70) in order to act therewith for releasing a keeper engaging member (50) from engagement with a keeper assembly. The handle (70) is locked in a closed position in a manner which secures it to the link mechanism (70) while trapping the keeper engaging member (50) therebetween. The arrangement of the handle (20), keeper engaging member (50) and link mechanism (70) is such as to allow the assembly to be aerodynamically flush mounted with the surface of the structure in which it is installed. Both the handle (20) and the keeper engaging member (50) are pivotally mounted at an end of the link mechanism which is opposite that end which mounts the link mechanism to the aircraft structure.