Westinghouse Electric Corporation

United States of America As Represented by the Secretary of the Air Force

Dale R Logan

Wayne B Lloyd

Ronald W Minarik

John J Buckley

Craig D Walrath

Peggy J Sowell

William H Renwick

Jonathan B Hammer

Robert J Bernhard

A laser-based target discriminator system for discriminating desired objects from other objects and clutter in an image scene is disclosed. The system is operative to scan a pulsed laser beam a plurality of times across an image area, the scans covering different juxtaposed strip portions of the image area. Range differential signals are derived from the sensed information of successive laser pulsed echoes of each scan corresponding to the image elements thereof. From the range differential signalling, a binary image map of the image area is generated and converted into a second topological image map having index codes which are derived from predetermined groupings of the binary values of the first image map. Clusters of contiguous image elements are identified from the second image map based on the derived codes of the indices thereof. Desired clusters may be discriminated from the identified clusters based on measured predefined parameters thereof. More specifically, predetermined cluster parameters of at least one known object may be stored in the discriminator system for correlation with the measured parameters of the identified clusters to discriminate the cluster of clusters corresponding to the known object. The position and orientation of the desired object may also be determined by the measured predefined parameters of the clusters and the correlation process associated therewith.

Laser-based target discriminator

An improved heliostat device for an electrooptical system in which a mirror is gimbaled in two axes for line-of-sight direction and stabilization. A half angle drive system is connected to the mirror for controlling azimuth rotation of the mirror relative to the stable body from which the mirror is mounted. The half angle drive system comprises a N-2N-speed synchro transmitter-receiver pair, with the N-speed synchro control transmitter mounted on the stable body axis, and the 2N-speed control receiver mounted on the mirror axis. This synchro transmitter-receiver pair is operable with a null error signal controlling mirror drive such that the angular rotation of the mirror is one-half that of the angular rotation of the stable body.

Half angle mechanism for a heliostat

A two axis gimbal set for a pod mounted electro-optical system wherein the azimuth gimbal is supported by the elevation gimbal which in turn is supported between a pair of spaced supporting arms of a base by bearings, one of which has a circular opening therein through which the line-of-sight travels from the optical system to a movable mirror. An inertial dampener is attached to the mirror shaft for reducing effects of vibration on the line-of-sight.

Inertially dampened heliostat assembly

An autoalignment system for a laser having a pair of reflector assemblies capable of providing six degrees of freedom of movement to the reflector element formed as part of each of the reflector assemblies. Each reflector assembly is made up of a reflector unit, a gimbal knuckle joint and a translator mechanism. The interconnection between the reflector unit and the gimbal knuckle joint provides for two degrees of freedom while the translator mechanism and its interconnection with the gimbal knuckle joint provides the additional four degrees of freedom. Cooling of the reflector elements is accomplished by way of a coolant system which is incorporated within the autoalignment system of the laser, while motivation of the autoalignment system is in the form of a plurality of drivers operably connected to the various elements of the reflector assembly. During utilization of the system in a vibrational environment, the autoalignment system maintains the correct relationship between the reflecting elements of the laser as well as providing sufficient cooling thereof.

Laser autoalignment system

Vibration isolated sensor apparatus with minimized air stream obstruction for external mounting on an aircraft. An elongated multi-gimbaled sensor assembly disposed within a cylindrical pod housing for extension along a longitudinal axis of an aircraft is resiliently supported for vibration isolation by a circumferential array of cantilevered longitudinally-extending leaf springs. By actuation of crank arms at the supported ends of the leaf springs, the direction and extent of such resilient support can be made to match g forces created by maneuvering of the aircraft, thereby maintaining minimal radial-wise spring travel clearance-way and minimal transverse section size.

Growing community of inventors

Bowie, MD, United States of America

Dale R Logan