Abstract: The present invention is generally directed to a system for taking displacement measurements of an object. The invention is realized by various embodiments. In one embodiment, the invention utilizes the Moiré effect to take precise displacement measurements of an object. In this regard, a visible pattern is disposed on an object, and a plurality of photosensors are uniformly spaced apart from the visible pattern. Importantly, the spacing between the photosensors is slightly different than the spacing of lines forming a projection or image of the visible pattern. This allows the invention to utilize the Moiré effect to accurately compute precise displacements or movements of the object. In this respect, electrical signal generated by the photosensor array will embody a repeating envelope pattern resulting from the difference in the pitch of the photosensors and the pitch of the projection or image of the visible pattern.

Abstract: An apparatus for determining the attitude of an orbiting spacecraft includes an optical system for generating an image on a substrate of a body around which the spacecraft is orbiting, an infrared detector positioned on the substrate in the form of a non-cooled two-dimensional array of pixels disposed in a spaced relationship forming rows and columns, the rows extending in a first direction, and the columns extending in a second direction perpendicular to the first direction, a scanner and an addressing controller for the scanner, the controller and the scanner cooperating to scan the pixels along a predetermined scan path which zig-zags between adjacent rows and columns of pixels, and a computation circuit responsive to the succession of pixel output signals along the scan path to calculate pitch and roll angle changes of the spacecraft according to changes in the image of the orbited body in the first and second direction.

Abstract: Described is a testing system which has a target point light source (12), a tracking light source (18) and therebetween a projection wall (24). Associated with the target point light source (12) is a two-axis deflection device (28) which is connected together with a target point computer (14). Associated with the tracking light source (18) is a two-axis scanner device (30) which is connected together with a tracking computer (20). Provided between the tracking light source (18) and the two-axis scanner device (30) is a beam splitter (32) with which a sensor device (42) is associated.

Abstract: A programmable optical system that dynamically corrects or induces aberrations into the optical path of a missile seeker. The system is dynamic in that the amount and type of aberration may be changed while the missile is in flight. The dynamic correction is accomplished by means of deformations applied to a low-mass mirror or mirrors in the optical path of the missile seeker. The missile includes an aspheric dome, and the optical system is dynamically compensated for aberrations introduced by the dome as the seeker system is moved through the field of regard.

Abstract: A photoconductive detector (3) comprises a single continuous photoconductive strip consisting of two interleaved photoconductive spiral paths (1, 2) separated by much thinner gaps (5, 6). The two spiral paths (1, 2) have the same central point (19). The detector (3) is substantially planar and has the overall shape of roughly a circle (10). A circular band (4) of incident radiation (16) crosses the gaps (5, 6) in a nearly parallel fashion, rather than nearly perpendicularly as in the prior art, lessening unwanted modulations of the detected signal. The terminal (11) to terminal (12) resistance of the detector (3) is increased to the point where, when the photodetector (3) is made of the preferred HgCdTe, simple thermo-electric coolers are sufficient to enable use of the detector (3) as an infrared detector (3) in a heat-seeking missile (17).