Lockheed Martin Corporation

Martin Marietta Corporation

Carl Zeiss Gmbh

James Paul Foley

Bronson Murray

Ernest R Jones

Thomas MacKenzie Stuart

Robert K Dockstader, Jr

Fred Manfred Weiss

An embodiment of the present invention is an apparatus to determine position of an eye that includes: (a) two off-axis, radiation emitter-photodetector pairs, wherein an emitter of a pair is disposed to transmit radiation toward the eye and a photodetector of the pair is disposed to receive radiation reflected by the eye; and (b) a controller that analyzes output from the photodetectors to determine the position of the eye.

Method and apparatus for determining position of an eye

A spacecraft carries a deployable active antenna array panel(s) and a deployable solar array panel(s). In the stowed condition, the antenna array panel(s) is sandwiched between a side of the body of the spacecraft and the solar array panel(s). This stowed state prevents the antenna panels from becoming too cold by radiation, or too hot by insolation, in an intermediate orbit. The outermost solar panel preferably has its active surface facing outward, so that it can generate electricity in the intermediate orbit.

Spacecraft with active antenna array protected against temperature

An array antenna especially adapted for spacecraft use includes a support frame made up of intersecting beams which form an 'eggcrate' of square openings. A plurality of subarrays or radiating tiles are dimensioned to fit within the openings. Distortion of the support frame due to external forces, or due to expansion and contraction of the radiating tiles, is accommodated andor resisted by a four-point mounting arrangement for each tile. Each mounting is located on the center of the sides of the radiating tile, and the corresponding center of the side of the opening in which it fits. Each mounting consists of a thin, flexible mounting beam, extending parallel to the associated support beam, and fastened to the support beam at the ends of the mounting beam. The center of the side of the tile is fastened to the center of the flexible support beam, so expansion and contraction of the tile are compensated by bending of the flexible beam. Mutually opposing external forces acting parallel to the elements of the support frame are resisted by the longitudinal stiffness of the flexible beam and the diagonal stiffness of the tile.

Modular supertile array antenna

A lift vehicle has an elongated support structure affixed to its upper end, with the axis of elongation of the support structure parallel to or coincident with the longitudinal axis of the lift vehicle. The support structure defines a plurality of attachment planes, each of which includes the axis of elongation, which together divide the region about the axis of elongation into N angular sections or regions, each with an included angle of 360.degree./N. A plurality MN of spacecraft are organized into a plurality of M sets or layers, each containing N spacecraft. Each spacecraft defines first and second lateral support planes, skewed relative to each other, which intersect at a line of intersection, is parallel to the axis of elongation when the spacecraft are mounted to the support structure. Two or more spacecraft are mounted in end-to-end position in each angular portion. Each spacecraft stiffens the support structure, so that the stiffened support structure, can sustain the launch forces. Spacecraft of upper layers do not bear on lower layers. Controllable attachments hold the first and second lateral support planes of each spacecraft adjacent to the attachment planes defined by the support structure.

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Yardley, PA, United States of America

James Paul Foley