Lockheed Martin Corporation

Bronson Murray

James Paul Foley

Spencer Keith Connor

Douglas Vernon McKinnon

Jay H Ambrose

Joseph Charles Munder

Clement Alphonse Berard, Jr

Alan Ralph Cherrette

Fred Manfred Weiss

Thomas MacKenzie Stuart

A panel assembly for use with a spacecraft includes a payload, a radiator panel and a heat pipe. The payload is configured to generate waste heat during operation. The radiator panel is spaced apart from the payload and is configured to dissipate waste heat. The heat pipe is coupled to the payload and the radiator panel. The heat pipe includes a compliant portion to permit the radiator panel to move relative to the payload. Further the heat pipe is configured to transfer waste heat from the payload to the radiator panel.

Heat transfer assemblies with compliant heat pipes

A hosted multi-reflector antenna system includes a primary reflector, a subreflector, an aperture, a feed structure and an anti-jam housing. The feed structure includes an electronically steered antenna (ESA). The subreflector directs a reflected beam between a primary reflector and an ESA, and the anti-jam housing encloses the subreflector and the ESA. The antenna system is thermo-elastically decoupled and thermally self-sufficient, accommodates thermal dissipation of the feed structure, and can maintain a precise antenna alignment.

Hosted, compact, large-aperture, multi-reflector antenna system deployable with high-dissipation feed

An array antenna including: a frame having a two-dimensional array of a plurality of openings; an electromagnetically radiating tile disposed in each opening; and mounting means for holding at least one tile in a corresponding opening of the frame, each of the mounting means comprising at least two biasing members, each biasing member exerting a biasing force on the tile relative to the frame. Preferably, each biasing member is a leaf spring having first and second ends attached to the frame and a bowed section attached to the tile. Furthermore, it is preferred that each biasing member further have a way to vary the biasing force with temperature, such as fabricating the bow portion from a first and second material, each having a different coefficient of thermal expansion. Also provided is a spacecraft which utilizes the array antenna of the present invention.

Active array antenna with flexible membrane elements and tensioning arrangement

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

A spacecraft of a set of spacecraft has an antenna support frame defining square apertures, which are the same size in all spacecraft of the set of spacecraft. The set also includes a plurality of radiating tiles for various operating frequencies. The tiles all have the same dimensions, so that any combination of tiles may be mounted in the apertures of the frames of any spacecraft to form antenna arrays of various sizes, depending upon the customer's requirements. Each tile includes plural beamformers and power amplifiers, and remotely controllable phase shifters and level controls, for ready reconfiguration of the antennas while the spacecraft is in operation. The preferred dimension of each radiating tile is a one-foot square.

Spacecraft with modular communication payload

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.

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Freehold, NJ, United States of America

Bronson Murray