Abstract: A perimeter truss structure (103) that may be used, for example, to support an RF reflector may include multiple deployed bays (200) arranged in a ring. Each deployed bay (200) includes a first upper horizontal support member (726) attached to a first vertical support member (706) and collapsible on a first joint (728) translating on a second vertical support member (708), as well as a first lower horizontal support member (714) attached to the second vertical support member (708) and collapsible on a second joint (744) translating on the first vertical support member (706). The first and second vertical support members (706, 708) define a ring inside (122) and a ring outside (124). The first upper horizontal support member (712) is disposed on one ring side (e.g., the outside), while the first lower horizontal support member (714) is disposed on the opposite ring side.

Abstract: A spacecraft having a movable structure which is held in a preselected location by a holding mechanism substantially free of microdynamic noise. The holding mechanism comprises two mechanical members in physical contact with each other and movable with respect to each other. The unintentional movement of the two mechanical members with respect to each other generates microdynamic noise. The two mechanical members are secured together to provide joinder of the two mechanical members when the movable structure is located in the preselected position to prevent long-term unintentional movement between the two mechanical members.

Abstract: A deployable phased-array-of-reflectors antenna includes individual reflectors and feed arrays. Each feed array is disposed above a corresponding individual reflector. The individual reflector antennas are preferably disposed adjacent to one another (e.g., on a hexagonal lattice) to form a phased array antenna using the individual reflectors antennas as elements. Phase and amplitude control electronics are coupled to each reflector antenna to provide steering for the signal energy coupled between the reflectors and the feed arrays. Switching electronics are coupled to the feed arrays and selectively activate and deactivate beam forming clusters of feeds in the feed arrays. A method for generating a steerable antenna pattern couples signal energy through a beamforming section to form steered signal energy. Next, the method couples the steered signal energy between a phased array of reflector antennas.

Abstract: Apparatus for sensing the weight of an object and providing a digital representation of a weight range within which the sensed weight falls, and apparatus for controlling the deployment of a vehicular air bag in accordance with the weight of a passenger seated in a vehicle seat adjacent the air bag. A number of two-position switches 28 normally assume a first position and are responsive to a force of at least a predetermined amount to assume a second position. The first position represents a first weight range, and the second position represents a second weight range. A support surface 58, 60 overlies the switches to support an object to be weighed. A decoding circuit 30 monitors the positions of each of the two-position switches and provides a digital representation of the weight range within which the weight of the object falls. In the vehicular air bag system, a number of groups of the two-position switches 28 are mounted in a passenger seat 52 adjacent the air bag.

Abstract: The reflective mesh material that forms the reflector in a foldable perimeter truss antenna is remotely adjusted to shape using remotely controlled stepper motors carried on the truss. Connected to the end of the catenaries, which shape and support the pliant reflective mesh material on the truss, the stepper motors adjust the tension on the catenaries and thereby change its shape. An RF receiver and electronic controller associated with each stepper motor receives the tension command information from a remote source and controls the stepper motor in accordance with that information.

Abstract: A new combination is formed of a deployable solar array and a deployable perimeter truss reflector within a single structure, defining a deployable perimeter truss reflector and solar array combination. In that combination the pliant reflective mesh, which serves as the RF reflector, is located at one circular end of the perimeter truss and the solar array is located at the other end. The solar array is formed with photovoltaic cells formed on both sides of a pliant film base. The photovoltaic cells are exposed to sunlight, either directly, or through the mesh, which is eighty percent porous to sunlight. Constructed in deployed form, for storage the truss contracts to the conventional non-deployed condition of a barrel-like configuration; and both the pliant reflective mesh that forms the reflector and the pliant base supporting the photovoltaic cells become tucked in place inside opposite ends of the barrel.

Abstract: A deployable reflector having an umbrella-like structure in which a plurality of tubular parabolically curved ribs are connected end-wise to a central hub by associated strain energy hinges, which are flexible and spring-like in characteristic, creating a spring force when stressed. A thin pliant metal coated film material is shaped for expansion into a parabolic shape serves as the reflective surface. Rib anchors, suitably radially extending pockets, attached to the backside of the material receive the ribs that radially extend from the hub. When stowed and restrained, such as by a cable, the curved ribs are all held down, collapsing the parabolic shape of the material, and stressing the hinges, which produce a counter-biasing force. When the restraining force is released to deploy the reflector, the biasing force created in the spring-like flexible hinges automatically pivots the ribs outwardly, pulling the material into its parabolic shape.

Abstract: A deployable perimeter truss reflector is capable of achieving a hitherto unobtainable thirty to one ratio in size between its size in the deployed condition and the stowed condition. The improved truss reflector structure is characterized by deployable spars that are attached to and extend from a basic frame structure to the truss. When deployed the spars are positioned outwardly and away from the basic frame of the truss, carrying the catenaries, and, the latter carrying the reflective surface into position at an end of the truss cylindrical truss. New catenary systems, deployment mechanisms, basic truss structures and cable management systems are also described.

Abstract: A damped latch mechanism 116 is provided for a telescoping structure 10 including an inner tubular member 114 slidingly received within an outer tubular member 112. A first latch member 122 is coupled within the one tubular member 114 and a second latch member 126 is coupled to the other tubular member 114 so as to selectively interfere with the first latch member 122 to prevent the inner tubular member 114 from moving in an axial first direction relative to the outer tubular member 112. A fluid chamber 134 is provided on one of the first and second latch members 122, 126 opposite the other of the first and second latch members 122, 126. A magneto-rheological fluid 136 is disposed within the fluid chamber 134 to absorb shock between the first and second latch members 122, 126.

Abstract: A multi-focus reflector antenna for providing a plurality of antenna patterns from a single reflector structure eliminates the need for multiple reflector antennas on a single spacecraft. The multi-focus reflector antenna includes a plurality of at least partially overlapping reflecting structures on a single support structure, each reflecting structure having a focal point and a focal axis. A plurality of RF signals radiate from the focal points, at least one of which passes through at least one of the plurality of reflecting structures and is incident upon another of the plurality of reflecting structures. The plurality of reflecting structures then direct the plurality of RF signals along the plurality of focal axis and generate a plurality of antenna patterns. The multi-focus reflector has applications in communications systems and more particularly, in satellite voice and data communications, and other RF type signals.