Abstract: 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.

Abstract: 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.

Abstract: A high-linearity linearizer system includes a multi-stage linearizer circuit formed by cascading multiple linearizer circuits. The multi-stage linearizer circuit is configured to pre-distort an input signal to generate a pre-distorted signal. A non-linear high-power amplifier (HPA) having non-linear characteristics is coupled to the multi-stage linearizer circuit and is configured to amplify the pre-distorted signal. Pre-distortion characteristics of the multi-stage linearizer circuit are configured to counter the non-linear characteristics of the non-linear HPA and to compensate a non-linearity of the non-linear HPA to achieve a desired level of linearity.

Abstract: An adaptive linearizer system includes an adaptive linearizer circuit that is configured to pre-distort an input signal based on one or more control signals to generate a pre-distorted signal, and a non-linear high-power amplifier (HPA) having non-linear characteristics that is coupled to the adaptive linearizer circuit. The nonlinear HPA amplifies the pre-distorted signal. The pre-distortion characteristics of the adaptive linearizer circuit provide for countering the non-linear characteristics of the non-linear HPA and compensating a non-linearity of the non-linear HPA.

Abstract: An apparatus for satellite communication may include a reflector configured to redirect electromagnetic energy. Each of multiple feeds may be positioned at a predetermined location with respect to the reflector. A feed-switching mechanism may be configured to selectively activate for use at least one of the multiple feeds. A steering mechanism may be configured to steer the reflector such that a focal point of the reflector approximately coincides with a position of an activated feed of the multiple feeds. The reflector may be mechanically independent of the plurality of feeds and the feed-switching mechanism.

Abstract: An adaptive linearizer system includes an adaptive linearizer circuit that is configured to pre-distort an input signal based on one or more control signals to generate a pre-distorted signal, and a non-linear high-power amplifier (HPA) having non-linear characteristics that is coupled to the adaptive linearizer circuit. The nonlinear HPA amplifies the pre-distorted signal. The pre-distortion characteristics of the adaptive linearizer circuit provide for countering the non-linear characteristics of the non-linear HPA and compensating a non-linearity of the non-linear HPA.

Abstract: A high-linearity linearizer system includes a multi-stage linearizer circuit formed by cascading multiple linearizer circuits. The multi-stage linearizer circuit is configured to pre-distort an input signal to generate a pre-distorted signal. A non-linear high-power amplifier (HPA) having non-linear characteristics is coupled to the multi-stage linearizer circuit and is configured to amplify the pre-distorted signal. Pre-distortion characteristics of the multi-stage linearizer circuit are configured to counter the non-linear characteristics of the non-linear HPA and to compensate a non-linearity of the non-linear HPA to achieve a desired level of linearity.

Abstract: An instrument mounting system for a geosynchronous host satellite provides independent heat rejection capability for a hosted instrument. The system may include an instrument mounting structure that is thermally coupled to a radiator component via heat pipes that may include one or both of rigid and flexible elements. In some embodiments, the system is mounted on the hosting satellite so as to provide satellite components and the hosted instrument with a clear field of view while rejecting heat in one or both of the north and south directions. The system may also provide structural support for components of one or both of the hosted instrument or the hosting satellite.

Abstract: A spacecraft is provided. The spacecraft comprises a plurality of heat generating electrical components. A first thermal radiator panel and a second thermal radiator panel are provided on the spacecraft, each panel being thermally coupled to the heat generating electrical components. Heat pipes are also provided. At least one first heat pipe is externally attached to the first thermal radiator panel and at least one second heat pipe is externally attached to the second thermal radiator panel. The at least one first heat pipe is thermally coupled to the at least one second heat pipe.

Abstract: An apparatus for satellite communication may include a reflector configured to redirect electromagnetic energy. Each of multiple feeds may be positioned at a predetermined location with respect to the reflector. A feed-switching mechanism may be configured to selectively activate for use at least one of the multiple feeds. A steering mechanism may be configured to steer the reflector such that a focal point of the reflector approximately coincides with a position of an activated feed of the multiple feeds. The reflector may be mechanically independent of the plurality of feeds and the feed-switching mechanism.

Abstract: A satellite (50) is disclosed having at least one deployable thermal radiator (64). Once deployed, this thermal radiator (64) may be repositioned. In one embodiment, the deployed thermal radiator (64) may be moved about a first axis (74), about a second axis (76), or both to move the deployed thermal radiator (64) from one deployed position to another deployed position.

Abstract: A spacecraft is provided. The spacecraft comprises a plurality of heat generating electrical components. A first thermal radiator panel and a second thermal radiator panel are provided on the spacecraft, each panel being thermally coupled to the heat generating electrical components. Heat pipes are also provided. At least one first heat pipe is externally attached to the first thermal radiator panel and at least one second heat pipe is externally attached to the second thermal radiator panel. The at least one first heat pipe is thermally coupled to the at least one second heat pipe.

Abstract: A satellite payload structure includes one side that includes at least two equipment mounting panels. Each of the equipment mounting panels are oriented substantially parallel to each other such that when the satellite is deployed, each of the equipment mounting panels are substantially parallel to a vector pointing from the deployed location of the satellite to a point on the earth's surface. The point on the earth's surface is located vertically beneath the satellite such that the vector is substantially normal to the earth's surface.

Abstract: Embodiments of the present invention are directed to a method and an apparatus for preventing interference of geosynchronous satellites due to ground stations with misaligned antennas. In one embodiment, a two-way satellite ground terminal is configured to communicate with a geosynchronous target satellite which transmits a target satellite signal. The ground terminal comprises an antenna which is configured to receive the target satellite signal from the geosynchronous target satellite only if the antenna is oriented toward the geosynchronous target satellite. A transmitter is configured to transmit signals from the ground terminal via the antenna A signal detector is operatively coupled with the antenna and with the transmitter.