Abstract: A low cost millimeter wave receiver and method for operating same is disclosed. In one embodiment, the method comprises receiving the first signal, converting the first signal of the first bandwidth into an intermediate frequency band, splitting the converted first signal into N of intermediate signals, each having a bandwidth less than the digital processor bandwidth, wherein N is an integer greater than one, downconverting each of the N intermediate signals to the second frequency band, processing the downconverted plurality of signals with the digital processor to generate N processed signals, upconverting each of the N processed signals to the intermediate frequency band, converting the upconverted signals to the third frequency band, and transmitting the converted signals.

Abstract: A low cost millimeter wave receiver and method for operating same is disclosed. In one embodiment, the method comprises receiving the first signal, converting the first signal of the first bandwidth into an intermediate frequency band, splitting the converted first signal into N of intermediate signals, each having a bandwidth less than the digital processor bandwidth, wherein N is an integer greater than one, downconverting each of the N intermediate signals to the second frequency band, processing the downconverted plurality of signals with the digital processor to generate N processed signals, upconverting each of the N processed signals to the intermediate frequency band, converting the upconverted signals to the third frequency band, and transmitting the converted signals.

Abstract: A system for single wire secondary distribution comprising a spacecraft platform; a central bus interface unit coupled to the spacecraft platform; a payload unit coupled to the central bus interface unit; and a centralized power supply for powering the central bus interface unit and the payload unit; wherein the spacecraft platform provides a command to the central bus interface unit; wherein the central bus interface unit interrupts the power to the payload unit in a manner corresponding to the commands received by the central bus interface unit; wherein the payload unit decodes the interruption to the power and executes the command from the spacecraft platform.

Abstract: A system for single wire secondary distribution comprising a spacecraft platform; a central bus interface unit coupled to the spacecraft platform; a payload unit coupled to the central bus interface unit; and a centralized power supply for powering the central bus interface unit and the payload unit; wherein the spacecraft platform provides a command to the central bus interface unit; wherein the central bus interface unit interrupts the power to the payload unit in a manner corresponding to the commands received by the central bus interface unit; wherein the payload unit decodes the interruption to the power and executes the command from the spacecraft platform.

Abstract: A system for single wire secondary distribution comprising a spacecraft platform; a central bus interface unit coupled to the spacecraft platform; a payload unit coupled to the central bus interface unit; and a centralized power supply for powering the central bus interface unit and the payload unit; wherein the spacecraft platform provides a command to the central bus interface unit; wherein the central bus interface unit interrupts the power to the payload unit in a manner corresponding to the commands received by the central bus interface unit; wherein the payload unit decodes the interruption to the power and executes the command from the spacecraft platform.

Abstract: A power control system for a satellite receiving radio-frequency signals includes a traveling wave tube amplifier system and corresponding traveling wave tube. An anode voltage of the traveling wave tube amplifier system is used to modulate or saturate the current of the electron beam of the traveling wave tube so that the output power of the traveling wave tube amplifier system, from the saturated electron beam, is proportional to a waveform envelope of the radio-frequency signals.

Abstract: A power system for a satellite includes a high power amplifier that has a control input. The high power amplifier has a minimum effective isotropic radiated power. A controller is coupled to the control input. The controller generates a control signal to adjust a saturated power output of the high power amplifier to the minimum effective isotropic radiated power.

Abstract: An apparatuses and methods for phase matching power combined signals are described. A typical apparatus includes at least a waveguide portion in at least a first branch conducting a first electromagnetic signal of a combiner, the waveguide portion having an effective size and a thermal control system effecting a temperature change in the waveguide portion to alter the effective size. Altering the effective size of the waveguide portion adjusts phase matching between the first electromagnetic signal of the first branch and at least a second electromagnetic signal of a second branch of the combiner. High thermal expansion coefficient materials including silver plated polyetherimide can be used. In addition, composite materials having anisotropic thermal expansion may be used.

Abstract: A power control system (12) for a satellite (10 includes a high power amplifier circuit (28) that receives a saturated power output adjustment signal. The amplifier circuit (28) includes a programmable circuit (70). An electronic power conditioner (56) is coupled to the programmable circuit (70) and is configured to reset an operating set-point of said high power amplifier circuit (28) in response to the saturated power output adjustment signal. A high power amplifier (46) has a variable output power range and amplifies a received signal in response to change in the operating set-point. A channel amplifier (44) is coupled to the programmable circuit (70) and is configured to gain offset the received signal in response to change in the operating set-point.

Abstract: A power control system for a satellite receiving radio-frequency signals includes a digital processor and a traveling wave tube amplifier system and corresponding traveling wave tube. An anode voltage of the traveling wave tube amplifier system is used to modulate or saturate the current of the electron beam of the traveling wave tube so that the output power of the traveling wave tube amplifier system, from the saturated electron beam, is proportional to a waveform envelope of the radio-frequency signals. The digital processor controls anode and RF input signal amplitudes to the traveling wave tube and predicts necessary corrections.

Abstract: A power control system (12) for a satellite (10 includes a high power amplifier circuit (28) that receives a saturated power output adjustment signal. The amplifier circuit (28) includes a programmable circuit (70). An electronic power conditioner (56) is coupled to the programmable circuit (70) and is configured to reset an operating set-point of said high power amplifier circuit (28) in response to the saturated power output adjustment signal. A high power amplifier (46) has a variable output power range and amplifies a received signal in response to change in the operating set-point. A channel amplifier (44) is coupled to the programmable circuit (70) and is configured to gain offset the received signal in response to change in the operating set-point.

Abstract: A power system for a satellite includes a high power amplifier that has a control input. The high power amplifier has a minimum effective isotropic radiated power. A controller is coupled to the control input. The controller generates a control signal to adjust a saturated power output of the high power amplifier to the minimum effective isotropic radiated power.

Abstract: A microwave tube system for use with a spacecraft telecommunication system is provided. The system includes a traveling wave tube subsystem, a high voltage converter subsystem, and a low voltage converter subsystem. The traveling wave tube subsystem includes a plurality of traveling wave tubes. The high voltage converter subsystem powers the traveling wave tube subsystem. The high voltage converter subsystem includes a plurality of high voltage converter members that are paired with the traveling wave tubes on a one-to-one basis. The low voltage converter subsystem is a central power conditioner subsystem including a plurality of low voltage power conditioners that are connected in parallel to one another. A common power output of the central power conditioner subsystem is received by the high voltage converter members which in turn power the traveling wave tubes that are paired with the high voltage converters.

Abstract: A microwave tube system for use with a spacecraft telecommunication system is provided. The system includes a traveling wave tube subsystem, a high voltage converter subsystem, and a low voltage converter subsystem. The traveling wave tube subsystem includes a plurality of traveling wave tubes. The high voltage converter subsystem powers the traveling wave tube subsystem. The high voltage converter subsystem includes a plurality of high voltage converter members that are paired with the traveling wave tubes on a one-to-one basis. The low voltage converter subsystem is a central power conditioner subsystem including a plurality of low voltage power conditioners that are connected in parallel to one another. A common power output of the central power conditioner subsystem is received by the high voltage converter members which in turn power the traveling wave tubes that are paired with the high voltage converters.

Abstract: A method and apparatus are disclosed for controlling the operation of a synchronous rectifier used in power conversion circuitry. The disclosed method and apparatus senses the voltage across the synchronous rectifier, and turns the synchronous rectifier OFF when the voltage across the rectifier is about to change direction. Preferably, the synchronous rectifier is commanded OFF at the approximate instant when the voltage across the rectifier reaches approximately zero, which also corresponds to a current of approximately zero. Accordingly, currents are prevented from flowing in the reverse direction in the synchronous rectifier. This results in approximately zero voltage and zero current switching when the rectifier is turned OFF, thereby minimizing switching losses.

Abstract: A fully regulated multiple source power bus subsystem for a satellite having at least a solar panel array and a battery providing unregulated sources of electrical power. The battery and solar panel array are connected to one or more multiple source bus regulators to produce a fully regulated bus output at one or more preselected voltages. Each multiple source bus regulator automatically switches between the battery and solar panel array and may produce either a positive or a negative bus voltage. A battery charge controller controls the charging of the battery when the output voltage of the solar panel array is greater than the output voltage of the battery.

Abstract: A synchronized switching system for use in a power converter. A pulse-width modulation controller is provided to alternately turn on and off a switching device and control the on/off duty cycle. When the switching device is turned off, initial commutating or flyback current from an inductor is conducted by a protective diode connected to ground. The diode is paralleled by a more efficient secondary switching device that is synchronized to conduct during the nonconduction period of a main switching device. A sense winding is added on the inductor for synchronizing the secondary switching device. A digital logic circuit controls the conduction time of the secondary switching device based on signals from a pulse-width modulation controller and from the sense winding of the inductor. After the main switching device has been conducting for the required time, the pulse-width modulation controller turns it off.

Abstract: A leakage regulator for use with switching power supplies which include a field effect transistor (FET) is disclosed. The leakage regulator comprises a bias circuit coupled in a feedback arrangement with the FET to provide a self-generated bias voltage. The bias circuit includes a current transformer coupled to receive a drain-source leakage current. A bias voltage is generated from the transformed leakage current and this bias voltage is applied to the FET gate to help decrease the leakage current.