Abstract: A system and method for generating a satellite commanding procedure includes a computer having a central processing unit and a screen display coupled to the computer. The display has a plurality of object-oriented display indicia. An input device is coupled to the computer and is used for entering a plurality of arguments into the computer. A stub generator operating within the computer receives the arguments and generates a stub. A mission tool kit has a plurality of stored commands. A program memory stores the satellite commanding procedure. The computer associates the stub with the procedure steps and stores the procedure steps in program memory. When the satellite commanding procedure is run or tested, a mediator is used to recognize the stub and recall the procedure steps and arguments associated with the screen indicia.

Abstract: An ESD bleed path for a coaxial cable (10). A disk (20) is provided around a center pin (18) of a SMA connector (12) for a center conductor (22) of the coaxial cable (10) in order to provide a bleed path for a floating center conductor (22). The disk (20), preferably made of carbon loaded with kapton, fits over the center pin (18) of a male portion (14) of the SMA connector (12). The disk (20) is compressed between the male portion (14) of the SMA connector (12) and the female portion (16) of the SMA connector (12). The compression connection provides electrical contact among the connector (12), the disk (20), the center conductor (22) and the outer conductors (23, 25) of the connector (12) and the cable (10). The present invention provides an electrostatic discharge bleed path for the center conductor (22) of the coaxial cable (10).

Abstract: The disclosure describes a method of adjusting a reference level for uplink signal power for use in a dynamic power control system with satellite-based measurements in a satellite communications system. The uplink signal power for a plurality of received uplink signals is measured and combined to determine whether a signal power reference level requires adjustment. The signal powers of a plurality of uplink signals are measured at the satellite and the received signals are validated to ensure the signals are acceptable for use in adjusting the reference level. The valid signals are used to calculate an average signal power of the measured uplink signal powers, with the calculated average being compared to the current value of the reference level. Based on the comparison, the reference level either retains the current value or is reset to an adjusted value.

Abstract: Apparatuses, methods and systems for mesh integration and tension control, mesh retention, and mesh management of mesh-type deployable reflectors. The mesh members are comprised of a plurality of wedge-shaped gore members, each of which are pre-tensioned initially utilizing double-sided tape in a temporary manner prior to final stitching. String-like chord catenary members are positioned in pockets formed on the outer end of the gore members. The mesh member is attached to a ribbed reflector frame structure through a plurality of nodal assembly mechanisms. The nodal assemblies have spring biasing members for tensioning radial and transverse chord members along the reflector surface. A plurality of string-like members positioned in washers on the mesh member are used to maintain a tension field in the mesh member when the reflector is in its collapsed and stowed condition.

Abstract: A terrestrial thermal vacuum system that tests spacecraft by developing a thermal balance having a margin of error of less then 5% and preheats spacecraft prior to terrestrial thermal vacuum testing are disclosed. In operation, working fluid is pumped through a cooling plate that receives heat from the spacecraft and then passes through a heat exchanger where the heat is discarded. The temperature of the working fluid is measured at both the supply and return portions of the cooling plate and the flow rate determined for the fluid. From these measurements an initial heat flow from the spacecraft is determined and an equivalent amount of heat is added back to the spacecraft at the appropriate location. The process is repeated until thermal balance is achieved. Also disclosed is a method for designing the cooling plate used by the above described system.

Abstract: The present invention is directed to a method of and a device for adjusting the concavity of a springback antenna reflector. The method and device of the present invention can be used to adjust the concavity of the springback reflector prior to stowage within a satellite to correct actual or anticipated variations in the desired shape of reflector that are caused by storage of the reflector, fabrication of the reflector, thermal effects on the reflector, and moisture absorption by the material from which the reflector is fabricated. By adjusting the concavity of the reflector to correct the variations in the shape of the reflector, degradation of the performance of the reflector due to distortions in the shape of the reflector may be greatly reduced.

Abstract: A TWT collector has axially-positioned collector stages in which at least one of the stages includes a plurality of annularly-arranged stage segments. The collector enhances electron beam velocity sorting by facilitating a combination of (a) selecting axial electric field distributions with application of selected voltages to the axially-positioned collector stages and (b) selecting radial electric field distributions with application of selected voltages to the annularly-arranged stage segments.

Abstract: An electronic assembly is fabricated by tinning a solder to the electrical bonding pads of a printed circuit board, and applying an adhesive, preferably a filled polyurethane adhesive, to the component that is to be bonded to the printed circuit board. The component is contacted to its bonding location on the printed circuit board, and the electrical contact on the component is contacted to the tinned bonding pads. The assembly is heated in a single solder temperature/time reflow cycle to simultaneously cure the adhesive and solder the electrical contacts to the bonding pads.

Abstract: A compact “T” switch for use in a waveguide communication system switch includes a housing, a rotor, and a motor. The housing includes a pair of ends and an interconnecting sidewall enclosing a cylindrical cavity. One of the housing ends including an entry port, and the sidewall includes a plurality circumferentially spaced exit ports. The rotor is rotatably disposed within the housing cylindrical cavity, and includes an input end having an input port aligned with the housing entry port and an outer surface having a plurality of output ports for alignment with the housing exit ports. The rotor includes a primary or first passage connecting the input port to one of the output ports and further includes at least one secondary passages connecting a pair of the output ports.

Abstract: A DC to DC converter that uses three switching devices and processes power in such a way that it can operate very efficiently. The converter only processes that portion of the input power that is required to provide regulation. In addition, by judiciously selecting magnetic components and turns ratios, the converter can be optimized for narrow input voltage ranges or for wide input voltage ranges. The converter operates in such a way that it can add or subtract energy on the primary side of the converter to achieve regulation.

Abstract: An apparatus for limiting intermediate frequency variation in a multiple conversion phase locked loop includes a reference oscillator and a voltage controlled oscillator (VCO). The reference oscillator generates a first reference frequency, while the VCO generates an output frequency. The output frequency is divided by a first VCO divider and mixed with the first reference frequency to generate a first intermediate frequency. A second VCO divider also divides the output frequency and mixes it with the first intermediate frequency to generate a second intermediate frequency, which is filtered and used to control the VCO. An algorithm processor generates the division constants of the first and second VCO dividers as a function of the reference frequency and the output frequency to limit intermediate frequency variation.

Abstract: A laser crosslink attitude determination system using the payload laser crosslinks as the principal attitude sensor and thereby eliminating the need for additional high-cost, high performance dedicated celestial body or inertial sensors to provide attitude information. The method and system establishes optical crosslinks among orbiting spacecraft for attitude control by performing a series of deterministic scans. The need for separate dedicated attitude sensors is minimized or eliminated by increasing the acquisition field of uncertainty and/or reducing the crosslink acquisition field of view.

Abstract: The focus angle of a search light mounted on a helicopter or other platform is narrowed or widened by rotating a bidirectional focus control cam in a clockwise or counterclockwise direction as selected by a manually operated three-position control switch which determines the rotational direction of a DC motor driving the bidirectional focus control cam. The DC motor has first and second terminals which are selectively connected to either a DC power source or ground by a double-pole, single throw dual relay which reverses the polarity and thus the direction of rotation of the DC motor. The dual relay is connected by the same single wire interface currently in use to the manually operated control switch, which manually operated control switch is within a control box located in the helicopter.

Abstract: A deployable segmented dish-like reflector includes a main body with one or more additional reflector segments. Each reflector segment is connected to the main body with one or more link members, such that the entire reflector may be stowed into a compact volume and subsequently deployed to its operational configuration. The system provides a mechanism for stowing the at least one segment in an overlapping manner, substantially parallel to the main body, in order to minimize its stowage volume. The linkage arrangement allows the at least one reflector segment to be deployed from the stowed position to a desired final position. Rate control and deployment coordination may be introduced in a variety of ways.

Abstract: A spacecraft (10) having a main body portion (12) comprising a payload module (14), a bus module (16) and an antenna potion (17), a first solar wing (24) having a first side (30) and a second side (32), a second solar wing (26) having a first side (36) and a second side (38), a first battery pack (50) secured to the first solar wing and a second battery pack (52) secured to the second solar wing.

Abstract: Spacecraft cost, volume and weight are reduced with gyroscope calibration methods that can be effected with structures (e.g., a single-axis Sun sensor and a wheel system) which are typically carried by spacecraft for other purposes. In a method embodiment, these methods include an initial step 1) of calibrating a selected gyroscope and subsequent steps for each uncalibrated gyroscope of: 2) slewing the spacecraft by a slew angle and controlling attitude with the uncalibrated gyroscope for a selected time period to thereby couple its drift into the inertial axis of a calibrated gyroscope, 3) backslewing the spacecraft to return the calibrated gyroscope to its inertial axis, and 4) measuring an error angle generated by the uncalibrated gyroscope during the selected time period (e.g., with a Sun sensor or with the calibrated gyroscope).

Abstract: The present invention is directed to improved coupling mechanisms for TE.sub.011 and TE.sub.01.delta. mode resonators. In one embodiment, the coupling mechanism provides an adjustable connection for transferring electromagnetic energy from a first resonator to a second resonator. Once the resonators are coupled, the coupling mechanism is adapted to allow adjustment of the magnitude and/or the phase of the electromagnetic energy while preserving the electromagnetic connection between the resonators. In another embodiment, the coupling mechanism provides a connection of the resonators using a waveguide. By varying the connection of the resonators with respect to the waveguide, positive relative coupling and/or negative relative coupling of the electromagnetic energy transferred between the waveguide and the resonators is provided.

Abstract: An energy storage cell includes a vessel having a wall with a pair of oppositely disposed apertures therethrough, and an electrochemical cell, such as a nickel-hydrogen cell, within the vessel interior. A central core extends through the oppositely disposed apertures and performs all basic electrical, compressive support, and thermal removal functions for the energy storage cell. The central core includes electrical interconnects for the plate sets of the electrochemical cell, axial compression loading supports for the plate sets, and a heat pipe or other structure for removing heat from the interior of the vessel.

Abstract: A system and method for determining the location of a source of interference for a communications satellite. The system has an antenna array located on the earth facing panel of the communications satellite. The method and system determine the direction of a source of interference relative to the satellite's own coordinate system. The angle of arrival of the interference signal is determined with respect to the horizontal and vertical baselines of the coordinate system and by comparing the outputs of the appropriate antennas in the antenna array.

Abstract: A black film useful in thermal control has a matrix with 100 parts by weight of a polymer, and from about 1 to about 6 parts by weight of an electrically conductive carbon pigment having a porous, sponge-like structure dispersed through the matrix. The film may be a freestanding film, typically about 0.001 to about 0.003 inches thick, used as a radome. The film may instead be a liquid paint or a solid paint applied to a surface.