Abstract: A release device having a multi-segment split spool with a central bore adapted to axially restrain a tensioned member. A tensioned tape is overlappingly wound around the spool segments thereby preventing radial movement of the spool segments. The overlapping winding allows for a low profile housing for the-release device. The multiple segments require less radial motion for release of the tensioned member.

Abstract: A radio frequency (RF) dielectric resonator filter includes at least a first cavity and a second cavity, each cavity being loaded with a dielectric resonator. The first cavity is separated from the second cavity by a common wall, the common wall including a first and second aperture that couple an electromagnetic field between the first cavity and the second cavity. A first externally adjustable tuning screw extends from the second aperture, a portion of the tuning screw being external to the filter. The first aperture is an iris disposed in a central portion of the wall and the second aperture is disposed proximate to a perimeter of the wall. The second aperture has an effective area that is adjustable by the first externally adjustable tuning screw.

Abstract: An antenna reflector includes a laminated structure including a first layer and a second layer, where the first layer has an electrically conductive and electrically reflective front surface and includes a nonwoven metallized fiber matte and the second layer includes an open weave fabric. The laminated structure is acoustically permeable. In some implementations, a laminated structure is formed by co-curing the first layer and the second layer.

Abstract: Single or multi-axis positioning mechanisms are provided that include a caging mechanism that may be actuated without requiring axial displacement of rotational components of the positioning mechanisms. In some multi-axis positioning mechanism implementations, each rotational axis may have an associated caging mechanism that is transitioned between a caged and uncaged state using a common release device. In some implementations, the release device may be a single-use device. In other implementations, the release device may be capable of re-caging the positioning mechanism after uncaging the positioning mechanism.

Abstract: Techniques for performing orbit raising, north-south stationkeeping, east-west stationkeeping, and momentum management with thrusters disposed on a spacecraft are disclosed. The spacecraft includes at least one thruster support mechanism (TSM), including a pointing arrangement and an elongated structural member, the structural member having a long dimension defining a first axis a proximal portion of the structural member is attached to the pointing arrangement each of the thrusters is fixedly coupled with a distal portion of the structural member. The pointing arrangement includes a first, second, and third revolute joint, the first revolute joint being rotatable about the first axis; the third revolute joint being rotatable about a third axis, the third axis being fixed with respect to the spacecraft; and the second revolute joint being rotatable about a second axis, the second axis being orthogonal to each of the first axis and the third axis.

Abstract: A power combining arrangement includes an input divider waveguide and an output combiner waveguide, and a first and second amplifier. The power combining arrangement is configured to amplify RF energy having a characteristic wavelength ?. The first amplifier has a first input electrically coupled with a first output port of the divider waveguide. The second amplifier has a second input electrically coupled with a second output port of the divider waveguide. The first and second output ports are separated by a first distance corresponding to a phase delay Ø1, the first distance being selected substantially independently of the characteristic wavelength. The first amplifier has a first output electrically coupled with a first input port of the combiner waveguide and the second amplifier has a second output electrically coupled with a second input port of the combiner waveguide. The first and second input ports are separated by the first distance.

Abstract: A pliable multilayer blanket configured as a particle radiation shield, the blanket including multiple layers. A first layer of the multiple layers is composed of a first material and a second layer of the multiple layers is composed of a second material, different from the first material, each layer being less than 20 mils thick. At least one of the first material and the second material is a metal or metal alloy having an atomic number (Z) of at least 29.

Abstract: A photovoltaic solar cell assembly includes a bypass diode, a first and a second planar solar cell. Each of the first and the second solar cell includes a front facing side and a rear facing side, each rear facing side including a respective conductive surface, each front facing side including a respective current collector bar, and corresponding grid of metallic lines conductively coupled with the current collector bar. A first terminal of the bypass diode is electrically coupled with the conductive surface of the first solar cell. A second terminal of the bypass diode is electrically coupled with the current collector bar of the second solar cell. Electrical coupling of the bypass diode with the first solar cell and the second solar cell excludes any external wiring or busbar.

Abstract: A spacecraft includes a payload subsystem including a digital channelizer. The digital channelizer provides at least a portion of spacecraft command or telemetry functionality. The spacecraft may optionally also include a telemetry and command (T&C) subsystem, the T&C subsystem including one or more of a command receiver, a command decoder, a telemetry encoder and a telemetry transmitter. The digital channelizer may be communicatively coupled with at least one of the command receiver, the command decoder, the telemetry transmitter and the telemetry encoder.

Abstract: Techniques for testing a component for compatibility with a depressurization profile associated with a launch vehicle payload fairing during ascent are disclosed. A pressure of air or other gas within a pressure vessel containing the component is raised to a first value substantially higher than one atmosphere absolute pressure. The air/gas pressure within the pressure vessel is lowered, by venting into the ambient atmosphere, at a rate simulating or demonstrating margin with respect to the launch vehicle payload fairing depressurization profile. The component is inspected for damage. The component may be a panel including a honeycomb core sandwiched between two faceskins, the panel having a planar area in excess of twenty five square feet.

Abstract: This disclosure provides systems, methods and apparatus for determining beamforming coefficients that correct for pointing errors. In one aspect, a subsystem of a ground station can receive calibration signals from a satellite. The properties of the calibration signals can be measured and used to determine the pointing error of the satellite. Beamforming coefficients based on the pointing error can be provided by the ground station to the satellite.

Abstract: Techniques for deorbiting a satellite include executing an orbit transfer maneuver that transfers the satellite from an operational orbit to an interim orbit. The operational orbit is substantially geosynchronous and has (i) an inclination of greater than 70 degrees; (ii) a nominal eccentricity in the range of 0.25 to 0.5; (iii) an argument of perigee of approximately 90 or approximately 270 degrees; (iv) a right ascension of ascending node of approximately 0; and (v) an operational orbit apogee altitude. The interim orbit has an initial second apogee altitude that is at least 4500 km higher than the first apogee altitude, and the interim orbit naturally decays, subsequent to the orbit transfer maneuver, such that the satellite will reenter Earth's atmosphere no longer than 25 years after completion of the orbit transfer maneuver.

Abstract: Latching or locking deployment hinges are provided that include a latch mechanism, a spring-loaded tensioning device, and a trigger mechanism. The trigger mechanism and the spring-loaded tensioning device are configured to transfer the compressed spring load in the spring-loaded tensioning device to the latch mechanism once the hinge has closed sufficiently far enough to latch together, thus inducing a pre-load through the latch mechanism that eliminates gapping in the hinge interface. The hinges may be sprung or actuated using a powered drive mechanism.

Abstract: An array of antenna feed elements includes a plurality of horns, each horn having an aperture and configured for transmission of electromagnetic energy therethrough. At least a first horn is configured with an electrically conductive external surface proximate to the aperture, the external surface contoured so as to reduce mutual coupling between the first horn and an adjacent horn. Where the electromagnetic energy is within a radio frequency (RF) band, the external surface is contoured so as to provide an abrupt change in a gap dimension between the first horn and an adjacent horn, the change occurring at a distance behind the aperture of equal to a multiple of one half the characteristic wavelength of the RF band.

Abstract: Techniques for placing a satellite into a highly inclined elliptical operational orbit (HIEO) having an argument of perigee of 90° or 270° include executing an orbit transfer strategy that transfers the satellite from a launch vehicle deployment orbit to the operational orbit. The launch vehicle deployment orbit is selected to have an argument of perigee of approximately 90° greater than the argument of perigee of the operational orbit, and to be substantially lower than the operational orbit. The orbit transfer strategy includes (i) an apsidal rotation of approximately 90°, at least a substantial part of the apsidal rotation being attained without expenditure of any satellite propellant; and (ii) an electric orbit raising maneuver to attain an apogee altitude and a perigee altitude required by the HIEO.

Abstract: A mode filter provides a low-loss transmission path for RF signals propagating in a first mode, while substantially suppressing at least one second mode. The mode filter includes a proximal port and a distal port, having a respective characteristic cross sectional dimension Dp1 and Dp2, and an electrically conductive hollow tube having a longitudinal axis that extends a length L between a distal end of the proximal port and a proximal end of the distal port. A cross section transverse to the longitudinal axis is non-uniform along length L and has a minimum internal characteristic dimension Dmin at least at a first longitudinal position and a maximum internal characteristic dimension Dmax at least at a second longitudinal position. The mode filter is configured to suppress the at least one second mode by at least 5 dB, and Dmax is less than 2.5 times the greater of Dp1 and Dp2.

Abstract: Techniques for testing whether a bond strength between a faceskin of a panel and a core of the panel exceeds a threshold value are disclosed. The testing includes: adhering a first surface of a sacrificial layer to a pull stub of a flatwise tensile (FWT) test apparatus by way of a first adhesive interface; adhering the second surface of the sacrificial layer to the panel faceskin by way of a second adhesive interface; operating the FWT test apparatus so as to gradually increase a FWT load on the faceskin; terminating the test upon the first to occur of separation of any one or more of the first adhesive interface, the second adhesive interface, the sacrificial layer and separation of the faceskin from the core; and determining that the bond strength exceeds the threshold value when separation of the faceskin from the core is not the first to occur.

Abstract: Techniques for placing a satellite into a highly inclined elliptical operational orbit having an argument of perigee of 90° or 270° include executing an orbit transfer strategy that transfers the satellite from a launch vehicle deployment orbit to the operational orbit. The launch vehicle deployment orbit is selected to have an argument of perigee of approximately 90° greater than the argument of perigee of the operational orbit, an apogee altitude of approximately 14000 km and a perigee altitude of approximately 500 km. The orbit transfer strategy includes (i) an apsidal rotation of approximately 90°, at least a substantial part of the apsidal rotation being attained without expenditure of any satellite propellant; and (ii) an electric orbit raising maneuver to attain an apogee altitude and a perigee altitude required by the HIEO.

Abstract: An arrangement is disclosed for providing the functionality of a four port, four channel rotary switch. The arrangement includes a first four port rotary microwave switch, the first switch including a first rotor and a first set of four waveguide ports, and a second four port rotary microwave switch, communicatively coupled to the first switch, the second switch including a second rotor and a second set of four waveguide ports. Each of the first switch and the second switch has at most three channels.

Abstract: A spacecraft includes substantially parallel first radiator and second radiator panels, and a transverse panel coupled, having a width, W, coupled therebetween. The spacecraft also includes a first heat pipe having a first section parallel and proximate to the first radiator panel and a second section parallel and proximate to the transverse panel, a second heat pipe having a first section parallel and proximate to the second radiator panel and a second section parallel and proximate to the transverse panel and a third heat pipe, proximate and parallel to the transverse panel, the second section of the first heat pipe, and the second section of the second heat pipe. The third heat pipe has a length, L, substantially greater than W/2.