Abstract: A pair of buses connect devices and a processor on a backplane. Each device monitors both buses for a bus reset that is produced by the processor on detecting a fault with the active bus, at which time the processor switches to the inactive bus and produces a bus reset signal on the inactive bus, telling the devices to switch to the inactive active bus. The devices are programmed to respond to the reset signal on either bus to make it the active bus.

Abstract: Reaction wheels are placed around an enclosure so that the reaction wheel rotors provide a radiation shield for electronic components inside the enclosure.

Abstract: A spacecraft payload, suspended by an isolator, is locked down during launch by using a compliant member to pull on a pin, clamping the payload against the launch lock. The payload is unlocked, after launch, by heating a shape memory alloy to move the pin to overcome the compliant member, releasing the payload from launch lock. The payload may be re-locked for reentry by heating another shape memory alloy to push the pin against the other shaped memory alloy.

Abstract: In a position in control, a velocity error is compared to a limit that is a non-linear, continuous and differentiable function of the position error. If the position error is greater than a limit or magnitude, the velocity limit is used for the velocity command; otherwise the position error is used.

Abstract: Parallel surfaces are interfacially mechanically bonded and optionally electrically, and/or thermally connected using an interposer fabricated from a flexible laminates, such as flex PWB. The bond/connection points for the device made on one side of the interposer are displaced in the X and Y axis from the bond/connection points on the other or obverse side for the interposer and the board. The optional electrical/thermal connection through the interposer is made through one or more traces and vias in the flex board.

Abstract: A constant volume damper which has a very constant damping constant over a considerable range of frequencies by including check valves that prevent cavitation as a piston moves in a chamber. The damper is also sealed for use in space application and is temperature compensated.

Abstract: A payload launching method measures the attitude of a booster during a launch with an inertial measurement unit on the payload to compare the actual booster trajectory with a desired trajectory to control the payload at the deployment location, the inertial measurement unit on a booster carrying the payload using said desired trajectory to reach the deployment location

Abstract: An acoustic vibration isolator for use in preventing damage to a payload connected to a launch vehicle by removing the air around the payload so that acoustic vibrations do not have a medium to travel through to reach the payload.

Abstract: A coil winding mandrel comprises a mandrel core and two end flanges, a stationary flange and an adjustable flange. A spring provides a predetermined force between the end flanges.

Abstract: A vibration isolator which may be constructed in the form of a cube for use in retrofitting a device which is subjected to unwanted vibration present in an attached member which utilizes an active vibration isolator and a passive isolator in series between the members and which may include an overload protection device in the form of a deformable member in parallel with the isolators.

Abstract: A moment control device for positioning a spacecraft which employs a plurality of spinning bodies operable to impart a desired torque to a space craft, the bodies being constructed in a unitary combination and the unitary combination being mounted to the spacecraft to be positioned.

Abstract: A coupling comprises blade flexures that connect two end members through which control rods extend to cross members that are attached near the mid-points of the blade flexures, providing stable-linear load reaction means for use as end pivots for linkages where stick-slip motion is undesirable. The blade flexures are housed in a rigid cage comprising four separators that are attached to end members, and the flexures are attached to the end members by the separators.

Abstract: Disclosed is a method of forming a multilayer opaque coating on an integrated circuit or multichip module. First, an opaque coating composition is heated to a molten state and the molten opaque coating composition is applied so as to form an opaque coating that overlies active circuitry on the surface of the integrated circuit or multichip module, to prevent optical and radiation based inspection and reverse engineering of the active circuitry. Further coatings are applied over the opaque coating to shield the active circuitry of the integrated circuit or multichip module from the adverse affects of electromagnetic interference and/or high energy radiation.

Abstract: Disclosed is a method of forming an opaque coating on an integrated circuit or multichip module. A coating composition is prepared and then heated to a temperature sufficient to transform the coating composition to a molten state. Next, the molten coating composition is applied to a surface of the integrated circuit device to form an opaque coating that overlies active circuitry on the surface, to prevent optical and radiation based inspection and reverse engineering of the active circuitry.

Abstract: A vehicle control system is disclosed utilizing a reaction wheel assembly for producing small scanning motions and, in combination, a scissored pair of low-cost control moment gyros is used to produce larger slewing motions.

Abstract: In a ring laser gyro (RLG), the dither pick off signal is applied to a variable gain amplifier, producing an output that controls the amplitude of the motion of a dither motor connected to the gyro. A square wave is generated from the dither pick off signal and applied to a signal processor with clockwise and counterclockwise signals produced by the motion of the gyro. The signal processor controls a multiplexer to select the gain for the variable gain amplifier by counting the clockwise and counterclockwise signals produced by the gyro motion in a interval (number of whole periods of dither motion) determined by counting the square wave signal produced from the dither pick off signal.

Abstract: A motor controller circuit including an energy storage device, a bus protection circuit, an input signal selector, a combiner, a compensator, a modulator, a motor driver circuit, a commutator, a feedback circuitry and a plurality of filters, resistors, inductances, capacitances and optical isolators all contained on a single circuit board for use in controlling a motor with a minimum of cost and space requirements.

Abstract: A method is disclosed for targeting a satellite orbiting earth between to sites on earth based on an access time that is transmitted from a ground station. Control momentum gyros are used to change the satellite's attitude for targeting. A gryo rate is selected based the longest time to target. The longest time is a value selected from the access time, the time to reach the target based on the satellite's attitude and the time to reach the target based on the gyro rate.

Abstract: A circuit for use with a limited resolution device such as a stepper motor to convert a high-resolution signal such as from a computer into a high fidelity signal for driving the limited resolution device. The input to the limited resolution device being an average of the integrated difference between the high-resolution signal and a limited resolution signal consistent with the values used for driving the limited resolution device. This average being a high fidelity signal which is substantially the same as the high-resolution signal.

Abstract: Controlled momentum gyros are rotated to change the attitude of a satellite as rapidly as possible by rotating them along a great circle path on an imaginary spherical surface around the satellite. Adjustments the gyro rotations are made in two directions, along the spherical surface, as the satellite rotates. All the stored angular momentum in the gyros is used to rotate the satellite, rather than limiting the rotation of the gyros to avoid instabilities from singularities in traditional control laws.