Abstract: An spacecraft control system is provided that includes a tube and a plurality of microwheels. The plurality of microwheels is disposed within the tube. Each microwheel has a first stator wafer, a second stator wafer, and a rotor wafer disposed therebetween. The first and second stator wafers are configured to spin the rotor wafer.

Abstract: A vehicle control system is provided that includes a slat having an axis, a plurality of microwheels disposed on the slat, each microwheel having a first stator wafer, a second stator wafer, and a rotor wafer disposed therebetween, the first and second stator wafers configured to spin the rotor wafer, and an actuator coupled to the slat and configured to at least partially rotate the slat about the axis.

Abstract: The present invention relates to a reaction wheel assembly and fiber optic gyro device. The device includes a reaction wheel assembly having a reaction wheel assembly housing, a fiber optic gyro coil integrated with the reaction wheel assembly housing, and a fiber optic gyro electronics integrated with the reaction wheel assembly housing. The fiber optic gyro coil may be wound around the reaction wheel assembly housing. The gyro coil may also be located within the reaction wheel assembly housing.

Abstract: An inertial reference system for a spacecraft includes an attitude control assembly and a plurality of force sensors. The attitude control assembly is coupled to a spacecraft body at a plurality of attachment points and at least one of the plurality of force sensors is integrated at each of the attachment points. In one embodiment, the force sensors are piezoelectric transducers. In another embodiment, the control assembly is coupled to the spacecraft body at four attachment points. In yet another embodiment, each of the force sensors is preloaded by a bolt that attaches the attitude control assembly to the spacecraft body.

Abstract: A preload adjustment device and method are provided for momentum control devices. The preload adjustment device includes a piezodynamic preload spacer and a control system. The piezodynamic preload spacer is coupled to a bearing in the momentum control device. The piezodynamic preload spacer is configured such that the application of a control voltage to spacer causes a change in the spacer dimensions, with that change in spacer dimension adjusting the preload of the bearing within the momentum control device. The control system provides dynamic control of preload by selective application of control voltage to the piezodynamic preload spacer. This allows for adjustments of preload to compensate for changes in operating environment, improving the performance of the momentum control device. Additionally, adjustments of preload can by used to compensate for wear in the bearings that would otherwise negatively impact the life of the momentum control device.

Abstract: A vibration damping device and method for momentum control devices is provided. The vibration damping device includes a piezodynamic damping spacer and a tuning system. The piezodynamic damping spacer is coupled to a bearing in the momentum control device. The piezodynamic damping spacer is configured such that vibrations in the momentum control device are absorbed by piezodynamic damping spacer. The piezodynamic damping spacer converts these vibrations to electrical energy, where they can be dissipated by the tuning system. The tuning system provides the ability to tune the vibration damping device to most effectively absorb vibrations in specific frequency ranges. Thus, the vibration damping device is able to effectively reduce vibrations in the momentum control device.

Abstract: A remote Information Management Network routing system located either at an independent hosting facility or at a central station monitoring facility that receives event and alert information from a security or premise monitoring system and sequentially transmits interactive notifications about the event and alert information to wired and wireless devices specified in a user profile within the Information Management Network.

Abstract: A plurality of sensors provide spacecraft attitude signals to reaction wheel assemblies which provide converted signals to a flight controller that controls the reaction wheel assemblies. The reaction wheel assemblies include a secondary power supply to power the sensors, and power can be regenerated from the reaction wheels. A microcomputer in the reaction wheel assemblies can control the reaction wheel assemblies in place of the flight controller.

Abstract: A reaction wheel system is provided that includes at least two rotors. The first rotor is the primary rotor that provides the large output torques to the vehicle. The second rotor is a vernier control rotor. The primary rotor and vernier control rotor each rotate about a common axis. The vernier control rotor has an inertial mass that is less than the inertial mass of the primary rotor, and rotates independently of the primary rotor. Because the vernier control rotor can be rotated independently from the primary rotor, it can be used to significantly improve the performance of the reaction wheel system. Specifically, the vernier control rotor is used to provide relatively small output torques. These relatively small output torques can be used to reduce the disturbances created by motor ripple, provide precise torque output control and/or reduce the disturbances created by static friction.

Abstract: A plurality of sensors provide spacecraft attitude signals to reaction wheel assemblies which provide converted signals to a flight controller that controls the reaction wheel assemblies. The reaction wheel assemblies include a secondary power supply to power the sensors, and power can be regenerated from the reaction wheels. A microcomputer in the reaction wheel assemblies can control the reaction wheel assemblies in place of the flight controller.

Abstract: An inertial reference system for a spacecraft includes an attitude control assembly and a plurality of force sensors. The attitude control assembly is coupled to a spacecraft body at a plurality of attachment points and at least one of the plurality of force sensors is integrated at each of the attachment points. In one embodiment, the force sensors are piezoelectric transducers. In another embodiment, the control assembly is coupled to the spacecraft body at four attachment points. In yet another embodiment, each of the force sensors is preloaded by a bolt that attaches the attitude control assembly to the spacecraft body.

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: A gear drive having a third order damper operating with the antibacklash gear so as to lower the impact of the antibacklash gear at high torques to reduce gear wear while maintaining good contact with the antibacklash gear at lower torques to maintain high accuracy and bandwidth.

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 connector tow for providing external electrical access to an electrical device embedded within a composite structure. The connector comprises a plurality of tubes disposed between a pair of opposed film layers. The film layers are adhered to opposite sides of the plurality of tubes and can be comprised of an insulating material so as to electrically isolate the plurality of tubes. By extending through the edge surface of the composite structure, the electrical ports can be accessed during the fabrication of the a composite structure such that the operations of the embedded electrical device can be monitored.

Abstract: A fiber optic connector for establishing an optical connection with an optical fiber embedded within a composite structure is provided. The fiber optic connector includes a first lens element, such as a metal sheathed graded index (GRIN) lens, that is attached to the portion of the edge surface of the composite structure to which the optical fiber extends. The fiber optic connector also includes an alignment tube and a second optical fiber, external to the composite structure, having an end portion disposed within one end of the alignment tube. By sliding the other end of the alignment tube over the first lens element, optical communication is established between the first optical fiber embedded within the composite structure and the second optical fiber external to the composite structure. The fiber optic connector also typically includes a ferrule mounted upon the end portion of the second optical fiber and inserted at least partially into one end of the alignment tube.

Abstract: A method is provided for fabricating a composite structure having an externally accessible electrical device embedded therein. At least one supporting ply is initially provided that has first and second depressions. An electrical device having at least one electrical lead is disposed in the first depression and a connector tow having at least one tube with opposed first and second ends is disposed in the second depression. The first end of the tube of the connector tow is electrically connected to the electrical lead. Thereafter, at least one additional ply is stacked on the supporting ply such that the electrical device and the connector tow are embedded. The stacked plies can then be consolidated to form an integral laminate structure. Following the consolidation, the second end of the tube of the connector tow can be accessed through the edge surface of the laminate structure to thereby define an externally accessible electrical port for receiving a corresponding connector.

Abstract: A composite structure having an externally accessible electrical device embedded therein includes at least one tube disposed within the composite structure and extending from a first end which is electrically connected to an electrical lead of the electrical device to a second end which opens through the edge surface of the composite structure to thereby define an externally accessible electrical port. By plugging a corresponding connector into the electrical port, electrical contact can be established via the electrical lead with the electrical device embedded within the composite structure. By extending through the edge surface of the composite structure, the electrical ports can be accessed during the fabrication of the composite structure such that the operations of the embedded electrical device can be monitored.

Abstract: A composite structure and related fabrication method is provided which has a plurality of composite material layers and at least one embedded shape memory alloy component for providing controlled structural deformation. The shape memory alloy component includes a shape memory alloy tendon having a relaxed shape at temperatures below a predetermined transition temperature and a contracted shape at temperatures above the predetermined transition temperature. The shape memory alloy component also comprises a pair of electrically insulating opposing face sheets adhered to opposite sides of the shape memory alloy tendon to electrically isolate the shape memory alloy tendon from the surrounding composite material layers.

Abstract: A composite structure and related fabrication method is provided which has a plurality of composite material layers and at least one embedded shape memory alloy component for providing controlled structural deformation. The shape memory alloy component includes a shape memory alloy tendon having a relaxed shape at temperatures below a predetermined transition temperature and a contracted shape at temperatures above the predetermined transition temperature. The shape memory alloy component also comprises a pair of electrically insulating opposing face sheets adhered to opposite sides of the shape memory alloy tendon to electrically isolate the shape memory alloy tendon from the surrounding composite material layers.