Abstract: An aircraft system may include an airfoil and a deployable device coupled to the airfoil. The system may further include a shape memory alloy actuator coupled between the airfoil and the deployable device. The actuator may be movable between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil. The system may additionally include an activatable link positioned between the actuator and the deployable device. The link may have an engaged configuration in which motion of the actuator is transmitted to the deployable device, and a disengaged configuration in which motion of the actuator is not transmitted to the deployable device.

Abstract: A shape memory alloy (SMA) actuated aerostructure operable to dynamically change shape according to flight conditions is disclosed. Deformable structures are actuated by SMA actuators that are coupled to face sheets of the deformable structures. Actuating the SMA actuators produces complex shape changes of the deformable structures by activating shape changes of the SMA actuators. The SMA actuators are actuated via an active or passive temperature change based on operating conditions. The SMA actuated aerostructure can be used for morphable nozzles such as a variable area fan nozzle and/or a variable geometry chevron of a jet engine to reduce engine noise during takeoff without degrading fuel burn during cruise.

Abstract: Aircraft systems with shape memory alloy (SMA) actuators, and associated methods are disclosed. A system in accordance with one embodiment includes an airfoil, a deployable device coupled to the airfoil, and a shape memory alloy actuator coupled between the airfoil and the deployable device. In one embodiment, the deployable device can be coupled to the airfoil with a hinge having a hinge load path supporting the deployable device relative to the airfoil, and the actuator can be movable along a motion path different than the hinge load path between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil.

Abstract: A method and systems are disclosed for reducing fluid flow noise. The method and systems use a thermal mechanism to deploy a flap edge fence during landing and/or other operating conditions, and stow the flap edge fence during other operational conditions such as cruise. The flap edge fence is controlled passively by ambient temperature or actively by a controller based on temperature changes corresponding to various operating conditions.

Abstract: A method and systems are disclosed for reducing fluid flow noise. The method and systems use a thermal mechanism to deploy a flap edge fence during landing and/or other operating conditions, and stow the flap edge fence during other operational conditions such as cruise. The flap edge fence is controlled passively by ambient temperature or actively by a controller based on temperature changes corresponding to various operating conditions.

Abstract: Aircraft systems with shape memory alloy (SMA) actuators, and associated methods are disclosed. A system in accordance with one embodiment includes an airfoil, a deployable device coupled to the airfoil, and a shape memory alloy actuator coupled between the airfoil and the deployable device. In one embodiment, the deployable device can be coupled to the airfoil with a hinge having a hinge load path supporting the deployable device relative to the airfoil, and the actuator can be movable along a motion path different than the hinge load path between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil.

Abstract: A method and systems are disclosed for reducing fluid flow noise. The method and systems use a thermal mechanism to deploy a flap edge fence during landing and/or other operating conditions, and stow the flap edge fence during other operational conditions such as cruise. The flap edge fence is controlled passively by ambient temperature or actively by a controller based on temperature changes corresponding to various operating conditions.

Abstract: An impedance tuning system, especially for a cellular telephone system. The system can be used to match the impedance of an antenna element with that of an output stage of a transmitter driving the antenna element. The system includes a piezo capacitor in parallel with the magnetostrictive inductor to form an LC circuit. A voltage controller applies a voltage bias signal to the piezo capacitor and a current controller applies a current bias signal to the inductor. A primary controller monitors the frequency of the output signal from the transmitter and controls the voltage and current controllers as needed to alter the impedance of the system as needed to match the impedance of the antenna element with that of the output stage of the transmitter. In an alternative form an ultrasonic sensor is provided.

Abstract: The present invention presents a system for a compound actuator. The system includes first and second electrode layers each including two electrode sections, an intermediate electrode layer between the first and second electrode layers, and first and second electrostrictive materials that change length in an applied electrical field. The first electrostrictive material is positioned between the first and intermediate electrode layers. The second electrostrictive material is positioned between the intermediate and second electrode layers. The first electrostrictive material has a first length adjoining the first electrode section and a second length adjoining the second electrode section. The second electrostrictive material has a third length adjoining the fourth electrode section and a fourth length adjoining the fifth electrode section.

Abstract: A noise reduction system for use with an exhaust nozzle associated with a jet engine of an aircraft. The noise reduction system employs a plurality of flow-altering components disposed circumferentially about a lip portion of an exhaust nozzle. In one preferred form the flow-altering components each comprise piezoelectric transduction layers. The flow-altering components are caused to move in an oscillating manner by an AC signal applied thereto such that they move into and out of the exhaust gas emitted from the exhaust nozzle to achieve a desired degree of intermixing of the exhaust flow with the flow adjacent the exhaust nozzle. This produces a reduction in the noise generated by the jet engine. The noise reduction can be utilized during takeoff conditions of an aircraft.

Abstract: The present invention presents a system for a compound actuator. The system includes first and second electrode layers each including two electrode sections, an intermediate electrode layer between the first and second electrode layers, and first and second electrostrictive materials that change length in an applied electrical field. The first electrostrictive material is positioned between the first and intermediate electrode layers. The second electrostrictive material is positioned between the intermediate and second electrode layers. The first electrostrictive material has a first length adjoining the first electrode section and a second length adjoining the second electrode section. The second electrostrictive material has a third length adjoining the fourth electrode section and a fourth length adjoining the fifth electrode section.

Abstract: A bimorph actuator is driven by electrostrictive materials configured to change length in response to applied electrical field. A first electrostrictive material is positioned between a first electrode and a second electrode. A second electrostrictive material is positioned between a second electrode and a third electrode. The second electrostrictive material and the first electrostrictive material are attached to each other such that a differential change in their respective lengths results in a lateral motion. A first voltage source provides a voltage differential between the first electrode and the third electrode. A second variable voltage applied to the second electrode causes the length of the first electrostrictive material to lengthen when the second electrostrictive material shortens, and vice versa. A system of electrodes for the bimorph actuator and a method for actuating electrostrictive materials are also provided.

Abstract: The present invention presents a system for a compound actuator. The system includes first and second electrode layers each including two electrode sections, an intermediate electrode layer between the first and second electrode layers, and first and second electrostrictive materials that change length in an applied electrical field. The first electrostrictive material is positioned between the first and intermediate electrode layers. The second electrostrictive material is positioned between the intermediate and second electrode layers. The first electrostrictive material has a first length adjoining the first electrode section and a second length adjoining the second electrode section. The second electrostrictive material has a third length adjoining the fourth electrode section and a fourth length adjoining the fifth electrode section.

Abstract: A bimorph actuator is driven by electrostrictive materials configured to change length in response to applied electrical field. A first electrostrictive material is positioned between a first electrode and a second electrode. A second electrostrictive material is positioned between a second electrode and a third electrode. The second electrostrictive material and the first electrostrictive material are attached to each other such that a differential change in their respective lengths results in a lateral motion. A first voltage source provides a voltage differential between the first electrode and the third electrode. A second variable voltage applied to the second electrode causes the length of the first electrostrictive material to lengthen when the second electrostrictive material shortens, and vice versa. A system of electrodes for the bimorph actuator and a method for actuating electrostrictive materials are also provided.

Abstract: A noise reduction system for use with an exhaust nozzle associated with a jet engine of an aircraft. The noise reduction system employs a plurality of flow-altering components disposed circumferentially about a lip portion of an exhaust nozzle. In one preferred form the flow-altering components each comprise piezoelectric transduction layers. The flow-altering components are caused to move in an oscillating manner by an AC signal applied thereto such that they move into and out of the exhaust gas emitted from the exhaust nozzle to achieve a desired degree of intermixing of the exhaust flow with the flow adjacent the exhaust nozzle. This produces a reduction in the noise generated by the jet engine. The noise reduction can be utilized during takeoff conditions of an aircraft.

Abstract: An integrated multi-mode transducer for use with a member to control movement of the member. The transducer includes an active element adaptable to engage the member. The active element is changeable from a first shape to a second shape in the presence of an electromagnetic field. Apparatus including a controller is provided for producing an electromagnetic field which extends through at least a portion of the active element to change the shape of the active element and thus exert a force on the member, for sensing movement of the member and for damping movement of the member. A method for using the transducer is provided.