Abstract: An aircraft can include a wing. A morphing member can be operatively connected to the wing. The morphing member can include a base and a shape memory material member operatively connected to the base. The base can be made of a flexible material. When the shape memory material member is activated, a shape of the morphing member can change. As a result, one or more aerodynamic characteristics of the aircraft can be changed. In some arrangements, the flexible material can be a fabric, and the shape memory material member can be a shape memory alloy wire.

Abstract: A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.

Abstract: A wind turbine including: at least a rotor blade including an aerodynamic device for influencing the airflow flowing from the leading edge section of the rotor blade to the trailing edge section of the rotor blade, wherein the aerodynamic device is mounted at a surface of the rotor blade, an actuator of the aerodynamic device for actuating the aerodynamic device at least between a first protruded configuration and a second retracted configuration, a pressure supply system for operating the actuator by means of a pressurized fluid, an acoustic receiver for measuring an acoustic signal in the pressure supply system, and a diagnostic unit connected to the acoustic receiver and configured for deriving an operative status of the aerodynamic device based on the acoustic signal, is provided.

Abstract: Some embodiments are directed to a three-dimensional (3D) preform including reinforcing fibres and shape memory alloys (SMA) wires and a composite material including a polymer matrix with a 3D-preform embedded therein, wherein the 3D-preform includes reinforcing fibres and shape memory alloy (SMA) wires.

Abstract: A rotor blade assembly includes a rotor blade including one or more pockets and a housing located on the rotor blade within one or more pockets. The housing is secured to the rotor blade via one or more dovetail joints. A drive mechanism for a control surface of a rotor blade includes an actuator and a rocker operably connected to the actuator. At least one hinge rod is operably connected to the rocker and operably connected to a control surface at a control surface pivot. The drive mechanism translates substantially linear motion of the actuator into rotational motion of the control surface about the control surface pivot.

Abstract: A system for connecting two relatively movable structures on an aircraft, comprising: a first rigid structure attached to one of the relatively movable rigid structures; a second rigid structure attached to another of the relatively movable structures; a flexible skin connected to the first and second rigid structures; a sleeve comprising first and second end portions; a first rod comprising a first end portion attached to the first rigid structure, a second end portion slidably coupled to the first end portion of the sleeve, and an intermediate portion made of shape memory alloy; a second rod comprising a first end portion attached to the second rigid structure, a second end portion slidably coupled to the second end portion of the sleeve, and an intermediate portion made of shape memory alloy; and means for heating at least the intermediate portions of the first and second rods.

Abstract: Apparatus and methods provide for a flow control actuator having a fluid cavity that is shaped to create periodic waveforms within the resulting resonant actuating flow with predetermined characteristics for actuating a high-speed fluid flow. According to various embodiments, a flow control actuator includes a power source for exciting the actuator fluid at a resonant frequency and a cavity shaped according to resonant macrosonic synthesis principles to maximize the exit velocity of the actuating flow at an orifice of the actuator.

Abstract: A rotational actuator assembly employs a first torsion actuator having a shape memory alloy (SMA) tube with a first trained twist direction and a second torsion actuator having a SMA tube with an opposite trained twist direction collinear with the first torsion actuator with abutting proximal ends. A central fitting joins the proximal ends. A control system for temperature control of the first torsion actuator and second torsion actuator about an average temperature provides combined antagonistic rotation of the central fitting.

Abstract: A system and method for producing surface deformations on a surface of a body. The system and method relate to changing the convective heat transfer coefficient for a surface. The system includes a first surface being a surface of a body exposed to a fluid flow and at least one actuator affecting deformation of the first surface. The system also includes a control system providing control commands to the at least one actuator, the control commands configured to change deformations on the first surface in order to change the convective heat transfer coefficient of the first surface. Further, the system includes a sensor providing environmental characteristic information to the control system.

Abstract: A method of making an auxetic mesh, which method includes: (a) extruding a polymeric material 60 onto an open casting surface 58 that has an intended pattern 62 disposed therein, the pattern 62 being configured to create an auxetic mesh 20; (b) wiping off excess extruded polymeric material 60 from the open casting surface 64; (c) removing the cast mesh 20 from the open casting surface 64 after the excess polymeric material 60 has been wiped off; and (d) removing any residual polymeric material that is not of the intended mesh pattern 20. The method allows for the continuous production of auxetic meshes.

Abstract: A panel structure includes a composite facesheet and a stiffening core having a plurality of core members in an intersecting web configuration provided on the composite facesheet.

Abstract: A torsion lock may include a clutch, a spring, and a shape memory alloy (SMA) member. The spring may cause the application of pressure on the clutch for engagement thereof. The SMA member may linearly contract when heated in a manner to relieve the pressure on the clutch for disengagement thereof.

Abstract: A shape-change material includes a shape memory material layer with an electrically conductive layer on a surface of the shape memory material layer. The conductive material may be used to heat the shape memory material by electrical resistance heating. The conductive material may be a primary heater, providing the heating to cause softening or shape change in the shape memory material, or may be a secondary heater in conjunction with a greater amount of heating from a primary heater, such as a conductive plate that provides electrical resistance heating to a surface of the shape memory material on an opposite side of the shape memory material from the conductive material. One use for the shape-change material is as the skin material for a shape changing material.

Abstract: A laminated wing structure includes at least one layer of metal material and at least one layer of a shape memory polymer (SMP) material. The SMP is heated to a temperature in its glass transition band Tg to roll the wing around the air vehicle into a stored position. The metal layer(s) must be thin enough to remain below its yield point when rolled up. In preparation for launch, the SMP material is thermally activated allowing the strain energy stored in the layer of metal material to return the wing to its deployed position at launch. Once deployed, the SMP cools to its glassy state. The SMP material may be reinforced with fiber to form a polymer matrix composite (PMC). SMP may be used to provide shear strain relief for multiple metal layers. By offloading the motive force required to return the wing to its original deployed position from the SMP to the metal, the polymer does not acquire a permanent set and the wing may be deployed accurately.

Abstract: A method and apparatus for an adaptive aerostructure is presented that relies on certified aerospace materials and can therefore be applied in conventional passenger aircraft. This structure consists of a honeycomb material which cells extend over a significant length perpendicular to the plane of the cells. Each of the cells contains an inelastic pouch (or bladder) that forms a circular tube when the cell forms a perfect hexagon. By changing the cell differential pressure (CDP) the stiffness of the honeycomb can be altered. Using an external force or the elastic force within the honeycomb material, the honeycomb can be deformed such that the cells deviate from their perfect-hexagonal shape. It can be shown that by increasing the CDP, the structure eventually returns to a perfect hexagon. By doing so, a fully embedded pneumatic actuator is created that can perform work and substitute conventional low-bandwidth flight control actuators.

Abstract: A method, apparatus, and computer program product for identifying a number of air states for a vehicle. A deflection of a control surface associated with an actuator is identified to form an identified deflection. A current in the actuator is identified to form a measured current. The number of air states for the vehicle is estimated using the identified deflection and the measured current.

Abstract: Systems and methods for providing dynamic control to a surface immersed in a dynamic fluid. The systems and methods of the invention relate to one or more morphable surfaces that can be control in an active manner to provide asperities that interact with a fluid moving across the morphable surfaces. By controlling the size, shape and location of the asperities, one can exert control authority over the motion of the surface relative to the fluid. Examples of materials that provide suitable morphable surfaces include ionic polymer metal composites and shape memory polymers, both of which types of material are commercially available. Useful morphable surface systems have been examined and are described.

Abstract: The invention relates to an elongated, torsion-deformable aerodynamic element, in which the upper surface (2) is continuous while the lower surface (3) comprises a longitudinal slot (6) in the direction of the span and in the vicinity of the leading edge (4). Furthermore, an actuator device (14) inside said aerodynamic element is capable of sliding the edges (6A and 6R) of the slot (6) relative to each other.

Abstract: A composite flexible and aerodynamic load bearing wing structure suitable for compact unmanned vehicles, is described. Flexible printed circuitry and micro fuel cells can be incorporated as, or part of, the flexible aerodynamic structure. Accordingly, the overall system configuration can be optimized with respect to weight, space and size requirements. The flexible aerodynamic structure for the unmanned vehicle may be configured with a flexible dielectric substrate having an electrical contact on at least one surface of the substrate, and a flexible printed circuit disposed upon the substrate. The printed circuit can flex with the substrate and the substrate, with the printed circuit, to form a load lifting aerodynamic wing configuration when unfolded from a folded position.

Abstract: A device such as an aerofoil which in use is subject to fluid flow, includes an outer surface part the geometry of which is variable to affect the fluid flow, the device including a support structure which supports the outer surface part, the support structure being internal of the device and including a plurality of support members of composite material the geometry of the support structure being changeable by an actuating apparatus, between a first stable geometry and a second stable geometry to effect variation in the geometry of the outer surface part, the support members providing structure stiffness to the outer surface part.

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: An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members.

Abstract: A system and method is described generally for deforming a first surface of a body and deforming a second surface of a body to alter a fluid flow in order to change the characteristics of the fluid flow about the body and thereby control the fluid dynamic forces on the body.

Abstract: A system and method is described generally for deforming a surface of a body to alter a fluid flow in order to change the characteristics of the fluid flow about the body.

Abstract: A wind turbine blade has a suction side surface and a pressure side surface. A plurality of dynamic vortex elements are formed on at least one of the suction side or the pressure side surfaces. The vortex elements are activatable between a first retracted position that is inwardly recessed relative to a neutral plane of the surface on which they are formed and a second extended position that is outwardly protruding relative to the neutral plane of the surface.

Abstract: An apparatus for generating vortexes in fluid flow generally adjacent to a surface includes: (a) at least one vortex generating element; and (b) a piezoelectric motor element coupled with the at least one vortex generating element. The piezoelectric motor element responds to a varying voltage signal to move the at least one vortex generating element between a first position extending into the fluid flow an operating distance from the surface and a second position generally flush with the surface.

Abstract: An assembly for controlling a vehicle, including a fluid contact surface constructed and arranged to act against a fluid passing over the fluid contact surface; and a support structure coupled to the fluid contact surface. The support structure is constructed and arranged to expand or contract between a first position and a second position, such that a first dimension of the support structure changes during movement of the support structure between the first position and the second position, while a second dimension of the support structure remains substantially constant during the movement of the support structure between the first position and the second position.

Abstract: Apparatus and associated methods for actuating variable stiffness material (VSM) structures and achieving deformation of the structures. The apparatus and the associated methods use internal embedded actuation elements and/or externally attached elements to the VSM structures to achieve the desired deformation. In particular, the actuation can be changed due to the variable stiffness nature of the materials. That is, the invention provides the ability to control the deformation of structures using local stiffness control over subregions of the component in addition to or in substitution for actuation. Furthermore, the invention exploits the variable stiffness properties of the VSM structures to enable new functionalities impossible to realize with conventional constant stiffness materials.

Abstract: A cover skin for a variable-shape aerodynamic area, such as a wing structure, tail unit structure, control surface structure or flap structure is described. A cover skin is deformable in one direction without exhibiting substantial deformation in a transverse direction. A deformable framework structure is embedded in a layer of an elastic material, such as rubber or polymer. The framework structure may be comprised of non-deformable elements joined pivotably in auxetic and non-auxetic assemblies of elements that are capable of substantially eliminating transversal contraction, when the cover skin is longitudinal stretched, and substantially eliminating transversal expansion, when the cover skin is longitudinally contracted.

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 flow control device is disclosed including a flow control surface over which fluid is designed to flow in a predetermined direction. Vortex generators are associated with the flow control surface. Each respective vortex generator has a pivot axis that forms an acute angle with respect to the predetermined direction and is capable of being positioned in both of an extended state, in which the respective vortex generators function to create a swirling fluid flow, and a retracted state, in which the respective vortex generators are pivoted via the pivot axis so as to lie adjacent to the flow control surface. An actuator is associated with each of the vortex generators, each actuator adapted to position the associated vortex generator between the extended and retracted states. The flow control device is disclosed to be used in tiltrotor vehicles.

Abstract: An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members.

Abstract: Methods and apparatus for systems having deployable elements according to various aspects of the present invention comprise a system including a deployable surface and an adaptive actuator including a polymer foam. In one embodiment, the system comprises a vehicle including a deployable wing comprising an exterior surface. The exterior surface may be adjusted by adjusting the shape, size, position, and/or orientation of the adaptive actuator.

Abstract: Methods and apparatus for systems having deployable elements according to various aspects of the present invention comprise a system including a deployable surface and an adaptive actuator including a polymer foam. In one embodiment, the system comprises a vehicle including a deployable wing comprising an exterior surface. The exterior surface may be adjusted by adjusting the shape, size, position, and/or orientation of the adaptive actuator.

Abstract: The present invention relates to a sandwich-structure flat active actuator that is symmetrical relative to the mid-plane comprising at least one piezoelectric flat layer having an active direction superpose and fixedly attached to at least one passive flat layer of fabric with rigid warp and weft oriented in two directions forming a mesh; the two directions of each layer of fabric are the same. The active direction of each piezoelectric layer is oriented along one and the same diagonal of the mesh of the layers of fabric. The invention is also aimed at a device consisting of two actuators mounted head-to-tail. The invention applies to the active torsion of structures such as, for example, a helicopter blade.

Abstract: In a method of controlling the hardness of a damper in an aircraft landing gear, the aircraft having a structure that is deformable at a natural frequency, the hardness of the damper is adjusted during a contraction of the damper as a function of the natural frequency.

Abstract: A projectile includes a projectile body including a flow surface; the flow surface including at least one control surface formed therein. The controls surface is formed continuous with the flow surface, and a pressure source is connected to at least one control surface. The pressure source delivers a pressure to at least one control surface to cause at least one control surface to bulge away from the flow surface.

Abstract: A MagnetoRheolocial Fluid Elastic (MRFE) lag damper system for adaptive lead-lag damping of helicopter main rotors. Embodiments include snubber dampers especially for hingeless helicopter rotors, and concentric bearing dampers. The snubber lag dampers include a flexible snubber body defining a cavity, a flexible or rigid interior (e.g., center) wall subdividing the cavity, and a flow valve in the interior wall or external to the cavity. The flexible snubber body may comprise elastomeric materials and metal rings stacked together to create a sealed MR fluid cavity. The shear deformation of the snubber body induces MR fluid flow through the valve, controlled by a magnetic field in the valve. An MRFE concentric bearing damper is also disclosed, comprising a pair of concentric tubes with elastomeric material injected and cured in an annular gap between the two tubes, and an MR fluid reservoir with piston-mounted MR valve housed inside the innermost tube.

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: Methods and apparatus for systems having deployable elements according to various aspects of the present invention comprise a system including a deployable surface and an adaptive actuator including a polymer foam. In one embodiment, the system comprises a vehicle including a deployable wing comprising an exterior surface. The exterior surface may be adjusted by adjusting the shape, size, position, and/or orientation of the adaptive actuator.

Abstract: In some embodiments, a variable stiffness structure is provided having constant stiffness material layers and variable modulus material layers arranged in alternating layers. The variable modulus material layers have a material with a changeable elastic modulus in response to an applied energy field so as to allow reversible coupling and decoupling of stress transfer between successive layers of the constant stiffness material layers to provide a change in a bending stiffness of the variable stiffness structure. The constant stiffness material layers may include segmented portions. The constant stiffness material layers may have segmented portions arranged such that successive layers of the plurality of constant stiffness material layers have overlapping segmented portions. The variable modulus material layers may have shaped structures, for example, corrugation, pillars, striations, tubular, or honeycomb configurations.

Abstract: Apparatus and methods for hybrid actuation and suppressing vibration are disclosed. In one embodiment, a hybrid actuator includes a first actuator and a second actuator linked to move a component a combined actuation distance. The first actuator may include a hydraulic piston, and the second actuator may include a piezo-electric actuator. In another embodiment, the first actuator is activated within a first frequency range, and the second actuator is activated within a second frequency range. In another aspect, a method is provided combining a first actuation movement and a second actuation movement. In another embodiment, a system is provided for suppressing movement of a component including a combination of actuators. In a further embodiment, an aircraft is provided with hybrid motion suppression including a first actuator and a second actuator linked to activate a control surface.

Abstract: A jet engine exhaust nozzle flow effector is a chevron formed with a radius of curvature with surfaces of the flow effector being defined and opposing one another. At least one shape memory alloy (SMA) member is embedded in the chevron closer to one of the chevron's opposing surfaces and substantially spanning from at least a portion of the chevron's root to the chevron's tip.

Abstract: Apparatus and methods for hybrid actuation and suppressing vibration are disclosed. In one embodiment, a hybrid actuator includes a first actuator and a second actuator linked to move a component a combined actuation distance. The first actuator may include a hydraulic piston, and the second actuator may include a piezo-electric actuator. In another embodiment, the first actuator is activated within a first frequency range, and the second actuator is activated within a second frequency range. In another aspect, a method is provided combining a first actuation movement and a second actuation movement. In another embodiment, a system is provided for suppressing movement of a component including a combination of actuators. In a further embodiment, an aircraft is provided with hybrid motion suppression including a first actuator and a second actuator linked to activate a control surface.

Abstract: An assembly for controlling a vehicle, including a fluid contact surface constructed and arranged to act against a fluid passing over the fluid contact surface; and a support structure coupled to the fluid contact surface. The support structure is constructed and arranged to expand or contract between a first position and a second position, such that a first dimension of the support structure changes during movement of the support structure between the first position and the second position, while a second dimension of the support structure remains substantially constant during the movement of the support structure between the first position and the second position.

Abstract: In one preferred embodiment, a structure is provided that includes a body having a first wall and a second wall. At least one appending component extends from an end of the body and includes a first skin and second skin. The structure additionally includes at least one actuator positioned within a cavity formed in the body first wall and the appending component second skin. The actuator includes at least one shape memory alloy (SMA) wire adapted to constrict when activated to move the first skin of the appending component from a first position to a second position.