Abstract: Embodiments of the present invention include an aircraft capable of sustained out-of-ground-effect hover flight and sustained supersonic flight. At least some embodiments includes two wings powered by an engine to counterrotate while hovering, and to not rotate and sweep while flying at transonic and supersonic speeds. Other embodiments include two rotating wings that generate a force per unit area of under 100 lb/ft2 within the rotating wing disk during hover. Still other embodiment include a vehicle with rotating wings that can increase pitch to accelerate the aircraft, align the chord line of the wings with the airstream, and sweep the wings. Still further embodiments include a power plant that powers unducted rotating wings during hover and disengages from the wings to propel the aircraft at supersonic speeds.

Abstract: An apparatus and method for adaptive materials arranged in a variety of orientations and with a wide range of attachment configurations to induce structural vibrations at extremely high frequencies. These mechanical vibrations cause fouling agents to become detached and accordingly “clean” an otherwise dirty element or wire of a hot-wire anemometer, planar or curvilinear sensor surface, or display surfaces. They also can be made to vibrate at such frequencies with such intensities that local droplets of water are either shaken off or instantaneously cavitate, thereby allowing the elements to be used in all weather conditions.

Abstract: A method and apparatus for a novel 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: An apparatus and method adapted to enhance the structural performance of a desired connection and provide a readily perceivable indication of predetermined limitations having being reached prior to actual failure of a connection. A method for enhancing structural performance of a desired structure by preventing fracture propagation.

Abstract: The design and refinement of a tethered hovering platform into a feasible working system is presented. To determine a starting point for the design, a detailed historical search was conducted to find the history and the current state of such technology. Real world current needs are analyzed to produce a mission specification and to drive the preliminary vehicle design. Analysis of environmental conditions and decisions about an initial payload package are made in conjunction with motor and propeller sizing. Initial concept testing to discover feasibility and operational issues was performed; from this, instability issues were discovered. Analyzing these instability issues using known rotorcraft and momentum effects, in conjunction with flight testing, yields possible solutions to the problem. The use of constrained layer dampers as a means of passive stabilization is addressed and suggested as the preferred solution. Testing of passive constrained layer damping verifies the stability of the solution.

Abstract: A method and system for a device to embed a low signal to interference plus noise ratio (SINR) communications signal into the backscatter of an illuminating signal. The illuminating signal may be acoustic or electromagnetic (EM) such as radio frequency (RF), light, or infrared (IR). The embedded communications signal may be recovered at a desired receiver.

Abstract: A method and apparatus for active boundary layer control on an aerodynamic surface. One or more piezoelectric synthetic jet actuators operate as a boundary layer pump to ingest fluid along the surface of an aerodynamic object and discharge fluid tangentially to the fluid flow along the surface and/or at the trailing edge of the object to reduce drag and delay stall.

Abstract: A method and apparatus for active boundary layer control on an aerodynamic surface. One or more piezoelectric synthetic jet actuators operate as a boundary layer pump to ingest fluid along the surface of an aerodynamic object and discharge fluid tangentially to the fluid flow along the surface and/or at the trailing edge of the object to reduce drag and delay stall.

Abstract: An apparatus, system and method for actuating or sensing strains in a substrate which includes at least one actuator/sensor element which has transverse and longitudinal axes. The actuator/sensor element is attached to the substrate in such a manner that the stiffness of the actuator/sensor element differs in the transverse and longitudinal axes. In this manner, it is possible to sense or actuate strains in the substrate in a desired direction, regardless of the passive stiffness properties of the substrate, actuator element or sensor element. An isotropic actuator/sensor element attached to a substrate in this manner can then operate in an anisotropic way. In a preferred embodiment, the actuator/sensor element is bonded to the substrate at an area of attachment occupying only the central third of the actuator/sensor element in its longitudinal axes. The actuator/sensor element may be a piezoelectric, magnetostrictive, thermally actuated lamina (including bi-metallic) or shape memory alloy element.