Abstract: An aerial vehicle includes a body having a longitudinal axis, a plurality of movable members emanating connected to the body, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. The movable members are connected to the body and extend away from the body.

Abstract: An aerial vehicle capable of convertible flight from hover to linear flight includes a body having a longitudinal body axis, a plurality of forward wings, a plurality of aft wings, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. Each forward wing extends a forward wing plane. Each aft wing extends from an aft wing plane. The aerodynamic propulsors are mounted longitudinally between the plurality of forward wings and plurality of aft wings.

Abstract: An aerial vehicle capable of convertible flight from hover to linear flight includes a body having a longitudinal body axis, a plurality of forward wings, a plurality of aft wings, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. Each forward wing extends a forward wing plane. Each aft wing extends from an aft wing plane. The aerodynamic propulsors are mounted longitudinally between the plurality of forward wings and plurality of aft wings.

Abstract: A family of Radar energy Absorbing Deformable Low Drag Vortex Generators (RAD-LDVG) is described herein. This family of devices are fabricated in such a way that it can conform to aircraft surface features while reducing radar returns from structural details. Vortex generators (VGs) are typically used to reattach or smooth gross flowfields over aircraft surfaces. By doing so, an airfoil or wing can maintain attached flow at higher angles of attack and/or higher lift coefficients than one without the VGs. These devices are also used to reattach and/or smooth flows that encounter crossflow-induced instabilities and/or adverse pressure gradients on the upper surfaces of wings or near aircraft boattails. Other uses include reduction of buffet, vibration, flutter, cavity resonance or general bluff-body pressure drag reduction. Although conventional rigid VGs do generate vortical aerodynamic structures, two major problems are often experienced: i.) the inability to conform to curved surfaces, ii.

Abstract: A family of Radar energy Absorbing Deformable Low Drag Vortex Generators (RAD-LDVG) is described herein. This family of devices are fabricated in such a way that it can conform to aircraft surface features while reducing radar returns from structural details. Vortex generators (VGs) are typically used to reattach or smooth gross flowfields over aircraft surfaces. By doing so, an airfoil or wing can maintain attached flow at higher angles of attack and/or higher lift coefficients than one without the VGs. These devices are also used to reattach and/or smooth flows that encounter crossflow-induced instabilities and/or adverse pressure gradients on the upper surfaces of wings or near aircraft boattails. Other uses include reduction of buffet, vibration, flutter, cavity resonance or general bluff-body pressure drag reduction. Although conventional rigid VGs do generate vortical aerodynamic structures, two major problems are often experienced: i.) the inability to conform to curved surfaces, ii.

Abstract: A flat-stock aerial vehicle includes a body having a plurality of flat-stock sheets connected to one another, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. The aerodynamic propulsors can provide lifting thrust, pitch, yaw, and roll control in both helicopter-like hover flight and airplane-like translational flight.

Abstract: A family of Radar energy Absorbing Deformable Low Drag Vortex Generators (RAD-LDVG) is described herein. This family of devices are fabricated in such a way that it can conform to aircraft surface features while reducing radar returns from structural details. Vortex generators (VGs) are typically used to reattach or smooth gross flowfields over aircraft surfaces. By doing so, an airfoil or wing can maintain attached flow at higher angles of attack and/or higher lift coefficients than one without the VGs. These devices are also used to reattach and/or smooth flows that encounter crossflow-induced instabilities and/or adverse pressure gradients on the upper surfaces of wings or near aircraft boattails. Other uses include reduction of buffet, vibration, flutter, cavity resonance or general bluff-body pressure drag reduction. Although conventional rigid VGs do generate vortical aerodynamic structures, two major problems are often experienced: i.) the inability to conform to curved surfaces, ii.

Abstract: A flat-stock aerial vehicle includes a body having a plurality of flat-stock sheets connected to one another, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. The aerodynamic propulsors can provide lifting thrust, pitch, yaw, and roll control in both helicopter-like hover flight and airplane-like translational flight.

Abstract: An aerial vehicle includes a body having a longitudinal axis, a plurality of movable members emanating connected to the body, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. The movable members are connected to the body and extend away from the body.

Abstract: An aerial vehicle capable of convertible flight from hover to linear flight includes a body having a longitudinal body axis, a plurality of forward wings, a plurality of aft wings, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. Each forward wing extends a forward wing plane. Each aft wing extends from an aft wing plane. The aerodynamic propulsors are mounted longitudinally between the plurality of forward wings and plurality of aft wings.

Abstract: A family of Radar energy Absorbing Deformable Low Drag Vortex Generators (RAD-LDVG) is described herein. This family of devices are fabricated in such a way that it can conform to aircraft surface features while reducing radar returns from structural details. Vortex generators (VGs) are typically used to reattach or smooth gross flowfields over aircraft surfaces. By doing so, an airfoil or wing can maintain attached flow at higher angles of attack and/or higher lift coefficients than one without the VGs. These devices are also used to reattach and/or smooth flows that encounter crossflow-induced instabilities and/or adverse pressure gradients on the upper surfaces of wings or near aircraft boattails. Other uses include reduction of buffet, vibration, flutter, cavity resonance or general bluff-body pressure drag reduction. Although conventional rigid VGs do generate vortical aerodynamic structures, two major problems are often experienced: i.) the inability to conform to curved surfaces, ii.

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: 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: 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 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: 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: 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: 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.