Abstract: A ducted-fan unmanned aerial vehicle (UAV) capable of low-energy high-rate maneuvers for both vertical roll control and horizontal pitch control. The maneuverability of the UAV is enhanced by equipping the ducted fans with respective piezoelectric-actuated thrust vectoring flaps. Thrust vector control is achieved by controlling the angular positions of a plurality of thrust vector flaps pivotably coupled at respective outlets of a plurality of ducts having fan rotors at the inlets. Each thrust vectoring flap has only one degree of freedom in the frame of reference of the UAV, namely, rotation about a single axis that is perpendicular to the axis of the duct. The angular position of the flap is controlled by sending electrical signals to a piezoelectric actuator (e.g., a piezoelectric bimorph actuator) having a voltage sufficient to cause the piezoelectric actuator to bend.

Abstract: Layered energy storage devices and methods of forming the layered energy storage devices are disclosed herein. The layered energy storage devices include a first device layer, a second device layer, an intermediate layer, and an interlock structure. The first device layer defines a first electrode, and the second device layer defines a second electrode. The intermediate layer extends between, and electrically separates, the first electrode and the second electrode. The intermediate layer includes an electrolyte material configured to facilitate ion transport between the first electrode and the second electrode. The interlock structure is at least partially defined by the first device layer and also by the second device layer. The interlock structure is configured to operatively interlock the first device layer, the second device layer, and the intermediate layer to one another. The methods include methods of forming the layered energy storage devices.

Abstract: End effectors and methods for gripping a curvilinear sheet of material are disclosed herein. The curvilinear sheet of material defines a first sheet side having a curvilinear first side topography and a second sheet side having a curvilinear second side topography. The end effector includes a negative mating shaped first sheet-engaging surface configured to operatively support the first sheet side and having a curvilinear first sheet-engaging surface topography that corresponds to the curvilinear first side topography. The end effector also includes a second sheet-engaging surface configured to operatively support the second sheet side and having a curvilinear appropriately mating negative shaped second sheet-engaging surface topography that corresponds to the curvilinear second side topography. The end effector further includes an actuation mechanism configured to selectively transition the end effector between an open orientation and a gripping (converging) orientation.

Abstract: Structurally integrated energy supply systems for aircraft and methods of forming the structurally integrated energy supply systems. The structurally integrated energy supply systems include an aircraft structural component, a cell array, and a plurality of energy-producing inserts. The aircraft structural component at least partially defines an interior region. The cell array includes a plurality of cell walls that defies a plurality of elongate cell volumes and is positioned within the interior region. Each energy-producing insert in the plurality of energy-producing inserts is positioned within a corresponding elongate cell volume in the plurality of elongate cell volumes and is configured to produce a corresponding insert electric current. The cell array provides structural load distribution to the aircraft structural component via the plurality of cell walls and contributes to a structural stiffness of the aircraft structural component.

Abstract: A robust amphibious air vehicle incorporates a fuselage with buoyant stabilizers and wings extending from the fuselage. At least one lift fan is mounted in the fuselage. Movable propulsion units carried by the wings are rotatable through a range of angles adapted for vertical and horizontal flight operations.

Abstract: A fastening device may include a first member configured for forceful engagement with a second member. The first member may include a sensor configured to emit at least a first photo-luminescent signal to a detector when at least a predetermined first torque level is applied to the first member when the first and second members are engaged.

Abstract: A robust amphibious air vehicle incorporates a fuselage with buoyant stabilizers and wings extending from the fuselage. At least one lift fan is mounted in the fuselage. Movable propulsion units carried by the wings are rotatable through a range of angles adapted for vertical and horizontal flight operations.

Abstract: A system of transporting micro-cargo incorporates an unmanned aerial vehicle (UAV) having a tether capture device. A tether is connected to and suspends a micro cargo container with a suspension system to vertically extend the tether. The system having a first pickup state and a second flight state with a transition between the first and second states. The first state provides the micro-container unsuspended via the tether from the suspension system. The transition state provides engagement of the tether by the UAV, the tether positioning the micro-cargo container with respect to the capture device which secures the tether. The second state is then entered with the micro-cargo towed by the UAV in cruising flight to its destination.

Abstract: A visual obscurant system for obscuring object from an observer having a field of view (FOV) is disclosed. The system comprises a sensor for detecting characteristics that indicate a presence of the object, a light source for emitting light in an electromagnetic spectrum, a source, and a controller. The source releases an obscurant into atmosphere to create a cloud. The obscurant attenuates a portion of the electromagnetic spectrum. The cloud is positioned within the FOV of the observer so as to obscure the object when the light emitted from the light source is directed towards the cloud. The controller is in communication with at least the sensor and the source. The controller modulates the light source at a frequency sufficient such that the observer interprets the light as being constant when energized.

Abstract: A robust amphibious air vehicle incorporates a fuselage with buoyant stabilizers and wings extending from the fuselage. At least one lift fan is mounted in the fuselage. Movable propulsion units carried by the wings are rotatable through a range of angles adapted for vertical and horizontal flight operations.

Abstract: A visual obscurant system for obscuring object from an observer having a field of view (FOV) is disclosed. The system comprises a sensor for detecting characteristics that indicate a presence of the object, a light source for emitting light in an electromagnetic spectrum, a source, and a controller. The source releases an obscurant into atmosphere to create a cloud. The obscurant attenuates a portion of the electromagnetic spectrum. The cloud is positioned within the FOV of the observer so as to obscure the object when the light emitted from the light source is directed towards the cloud. The controller is in communication with at least the sensor and the source. The controller modulates the light source at a frequency sufficient such that the observer interprets the light as being constant when energized.

Abstract: An apparatus is provided for dynamically controlling airflow behind a carrier aircraft to redirect air flow during an in-flight recovery of an unmanned aerial vehicle (UAV). The apparatus comprises a frame attached to an end portion of an arm member extending from the carrier aircraft. The apparatus comprises a plurality of vanes disposed within the frame. Each vane is controllable between an opened position and a closed position to dynamically modify the airflow behind the carrier aircraft during the in-flight recovery of the UAV. Alternatively, or in addition to, the apparatus comprises a plurality of compressed air jets disposed on the frame, wherein each jet is controllable to provide active airflow to dynamically modify the airflow behind the carrier aircraft during the in-flight recovery of the UAV.

Abstract: An apparatus is provided for dynamically controlling airflow behind a carrier aircraft to redirect air flow during an in-flight recovery of an unmanned aerial vehicle (UAV). The apparatus comprises a frame attached to an end portion of an arm member extending from the carrier aircraft. The apparatus comprises a plurality of vanes disposed within the frame. Each vane is controllable between an opened position and a closed position to dynamically modify the airflow behind the carrier aircraft during the in-flight recovery of the UAV. Alternatively, or in addition to, the apparatus comprises a plurality of compressed air jets disposed on the frame, wherein each jet is controllable to provide active airflow to dynamically modify the airflow behind the carrier aircraft during the in-flight recovery of the UAV.

Abstract: A device includes an interface adapter configured to physically couple to a corresponding interface adapter of a mobile communication device. The device includes a blast sensor configured to generate blast data based on one or more measurements and to communicate the blast data to the mobile communication device via the interface adapter. The device further includes a housing at least partially enclosing the blast sensor and at least partially enclosing the mobile communication device.

Abstract: A system of transporting micro-cargo incorporates an unmanned aerial vehicle (UAV) having a tether capture device. A tether is connected to and suspends a micro cargo container with a suspension system to vertically extend the tether. The system having a first pickup state and a second flight state with a transition between the first and second states. The first state provides the micro-container unsuspended via the tether from the suspension system. The transition state provides engagement of the tether by the UAV, the tether positioning the micro-cargo container with respect to the capture device which secures the tether. The second state is then entered with the micro-cargo towed by the UAV in cruising flight to its destination.

Abstract: A fastening device may include a first member configured for forceful engagement with a second member. The first member may include a sensor configured to emit at least a first photo-luminescent signal to a detector when at least a predetermined first torque level is applied to the first member when the first and second members are engaged.

Abstract: A system and method for providing landing guidance to an aircraft may include an aviation headset having one or more sensors and one or more antennas, a position module configured to determine a position of the headset, and an encoder module for encoding the position information as an audible subchannel. The encoded audible subchannel may be included with voice transmissions via the aircraft radio. A guidance portion may receive the transmission and analyze the encoded audible subchannel to determine the position of the aircraft. Landing guidance may be communicated based on a comparison of the position with a desired glide path.

Abstract: A system of transporting micro-cargo incorporates an unmanned aerial vehicle (UAV) having a tether capture device. A tether is connected to and suspends a micro cargo container with a suspension system to vertically extend the tether. The system having a first pickup state and a second flight state with a transition between the first and second states. The first state provides the micro-container unsuspended via the tether from the suspension system. The transition state provides engagement of the tether by the UAV, the tether positioning the micro-cargo container with respect to the capture device which secures the tether. The second state is then entered with the micro-cargo towed by the UAV in cruising flight to its destination.

Abstract: A fastening device may include a first member configured for forceful engagement with a second member. The first member may include a sensor configured to emit at least a first photo-luminescent signal to a detector when at least a predetermined first torque level is applied to the first member when the first and second members are engaged.

Abstract: A system and method for transmitting an information signal through a radio-frequency opaque barrier are disclosed. A transmitter is positioned on a first side of the barrier and a re-transmitter is positioned on a second side of the barrier. The transmitter includes a controller that modulates a received information signal with a carrier signal and forwards the modulated information signal to a vibration generator which converts the received electrical signal to a corresponding vibration signal. The re-transmitter includes an accelerometer that detects vibration signals and produces a corresponding electrical signal and a controller coupled to the accelerometer which receives the electrical signal from the accelerometer and demodulates the information signal included within the electrical signal received from the accelerometer.