Abstract: An aircraft including a wing system, a plurality of control surfaces, a camera mounted on a camera pod, and a control system. The camera pod is configured to vary the orientation of the camera field of view only in yaw, relative to the aircraft, between a directly forward-looking orientation and a side-looking orientation. The control system controls the control surfaces such that they induce a significant aircraft yaw causing an identified target to be within the field of view of the camera with the camera in the directly forward-looking orientation.

Abstract: A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) system including: a rearward facing tang extending from a rear fuselage portion of a VTOL UAV; one or more metallic contacts disposed on an exterior surface of the tang; a UAV pod including a landing surface; and an opening disposed in the landing surface to receive the tang.

Abstract: In one possible embodiment, a system capable of a self-propagating data link includes an unmanned vehicle having a data link transceiver and at least one deployable data link transceiver. The unmanned vehicle having a deployment means for deploying the at least one deployable data link transceiver.

Abstract: A system including a remote server connected over a network to a battery charger is configured to track usage of rechargeable batteries. Values of various sensed parameters of a battery, such as temperature, charge, current, and water level are stored with the battery and uploaded to the remote server, either wirelessly or through the network, and either directly from the battery or by way of the battery charger when the battery is coupled to the battery charger. The remote server operates to determine the condition, value and warranty of the battery based on the sensed parameters and on the user history of the battery. Alerts and warnings can be forwarded to the user and/or an enterprise manager or shop manager in the case of enterprise vehicles such as warehouses operating multiple electric forklifts, or rental car agencies, so that multiple rechargeable batteries can be readily tracked, monitored and maintained.

Abstract: Methods of and apparatus for removing heat generated by cells of a battery pack. The methods and apparatus may employ one or more fan modules disposed between or next to cells of the battery pack, or one or more fans directly mounted to the battery pack or battery pack case housing the cells. Further, a motor controller isolation system operates to electrically isolate the motor controller of the electric vehicle when the battery pack is being charged. The motor controller isolation system may be integrated with the integrated battery pack and thermal and ventilation system. The integrated system, or “integrated battery unit (IBU),” is preferably manufactured in a manner that requires no, modifications to the electric vehicle in which the IBU is installed.

Abstract: A motor assembly that includes a motor (102) having a rotatable shaft, a hub coupled to the rotatable shaft, the hub having a propeller indexer to receive a propeller (104), when the propeller is present, a sensor trigger rotatable with the shaft (100) and positioned at a propeller offset angle ?PROP from the propeller indexer, and a sensor coupled to the motor and positioned to detect the sensor trigger so that the propeller indexer may be positioned at the propeller offset angle ?PROP from the sensor through rotation of the shaft so that said sensor is proximate to the sensor trigger.

Abstract: A water-tight or air-tight accessible compartment has a removable hatch sealed at the edge with elastically conformable opposing seals, with elongate communication elements extending into the compartment between the opposing seals, seals conforming to the topology formed between the compartment edge and the elongate communication elements.

Abstract: An actuator controller with a power supply that steps down a high voltage for use by remote auxiliary loads in an aircraft is provided. A high voltage power bus running through the aircraft may use high gage or smaller diameter wiring, resulting in weight savings in the power bus. A control network running through the aircraft may use fiber optic cabling, providing further weight reductions. An actuator controller may receive the high voltage from the power bus and provide a lower voltage to a remote device. The actuator controller may facilitate communication between the control network and the remote device. The integration of control and power supply may enhance endurance, reliability, and enable localized calibration of the remote device. Modular wing components may include interface controllers, high and low power busswork, and remote devices. The modular wing components may include power and control interconnections.

Abstract: In one implementation, a method is provided for contactor monitoring and control in electric vehicle supply equipment, which includes updating an open error count and a close error count based on a detected condition of the contactor. The method also includes determining a detected state of the contactor by comparing the open error count and the close error count to maximum and minimum values. The method further includes performing at least one of controlling the state of the contactor based on the determined contactor state, or providing a visual indicator based on the determined contactor state.

Abstract: A portable electric vehicle support equipment (EVSE) unit is formed as a cord of plural insulated conductors and a flexible outer sheath enclosing said plural insulated conductors. The cord includes an EVSE docking connector on a docking end of the cord and a utility plug on a utility end of the cord, said cord being divided into a docking section terminated at said docking connector and a utility section terminated at said utility connector. The cord further includes an in-line EVSE controller and a housing enclosing said controller, said housing sealed with said flexible outer sheath and disposed at an intermediate section of said cord between said docking and utility sections.

Abstract: In one possible embodiment, an amphibious unmanned aerial vehicle is provided, which includes a fuselage comprised of a buoyant material. Separators within the fuselage form separate compartments within the fuselage. Mounts associated with the compartments for securing waterproof aircraft components within the fuselage. The compartments each have drainage openings in the fuselage extending from the interior of the fuselage to the exterior of the fuselage.

Abstract: A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.

Abstract: An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.

Abstract: A portable electric vehicle supply equipment (EVSE) kit or system includes a docking connector having a docking head engagable with the charging port of an electric vehicle and a barrel or handle fixed to the docking head and having a barrel electrical connector. An EVSE controller is embedded within the docking connector. An electric power cable has a first connector for engaging the barrel electrical connector and a second connector at an opposite end of the cable for connection to an electrical utility receptacle. The embedded EVSE controller enables the docking connector to function as an EVSE unit.

Abstract: A charging system detachably drawing from a power source comprising: (a) an electrical output configuration; (b) an electrical input configuration; and (c) an energy store configuration; and methods of provisioning the energy store, the charging system, and electric vehicle charger devices.

Abstract: A method of driving an isolated converter includes opening a first bi-directional switch on an input side of a transformer, accepting current into a resonant capacitor connected across the first bi-directional switch to reduce voltage across the first bi-directional switch in response to said opening the first bi-directional switch, reversing current out of the resonant capacitor, and closing the first bi-directional switch as voltage across the first bi-directional switch is approximately zero volts.

Abstract: A water-tight or air-tight accessible compartment has a removable hatch sealed at the edge with elastically conformable opposing seals, with elongate communication elements extending into the compartment between the opposing seals, seals conforming to the topology formed between the compartment edge and the elongate communication elements.

Abstract: An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515).

Abstract: In one possible embodiment, a UAV payload module retraction mechanism is provided including a payload pivotally attached to a housing. A biasing member is mounted to bias the payload out of the housing and a winch is attached to the payload. An elongated flexible drawing member is coupled between the housing and the winch, the elongated drawing flexible member being capable of being drawn by the winch to retract the payload within the housing.

Abstract: In electric vehicle supply equipment (EVSE), interruption of charging due to overheating is prevented by adjusting the pulse duty cycle on the control pilot conductor communicating the maximum allowed current level to the electric vehicle, the adjustment being performed whenever the EVSE temperature exceeds a predetermined threshold temperature below the maximum operating temperature as a function of the approach of the temperature to the maximum operating temperature.