Abstract: Devices, systems, and techniques for generating a graphical user interface including a three-dimensional virtual containment space for flight of an unmanned aerial vehicle (UAV) are described. In some examples, the graphical user interface may be generated based on user input defining a virtual boundary for the flight of the UAV.

Abstract: The present invention provides a catch and snare system for an unmanned aerial vehicle comprising: (a) a detection system, (b) a deployment system in communication with the detection system, (c) a capture system placed at an interference position by the deployment system, wherein the capture system comprises a net, a plurality of foam deploying canisters attached to the net for deploying foam, and at least one canister for deploying a decelerating parachute attached to the net, wherein the foam prevents the release of chemical or biological agents from the captured unmanned aerial vehicle, and (d) a descent system to bring the capture system and a captured unmanned aerial vehicle back to earth.

Abstract: A manipulator arm system on a ducted air-fan UAV is disclosed herein. The target site may be accurately located by the UAV, and the manipulator system may accurately locate the payload at the target site. The manipulator arm may select tools from a toolbox located on-board the UAV to assist in payload placement or the execution of remote operations. The system may handle the delivery of mission payloads, environmental sampling, and sensor placement and repair.

Abstract: A transforming unmanned aerial-to-ground vehicle assembly comprising: an aerodynamic flying assembly comprising an unmanned aerial vehicle integrated with an unmanned ground vehicle, a power unit shared by the unmanned aerial vehicle and the unmanned ground vehicle, vehicle controls shared by the unmanned aerial vehicle and the unmanned ground vehicle, a disengagement mechanism to separate the unmanned ground vehicle from the unmanned aerial vehicle, one or more manipulator arms located on either the unmanned aerial vehicle or the unmanned ground vehicle, and landing gear.

Abstract: The present invention provides apparatus and methods for accurate guidance of small munitions to a target. The guidance for the small munition is mainly provided by a device external to the small munition, such as an unmanned aerial vehicle (UAV). The UAV may provide external guidance commands by use of a command transmitter to the small munition. The small munition is equipped to receive the guidance commands and consequently use a maneuvering mechanism to react to the guidance commands. The UAV may determine a successful release point of the small munition and track a flight path from a release point toward the target of the small munition using a passive sensor mounted in a gimbaled mount, which is controlled by use of a closed-loop control system. The UAV may be controlled by a ground control device, such as an operator control unit (OCU), to release small munitions.

Abstract: A launch and capture system for capturing a vertical take-off and landing (VTOL) vehicle having a thruster and a duct configured to direct airflow generated by the thruster includes a capture plate and an extension. The capture plate is configured to alter the airflow and generate a force attracting the duct to the capture plate. The extension is coupled to the capture plate, and is configured to at least facilitate holding the VTOL vehicle against the capture plate.

Abstract: Systems and methods for inertially controlling a hovering unmanned aerial vehicle (HUAV) are provided. One inertial controller includes a frame and a sensor for detecting a change in an orientation and/or motion of the frame with respect to a predetermined neutral position. The inertial controller also includes a processor for generating commands to the HUAV to modify its current orientation and/or motion in accordance with the change. A system includes the above inertial controller and a sensor for determining a second change for an orientation and/or motion for the HUAV based on the change, and a processor for generating a signal commanding an HUAV control system to orient and/or move the HUAV in accordance with the second change. One method includes detecting a change in an orientation and/or motion of an inertial controller frame and commanding the HUAV to modify its current orientation and/or motion in accordance with the change.

Abstract: Methods and systems are provided for attaching and detaching a payload device to and from, respectively, a gimbal system without requiring use of a mechanical tool. The gimbal system includes a gimbal assembly that includes a payload socket arranged to attach a payload device to the gimbal assembly. The payload socket is preferably arranged to allow any of a plurality of payload devices to attach to and detach from the payload socket without requiring use of a mechanical tool.

Abstract: Systems and methods for inertially controlling a hovering unmanned aerial vehicle (HUAV) are provided. One inertial controller includes a frame and a sensor for detecting a change in an orientation and/or motion of the frame with respect to a predetermined neutral position. The inertial controller also includes a processor for generating commands to the HUAV to modify its current orientation and/or motion in accordance with the change. A system includes the above inertial controller and a sensor for determining a second change for an orientation and/or motion for the HUAV based on the change, and a processor for generating a signal commanding an HUAV control system to orient and/or move the HUAV in accordance with the second change. One method includes detecting a change in an orientation and/or motion of an inertial controller frame and commanding the HUAV to modify its current orientation and/or motion in accordance with the change.

Abstract: A tether continuous energy supply system for an unmanned aerial vehicle comprising: a ground station, a ground station energy system, a spool coupled to the ground station energy system at a rotating joint, a tether that is wound about the spool, wherein a first end of the tether is coupled to the rotating joint, a tension control motor coupled to both the spool and the ground station energy system, an unmanned aerial vehicle coupled to a second end of the tether, a UAV energy system, a fluid that moves throughout the tether continuous energy supply system, a tension control system that receives and transmits signals from a plurality of sensors contained within the tether continuous energy supply system, and a distributed controls system that receives and transmits signals from the plurality of sensors contained within the tether continuous energy supply system.

Abstract: The present invention provides apparatus and methods for accurate guidance of small munitions to a target. The guidance for the small munition is mainly provided by a device external to the small munition, such as an unmanned aerial vehicle (UAV). The UAV may provide external guidance commands by use of a command transmitter to the small munition. The small munition is equipped to receive the guidance commands and consequently use a maneuvering mechanism to react to the guidance commands. The UAV may determine a successful release point of the small munition and track a flight path from a release point toward the target of the small munition using a passive sensor mounted in a gimbaled mount, which is controlled by use of a closed-loop control system. The UAV may be controlled by a ground control device, such as an operator control unit (OCU), to release small munitions.

Abstract: An air data system and method for a ducted fan air-vehicle is described. The air data system includes a plurality of air pressure sensors placed around a lip of an air duct of the ducted fan air-vehicle. The air data system calculates the speed and direction of airflow surrounding the ducted fan air-vehicle based on pressure data measured across the lip of the air duct. Additionally, the air data system may estimate forces generated by airflow surrounding the air-vehicle.

Abstract: A transforming unmanned aerial-to-ground vehicle assembly comprising: an aerodynamic flying assembly comprising an unmanned aerial vehicle integrated with an unmanned ground vehicle, a power unit shared by the unmanned aerial vehicle and the unmanned ground vehicle, vehicle controls shared by the unmanned aerial vehicle and the unmanned ground vehicle, a disengagement mechanism to separate the unmanned ground vehicle from the unmanned aerial vehicle, one or more manipulator arms located on either the unmanned aerial vehicle or the unmanned ground vehicle, and landing gear.

Abstract: The present invention provides a catch and snare system for an unmanned aerial vehicle comprising: (a) a detection system, (b) a deployment system in communication with the detection system, (c) a capture system placed at an interference position by the deployment system, wherein the capture system comprises a net, a plurality of foam deploying canisters attached to the net for deploying foam, and at least one canister for deploying a decelerating parachute attached to the net, wherein the foam prevents the release of chemical or biological agents from the captured unmanned aerial vehicle, and (d) a descent system to bring the capture system and a captured unmanned aerial vehicle back to earth.

Abstract: Self-leveling legs are used to accommodate landing a ducted fan hovercraft on a sloped surface such as a roof-top. These legs move to accommodate a variation of slope within their range of motion irrespective to the azimuth of the vehicle body. The configuration and operation of the landing legs allow the hovercraft to land in a stable fashion with the hovercraft vehicle body maintained in a vertical orientation. The basic kinematics of the present invention is the displacement of one landing leg upwards is connected by a horizontal member to the opposite leg and displaces it downwards, and visa-versa. Planar surface contact is accomplished by the unique curvature of the legs and the splay of the legs from the vehicle body.

Abstract: The present invention provides methods and systems for adjusting video quality outputted by an aerial vehicle to manage the data stream bandwidth to match the needs of each mission segment. A mission segment is monitored in order to determine a preferred video quality of service. A quality of service is set based on the monitored mission segment. The quality of service is selectively altered based on a change of at least one of a mission segment or an environmental condition.

Abstract: A system for illuminating an object of interest includes a platform and a gimbaled sensor associated with an illuminator. The gimbaled sensor provides sensor data corresponding to a sensed condition associated with an area. The gimbaled sensor is configured to be articulated with respect to the platform. A first transceiver transceives communications to and from a ground control system. The ground system includes an operator control unit allowing a user to select and transmit to the first transceiver at least one image feature corresponding to the object of interest. An optical transmitter is configured to emit a signal operable to illuminate a portion of the sensed area proximal to the object of interest. A correction subsystem is configured to determine an illuminated-portion-to-object-of-interest error and, in response to the error determination, cause the signal to illuminate the object of interest.

Abstract: A Micro Air-Vehicle (MAV) starting system that provides the combined functions of: packing protection of sensitive vehicle components, a mechanical starting assembly, and a launch pad. The preferred embodiment comprises a container and a container lid with the MAV clamped to the lid. Also disposed on the container lid is a starting assembly. The lid which doubles as a launching pad with the attached MAV is removed from the container, placed on the ground, the MAV is started with the starting mechanism and launched. The arrangement minimizes the physical risk to the operator, minimizes weight of the total MAV system, consumes minimum space in the operators transport system, and eliminates dependence on supply lines for battery replacement or charging.

Abstract: A dual ducted fan arrangement in which the duct components, engine, and avionics/payload pods are capable of being quickly disassembled to fit within common backpacking systems. Each duct is identical in fan, stator, and control vane design. Assembly connections between ducted fans and electronic modules are also identical. An engine or APU drives the dual ducted fans through a splined shaft to a differential or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms on each of the splined shafts between the differential and ducted fans. In the electric motor case relative speed is through electronic speed control. The fans are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.

Abstract: A Micro Air-Vehicle (MAV) starting system that provides the combined functions of: packing protection of sensitive vehicle components, a mechanical starting assembly, and a launch pad. The preferred embodiment comprises a container and a container lid with the MAV clamped to the lid. Also disposed on the container lid is a starting assembly. The lid which doubles as a launching pad with the attached MAV is removed from the container, placed on the ground, the MAV is started with the starting mechanism and launched. The arrangement minimizes the physical risk to the operator, minimizes weight of the total MAV system, consumes minimum space in the operators transport system, and eliminates dependence on supply lines for battery replacement or charging.