21144 results about "Flight vehicle" patented technology

A tethered unmanned aerial vehicle (“UAV”) may be outfitted with a sensor payload for data gathering. The tethered UAV may be tethered to a ground station for constricting the flight space of the UAV while also providing the option for power delivery and/or bidirectional communications. The tethered UAV's flight path may be extended by introducing one or more secondary UAVs that cooperate to extend the horizontal flight path of a primary UAV. The ground station, which may be coupled with the tethered aerial vehicle, may comprise a listening switch configured to determine a condition of the tether such that the supply of power to the tether may be terminated when tether damage or a tether severance is detected.

A rechargeable battery energized unmanned aerial vehicle having surveillance capability and an ability to clandestinely collect propulsion and other energy needs from a conveniently located and possibly enemy owned energy transmission line. Energy collection is by way of a parked vehicle engagement with the transmission line in a current flow dependent, magnetic field determined, rather than shunt, voltage dependent, conductor coupling. Surveillance during both a parked or docked condition and during aerial vehicle movement is contemplated.

Several improvements to an aircraft turbine engine and Auxiliary Power Unit (APU) are disclosed, as well as methods of using these improvements in routine and emergency aircraft operations. The improvements comprise the addition of cockpit-controllable clutches that can be used to independently disconnect the engine's integrated drive generator (IDG), engine driven pump (EDP), fuel pump, and oil pump from the engine gearbox. These engine components may then be connected to air turbines by the use of additional clutches and then powered by the turbines. Similar arrangements are provided for the APU components. Cranking pads, attached to various engine and APU components, are disclosed to provide a means for externally powering the components for testing purposes and to assist with engine and APU start. Detailed methods are disclosed to use the new components for routine ground-testing and maintenance and for the enhancement of flight safety, minimization of engine component damage, and extension of engine-out flying range in the case of an emergency in-flight engine shutdown.

An aircraft engine turbine frame includes a first structural ring, a second structural ring disposed co-axially with and radially spaced inwardly of the first structural ring about a centerline axis. A plurality of circumferentially spaced apart struts extend between the first and second structural rings. Forward and aft sump members having forward and aft central bores are fixedly joined to forward and aft portions of the turbine frame respectively. A frame connecting means for connecting the engine to an aircraft is disposed on the first structural ring. The frame connecting means may include a U-shaped clevis. The frame may be an inter-turbine frame axially located between first and second turbines of first and second rotors of a gas turbine engine assembly. An axial center of gravity of the second turbine passes though or very near a second turbine frame bearing supported by the aft sump member.

The present invention relates to a system for retrieving data from remote difficult to reach terrain, such as wilderness areas, etc. and in particular to a system comprised of one or more surface based data collectors in communication with one or more wireless transceivers adapted to transmit the collected data to an unmanned aerial vehicle adapted to fly within a predetermined distance from the data collector and receive data collected therefrom. The present invention further relates to an unmanned aerial vehicle adapted to fly a flight pattern relative to a moveable surface object or for controlling the position of a moveable surface object relative to the flight path of the unmanned aerial vehicle. Finally, the present invention relates to an improved unmanned aerial vehicle having airframe structural elements with electrical circuits adhered to the surfaces of the structural elements.

A vertical take-off and landing vehicle comprised of a fuselage having a front, a rear, and two lateral sides and a set of four thrusters set to the front, the left, the right, and the rear of said fuselage. The thrusters are either independently powered thrusters or could utilize a single power source. The thrusters, which are ducted fan units capable of providing a vertically upward force to the aircraft, are provided with such redundancy that the aircraft can hover with up to two thrusters inoperative. The thrusters are comprised of a set of two counter rotating propellers both of which creates lift. The two counter rotating propellers cancel out the torque effect normally created by using only one propeller. The Ducted fan units being movable between a first position in which they provide vertical lift and a second position in which they provide horizontal thrust using a set of servos and gears.

A landing pad receives and stores packages delivered from an aerial vehicle are awaiting pickup from an aerial vehicle. The landing pad can be placed outside of a window and can contain a transmitter for sending out an identification signal via radio frequency to aid aerial vehicles in finding the landing pad. The landing pad contains a landing platform with a trapdoor that leads to a storage compartment. The trapdoor can be configured to only open when it receives a signal from an authorized aerial vehicle. The storage compartment can be accessed via a storage compartment door which can contain a locking mechanism. The storage compartment can be climate controlled. The landing pad can also have a transmitter that emits sounds to discourage animals from nesting on or near the landing pad. The landing pad can also include a solar power generator as a source of electrical energy.

Systems and methods are provided for swapping the battery on an unmanned aerial vehicle (UAV). The UAV may be able to identify and land on an energy provision station autonomously. The UAV may take off and/or land on the energy provision station. The UAV may communicate with the energy provision station. The energy provision station may store and charge batteries for use on a UAV.

Systems, methods, and devices are provided for providing flight response to flight-restricted regions. The location of an unmanned aerial vehicle (UAV) may be compared with a location of a flight-restricted region. If needed a flight-response measure may be taken by the UAV to prevent the UAV from flying in a no-fly zone. Different flight-response measures may be taken based on the distance between the UAV and the flight-restricted region and the rules of a jurisdiction within which the UAV falls.

The disclosed invention consists of several improvements to well known Quad Tilt-Rotor (QTR) aircraft. The first is that during a wing-borne flight, one pair of tilt-rotors, which can be substantially larger than the other pair, is feathered and stopped. This can promote vehicle aerodynamic efficiency and can be utilized to increase vehicle speed. Second is that the wings are not attached to the fuselage at a fixed angle of incidence like on conventional QTR aircraft, but can also be tilted in respect to the fuselage independently of the tilt-rotors. Furthermore, each rotor and each wing can be tilted with respect to fuselage to any tilt-angle without limit, which gives the vehicle unprecedented ability to position the fuselage in any attitude in respect to the vehicle direction of flight.

The invention relates to remote control of an unmanned aerial vehicle, UAV, (100) from a control station (110) by means of a wireless command link (115). The UAV (100) may be controlled in an autonomous mode wherein it flies according to a primary route (R1, R1') defined by a first set of predefined waypoints (WP1-WP8, IP). The UAV (100) may also be controlled in a manual mode wherein it flies according to an alternative primary route (R1') defined in real-time by control commands received via the wireless command link (115). Flight control parameters are monitored in both modes, and in case a major alarm condition occurs, the UAV (100) is controlled to follow an emergency route (R2') defined by a second set of predefined waypoints (HP1-HP7, TP1-TP9, IP). Particularly, a major alarm condition is activated if an engine failure is detected. Then, the emergency route (R2') involves flying the UAV (100) to an air space above a termination waypoint (TP9) on the ground at which it is estimated that the vehicle's (100) flight may be ended without injuring any personnel or causing uncontrolled material damages.

The present invention relates to an unmanned flying vehicle using a PCB including a main board controlling power supply and flying operation, a motor rotating a propeller by changing electric energy into mechanical energy, a PCB frame changing a signal from a remote controller and connecting the main board with the motor, a propeller generating an impellent force by from rotation by the motor, a receiver receiving a control signal of the remote controller, and a remote controller controlling a motor rotation speed of a quadrotor and direction change, and accordingly, the structure of the unmanned flying vehicle can be simplified so that the flying vehicle can be down-sized and light-weighted, and assemblability can be improved.

A system and method for enhancing distribution logistics and surveillance ranges with unmanned aerial vehicles (UAV) and at least one dock in a dock network. The UAV remains in communication with the dock for enhancing distribution logistics of at least one package and increasing the range of surveillance for the unmanned aerial vehicle. From the dock, the UAV delivers the package to a destination point, obtains the package from a pick up point, recharges the unmanned aerial vehicle throughout the network of docks, and increases the range of distribution and surveillance. A logistics software controls the delivery and surveillance. A wireless communication device enables communication between the UAV and the dock. Light indicators indicate status of the package and the operational status of the UAV. A camera captures an image of the package in the dock. A motion detector detects the UAV for regulating access for loading/unloading and docking.

A method of management of a wireless device in an aircraft may include transitioning the wireless device from a first mode to a second mode based on data that is indicative of a change in flight condition of the aircraft. One of these modes may be a state of the device in which a transmitter of the device is deactivated and the other mode may be a state of the device in which the transmitter is activated. The data indicative of the change in flight condition may either be downloaded to the device from an external source, acquired from a sensor(s) embedded in the device, or may be determined based on both the data acquired by the sensor(s) and data downloaded to the device.

A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in least two dimensions relative to the horizontal during takeoff. An aerial vehicle which uses a rotating platform of engines in fixed relationship to each other and which rotates relative to the wings of the vehicle for takeoff and landing.

An air vehicle incorporating a hybrid propulsion system. The system includes a gas turbine engine as a first motive power source, and one or more battery packs as a second motive power source. Through selective coupling to a DC electric motor that can in turn be connected to a bladed rotor or other lift-producing device, the motive sources provide differing ways in which an aircraft can operate. In one example, the gas turbine engine can provide operation for a majority of the flight envelope of the aircraft, while the battery packs can provide operation during such times when gas turbine-based motive power is unavailable or particularly disadvantageous. In another example, both sources of motive power may be decoupled from the bladed rotor such that the vehicle can operate as an autogyro.

An apparatus and method of charging and housing of an unmanned vertical take-off and landing (VTOL) aircraft is disclosed. The apparatus includes an accommodator to accommodate an aircraft, a landing platform on which the aircraft lands, a housing portion to monitor state data by housing or charging the aircraft, and a sensor to assist in landing of the aircraft by allowing the aircraft to communicate with the apparatus. The apparatus enhances operational efficiency by reducing a travel time of the aircraft.

Methods are provided for generating a flight plan for an aerial vehicle equipped with a surveillance module by using a control unit having a display device. A method comprises graphically identifying, on a map displayed on the display device, a desired target for the surveillance module. A flight plan generated based on the desired target such that a predicted camera path for the surveillance module overlaps the desired target.

An aircraft having a vertical take-off and landing (VTOL) propulsion system. The aircraft includes a fuselage, the VTOL propulsion system, at least one forward thruster, a power source used for both the VTOL propulsion system and forward thruster, fore and aft wings and a plurality of spars attached to and spanning the space between the two wings. The VTOL propulsion system includes a plurality of VTOL cells (including a motor, motor controller, and propeller) attached in a spaced relation along each spar. The VTOL cells are used exclusively for vertical flight or hovering and are powered down as the aircraft develops forward flight velocity and corresponding wing lift. During forward flight the VTOL propellers are articulated to allow the aircraft to take on a low drag configuration. The present invention is suitable for use in manned or un-manned aircraft of any scale.

A platform for interchangeably mounting a payload to a base support is provided. In one aspect, the platform comprises: a support assembly configured to be releasably coupled to a payload via a first coupling and configured to control a spatial disposition of the payload; and a mounting assembly configured to be releasably coupled via a second coupling to a plurality of types of base supports selected from at least two of the following: an aerial vehicle, a handheld support, or a base adapter mounted onto a movable object.

An embodiment of the invention is directed to a platform for launching and/or capturing an unmanned air vehicle (UAV), particularly a small UAV. The launch/capture platform includes a frame, a floor attached to the frame that is capable of supporting the UAV, means for acquiring and tracking the UAV in flight, a connector and a connector controller, connecting the platform to an external support structure, providing a controllable, adaptive motion of the platform in response to approaching UAV position and attitude, means for launching the UAV from the platform and for capturing an in-flight UAV to the platform, and means for locking down the UAV between the capture and launch of the UAV. Another embodiment of the invention directed to a method for capturing a small, in-flight UAV involves providing a UAV capture platform, providing a UAV capturing means as an integrated component of the platform, providing means for determining in real-time the relative location of an engaging portion of the capturing means with respect to an approaching in-flight UAV, providing means for automatically maneuvering the engaging portion of the capturing means with respect to at least one of a position and an attitude of the approaching in-flight UAV, capturing the UAV, and securing the captured UAV to the capture platform.