597 results about "Flight direction" patented technology

An aerial reconnaissance camera and method provides for generating a first image of the terrain of interest with the camera pointing angle oriented or rotated about an azimuthal axis some angular amount (theta1) to a first, typically forward orientation, i.e., forward of a cross-line of flight direction. An image is obtained of the ground at this orientation. Then the camera is rotated about the azimuthal axis to new angular value (theta2), which will typically be aft of the cross line of flight direction. An image is generated at this value. The camera is then rotated back to the value of theta1, and a second image in the forward orientation is generated. The camera is then rotated again to the value of theta2 and another image in the aft orientation is generated. This process of rotating the camera about the azimuthal axis and generating images in forward and aft orientations continues over and over. Eventually, as the aircraft flies past the terrain of interest, any given location in the terrain of interest will have been imaged from two different perspectives-forward and aft. The motion of the aircraft during the interim in combination with the values of theta1 and theta2 provide the high baseline for the stereo image pairs. By selection of suitable values for the angular separation of theta1 and theta2 (such as theta1=+10 degrees and theta2=-10 degrees) the result will be pairs of images of the terrain of interest having a large baseline, producing truly high aspect stereo images from a single camera. The method also works in a similar fashion by rotation back and forth about the pitch axis and imaging the terrain in forward oblique and aft oblique orientations.

An aircraft including an airframe having a fuselage which extends longitudinally, and having fixed wings including a main wing, a horizontal tail wing and a vertical tail wing. A propeller-rotor torque transmission has a bevel gear which transmits the rotation of an input shaft simultaneously to a propeller shaft and to a rotor shaft. An engine gearbox supplies the above-mentioned input shaft with rotationalal motive power. The aircraft further includes a propeller collective pitch controller, a rotor collective pitch controller, an engine power controller which controls the output of the above-mentioned engine gearbox for the purpose of changing the rotational speed of the input shaft, and a flight control system having a directional (yaw) control system which controls the flight direction of the aircraft by controlling the positions of the above-mentioned control surfaces.

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.

An electronic device for controlling an unmanned aerial vehicle (UAV) displays a portion of a 3D virtual scene of a monitored area of the UAV on a screen, and displays a representation icon of the UAV on a preset position of the screen. The electronic device further converts an operation signal to a control signal, and sends the control signal to control movements of the UAV. After receiving flight data from the UAV, the electronic device recognizes movements of the UAV according to the flight data, and determines adjustments to the portion of the 3D virtual scene, to control displaying of the 3D virtual scene based on the recognized movements while maintaining the representation icon of the UAV on the preset position and maintaining a direction the user presumed to be viewing the 3D virtual scene the same as a flight orientation of the UAV.

A miniature, unmanned aircraft for acquiring and / or transmitting data, capable of automatically maintaining desired airframe stability while operating by remote directional commands. The aircraft comprises a fuselage and a wing, a piston engine and propeller, a fuel supply, at least one data sensor and / or radio transceiver, a microprocessor disposed to manage flight, a radio transceiver for receiving remotely generated flight direction commands, a GPS receiver, a plurality of control surfaces and associated servomechanisms, for controlling flight stabilization and direction, roll, pitch, yaw, velocity, and altitude sensors. The microprocessor uses roll, pitch, yaw, and altitude data to control attitude and altitude of the aircraft automatically, but controls flight direction solely based on external commands. The aircraft does not exceed fifty-five pounds.

An unmanned aerial vehicle (UAV) includes a driving unit and a control unit. The control unit detects a human figure in an image of a scene of a monitored area, determines coordinate differences between the scene image's center and the figure image's center, and determines a tilt direction and a tilt angle of a lens of the image capture unit based on the coordinate differences. If the tilt angle falls within an allowable rotation range of the lens, the control unit controls the driving unit to directly rotate the lens by the tilt angle along the tilt direction. Otherwise, the control unit controls the driving unit to rotate the lens by a threshold angle along the tilt direction, and further controls the driving unit to adjust a flight orientation and a flight height of the UAV until the figure image's center superposes the scene image's center.

The invention discloses an unmanned aerial vehicle trajectory optimization method and device based on deep reinforcement learning and an unmanned aerial vehicle. The method comprises the steps: constructing a reinforcement learning network in advance, and generating state data and action decision data in real time in a flight process of an unmanned aerial vehicle; and taking the state data as input, the action decision data as output and the instantaneous energy efficiency as reward return, optimizing strategy parameters by utilizing a PPO algorithm, and outputting an optimal strategy. The device comprises a construction module, a training data collection module and a training module. The unmanned aerial vehicle comprises a processor, and the processor is used for executing the unmanned aerial vehicle trajectory optimization method based on deep reinforcement learning. The method has the capability of carrying out autonomous learning from accumulated flight data, can intelligently determine the optimal flight speed, acceleration, flight direction and return time in an unknown communication scene, concludes a flight strategy with the optimal energy efficiency, and is higher in environment adaptability and generalization capability.

The invention relates to a time-of-flight mass spectrometer for injection of the ions orthogonally to the time-resolving axis-of-flight component, with a pulser for acceleration of the ions of the beam in the axis-of-flight direction, preferredly with a velocity-focusing reflector for reflecting the ion beam and with a flat detector at the end of the flight section. The invention consists of using, both for acceleration in the pulser and for reflection in the reflectors, a gridless optical system made up of slit diaphragms which can spatially focus the ions onto the detector in the direction vertical to the directions of injection and flight axis, but which does not have any focusing or deflecting effect on the other directions. For some reflector geometries it is essential to use an additional cylindrical lens for focusing, and for other reflector geometries the use of such a lens may be advantageous.

The invention relates to a time-of-flight mass spectrometer for injection of the ions orthogonally to the time-resolving axis-of-flight component, with a pulser for acceleration of the ions of the beam in the axis-of-flight direction, preferably with a velocity-focusing reflector for reflecting the ion beam and with a flat detector at the end of the flight section. The invention consists of using, both for acceleration in the pulser and for reflection in the reflectors, a gridless optical system made up of slit diaphragms which can spatially focus the ions onto the detector in the direction vertical to the directions of injection and flight axis, but which does not have any focusing or deflecting effect on the other directions. For some reflector geometries it is essential to use an additional cylindrical lens for focusing, and for other reflector geometries the use of such a lens may be advantageous.

The invention discloses a navigation control method of unmanned aerial vehicle group collaborative work. Each unmanned aerial vehicle determines the respective flight direction and the flight distance according to current position information and target position information; an unmanned aerial vehicle group collaborative task sequence is planned and the corresponding navigation path of each unmanned aerial vehicle is automatically generated according to the flight direction and the flight distance determined by each unmanned aerial vehicle in the unmanned aerial vehicle group; and each unmanned aerial vehicle flies to the target position for performing the work task according to the task sequence and the navigation path. According to the navigation method, the unmanned aerial vehicle group can perform autonomous flight control according to the calculated flight direction and the flight distance and plan the flight path of the whole unmanned aerial vehicle group in advance so that smooth proceeding of collaborative work can be ensured, and performing the more complex work task by using collaborative work between multiple unmanned aerial vehicles can be guaranteed.

A multi-reflecting TOF mass analyser has two parallel, gridless ion mirrors each having an elongated structure in a drift direction (Z). These ion mirrors provide a folded ion path formed by multiple reflections of ions in a flight direction (X), orthogonal to the drift direction (Z). The analyser also has a further gridless ion mirror for reflecting ions in the drift direction (Z). In operation ions are spatially separated according to mass-to-charge ratio due to their different flight times along the folded ion path and ions having substantially the same mass-to-charge ratio are subjected to energy focusing with respect to the flight and drift directions.

The invention belongs to the technological field of agricultural plant protecting information processing, and discloses an electric fence monitoring method for unmanned aerial vehicle plant protecting operations. An agricultural plant protecting operation plot has boundaries and to ensure the security and efficiency of a plant protection unmanned aerial vehicle in executing the operations of plant protecting, the plant protection unmanned aerial vehicle should not trespass the boundaries. Therefore, it is necessary to monitor the electric fence for the unmanned aerial vehicle plant protecting operations. The method in doing so comprises the following steps: 1) generating in a dynamic manner a security boundary; 2) establishing a dual link communication system based on an unmanned aerial vehicle radio station and a 4G module; and 3) determining the boundary trespassing and the tendency of trespassing of the unmanned aerial vehicle so as to raise the detection efficiency of the boundary trespassing of the unmanned aerial vehicle. According to the invention, it is possible to make pre-warnings when there is tendency for the unmanned aerial vehicle to trespass the boundary so that the user of the unmanned aerial vehicle is able to change the flight direction instantly and that high efficiency unmanned aerial vehicle boundary trespassing can be detected. Therefore, the computational complexity is reduced greatly and the algorithmic efficiency is increased.

In a method for controlling an unmanned aerial vehicle (UAV), a digital image is obtained by an image capturing device of the UAV. The method detects an object in the digital image, determines a distance between the detected object and the UAV, and obtains a flight direction of the UAV if the distance is less than a preset value. The method further calculates a relative position and a relative angle between the detected object and the UAV, determines a flight limiting range of the UAV according to the relative position and the relative angle, and controls the flight direction of the UAV according to the flight limiting range.

An apparatus for heat shielding and deceleration of a spacecraft comprises an unfoldable shield of individual panels made of a high temperature resistant fiber reinforced ceramic and pivotally mounted on the outer structure of the spacecraft. An unfolding ring slides axially along the body of the spacecraft. The panels are pivotally connected to the unfolding ring by compression struts acting as toggle levers. Tension springs pull the unfolding ring axially along the spacecraft body to toggle out the compression struts so as to outwardly pivotally deploy the panels. The unfoldable shield can be arranged on the forward end or the rear end of the spacecraft relative to its flight direction upon entry into the atmosphere.

The invention discloses a control device and method for integrated unmanned aerial vehicle (UAV) flight. The control device comprises a data link communication unit, an acquisition unit, a processing unit and a control unit, wherein the data link communication unit is used for interacting with a ground station, acquiring a flight task of a UAV and monitoring the flight state of the UAV; the acquisition unit is used for acquiring current flight acceleration and angular speed of the UAV, static air pressure on the UAV, motion speed of the UAV relative to surrounding air, magnetic field intensity of geomagnetic field on the UAV and positioning information of the UAV; the processing unit is used for processing data acquired by the acquisition unit to acquire the flight attitude of the UAV, and comparing the flight attitude with the flight task received by the data link communication unit so as to give flight height, flight speed and flight direction which need to be adjusted by the UAV; and the control unit is used for controlling a steering engine controller of the UAV to adjust according to the flight height, flight speed and flight direction which need to be adjusted by the UAV and are given by the processing unit, so that the UAV meets the requirement of the flight task. The device and the method can effectively and quickly control the flight of the UAV.

The invention discloses an unmanned aerial vehicle flight control method and an unmanned aerial vehicle control system. The method includes the following steps that: a control command is received, and the location information and flight attitude parameter of an unmanned aerial vehicle are acquired, and flight attitude information can be obtained according to the location information and the flight attitude parameter; aerial photography data are acquired, and the flight attitude information and the aerial photography data of the unmanned aerial vehicle are outputted according to the control command; a remote sensing command is sent out according to the flight attitude information and the aerial photography data of the unmanned aerial vehicle; the remote sensing command is received and analyzed; and a flight control command used for controlling the operation of the drivers of the unmanned aerial vehicle is formed according to the analyzed remote sensing command, and the flight attitude information of the unmanned aerial vehicle, so that the flight direction and flight speed of the unmanned aerial vehicle can be controlled. With the above technical schemes of the invention adopted, simplicity, security and real-time performance of data exchange can be improved.

The invention relates to a multi-freedom degree bird-like flapping wing air vehicle. The multi-freedom degree bird-like flapping wing air vehicle comprises a driving mechanism, two twisting mechanisms, an empennage mechanism, two flexible joint structures and a machine frame. The multi-freedom degree bird-like flapping wing air vehicle is simple and compact in structure, and fully-symmetrical flapping wing movement can be realized. Two rubber flexible grooved mechanisms are arranged, so that the flapping wing air vehicle can fly like a bird; flapping wings are curved and folded, so that when the flapping wings flap upwards, a stressed area is reduced, and the resistance is reduced; when the flapping wings flap downwards, the wing extending area is the largest; besides, outer wings can also be passively bent in a flight direction by air resistance, so that great lifting force and great thrust are generated; steering engines are adopted to control inner wing rods so as to change the elevation angle of the flapping wings, the multi-freedom degree bird-like flapping wing air vehicle conforms to the effect that upward flapping resistance is less than downward flapping lifting force in aerodynamics, and the aerodynamic efficiency is improved; the two steering engines are utilized to control the deflection of the empennage, so that operating and controlling of the flight attitude of the flapping wing air vehicle are facilitated. The multi-freedom degree bird-like flapping wing air vehicle disclosed by the invention can be used in the fields of models, aerial photography monitoring, information collecting, disaster searching and rescuing, airport bird expelling and the like.

A method for adjusting a flight direction of an unmanned aerial vehicle (UAV) using a control device receives a first direction of the control device and a control command of the UAV, obtains a second direction of the UAV, and calculates an angle deviation between the first direction and the second direction. The method further adjusts the control command of the UAV according to the angle deviation to obtain an adjusted control command, and controls a flight direction of the UAV according to the adjusted control command

The invention provides an auxiliary control system for a power line inspection unmanned aerial vehicle, which comprises a camera. The auxiliary control system for the power line inspection unmanned aerial vehicle further comprises an electric field intensity detector, a flying sensor, a motor rotational speed controller, a remote controller and a main controller; the electric field intensity detector is installed on the camera and used for detecting the electric field intensity around a power line; the flying sensor is used for controlling the flight direction of the unmanned aerial vehicle under the control of the main controller; the motor rotational speed controller is used for controlling the rotational speed of a motor in the unmanned aerial vehicle under the control of the main controller; the remote controller is communicated with the main controller and sends a control command to the main controller; the main controller is used for calculating the distance value between the unmanned aerial vehicle and the power line according to the electric field intensity detected by the electric field intensity detector, and also used for controlling the work of the flying sensor and the motor rotational speed controller according to the control command sent by the remote controller and the distance value; and the electric field intensity detector, the flying sensor and the motor rotational speed controller are electrically connected with the main controller respectively. By adopting the scheme, the problem that the unmanned aerial vehicle collides with the power line during the process of power line inspection can be effectively solved.

The invention provides a navigation decoy system and method for a coexistence unmanned aerial vehicle. The decoy system comprises a satellite search system, a cheat signal generation control system and a signal transmission system. The satellite search system is used for receiving and parsing a true satellite signal, and parsed result data is transmitted to the cheat signal generation control system; the cheat signal generation control system is used for calculating related parameters and generating a cheat signal; the signal transmission system sends the cheat signal generated by the cheat signal generation control system to a target unmanned aerial vehicle, and a receiver of the target unmanned aerial vehicle captures and tracks the cheat signal and the true satellite signal at the sametime; the cheat signal generation control system increases the power of the cheat signal to remove the true signal and controls a tracking loop of the target unmanned aerial vehicle. According to thenavigation decoy system and method, a synchronous false satellite is generated and coexists in the target receiver with a sky satellite, the power of the cheat signal is gradually increased after coexistence, the processed noise basis of the receiver is increased, and the output signal-to-noise ratio of the true signal in a correlator of the receiver is lowered; by relying on the power advantage of the cheat signal, the true signal is gradually removed out of the tracking loop, then the tracking loop is controlled, and cheat for the flight direction and speed of the black-flight unmanned aerial vehicle is achieved.

The present invention relates to a black flying UAV (unmanned aerial vehicle) navigation decoy system and method, and a technical problem of unpredictable and uncontrolled flying directions and falling locations and possible secondary injury are solved. By adopting a traction navigation decoy signal generation system, a satellite searching system in communication connection with the traction navigation decoy signal generation system, a black flying UAV flying direction decoy remote control system and an antenna array, the black flying UAV flying direction decoy remote control system is used for remotely controlling the flying direction of a black flying UAV through the antenna array according to a decoy signal generated by the traction navigation decoy signal generation system, the traction navigation decoy signal generation system is used for combining a traction decoy signal according to a motion trajectory of the black flying UAV and ephemeris parameters, according to the above technical scheme, the problem is solved well, and the system and the method can be used in the protection of the black flying UAV.

The invention provides an unmanned plane flight path drawing method, device and system. The method comprises the steps of: planning a flight destination and a flight path of an unmanned plane; receiving a position signal returned in the flight process of the unmanned plane every a set time interval, and drawing the flight path of the unmanned plane on an electronic map according to the position signals; and if failing to receive the position signals in the set time interval, then setting the position, corresponding to the last received position signal, on the electronic map as a starting point of a virtual path, starting drawing the virtual path, using the flight speed of the unmanned plane at the time of the last received position signal as an analog flight speed of the unmanned plane, determining the flight direction at the present position of the unmanned plane according to the direction of the destination, determining the next arrived position of the unmanned plane after the set time interval, and drawing the virtual path of the unmanned plane on the electronic map according to the next position. By adopting the unmanned plane flight path drawing method, a user is enabled to estimate the position of the unmanned plane after the unmanned plane is lost, and the user is enabled to be still ready for unmanned plane recovery.

The invention provides an aviation emergency instrument which comprises an atmospheric pressure measurement unit, an inertial measurement unit, a double-antenna GPS satellite receiver connected with a satellite signal receiving antenna, a graphic display unit, a secondary power supply circuit, and a comprehensive processing and calculation unit, wherein the comprehensive processing and calculation unit receives the information from the individual sensors, calculates the navigation parameters indicative of air speed, pressure altitude, posture, flight direction, longitude and latitude by use of a sensor information fusion algorithm, and sends the calculation result to the high-density liquid crystal graphic display unit. According to the invention, since the aviation emergency instrument can provide the navigation parameters indicative of air speed, pressure altitude, posture (pitch angle and roll angle), flight direction, longitude and latitude, the aviation emergency instrument can not only provide reference information to a pilot who operates the main flight instrument in the normal state but also serve as an emergency instrument in case that the main flight instrument is in the failure state. When the main flight instrument completely fails to work, the pilot can operate the aircraft to return safely by means of the navigation information provided by the emergency instrument.

The invention relates to an unmanned aerial vehicle for express parcels, belonging to the technical field of unmanned aerial vehicle application. Parcels to be expressed are firstly loaded in a cargo hold A and a cargo hold B, respectively, and a cargo hold exit door A and a cargo hold exit door B are closed at the same time. A signal received by a wireless antenna is input into a navigation radar and a computer control center, a lithium ion battery A supplies power to drive a motor A, a transmission shaft A and a rotating wing A to rotate to generate flying power, a lithium ion battery B supplies power to drive a motor B, a transmission shaft B and a rotating wing B to rotate to generate flying power, the navigation radar and the computer control center control the rotation of the motor A and the rotating wing A and the rotation of the motor B and the rotating wing B, and the unmanned aerial vehicle flies to a destination according to a flight line set by the navigation radar and the computer control center control after the flight direction is regulated and controlled by a tail vane. A cargo hold door A is opened to take out the express parcels in the cargo hold A and a cargo hold door B is opened to take out the express parcels in the cargo hold B after forward walking wheels and backward walking wheels at the bottom part of the unmanned aerial vehicle land at the destination.

A multi-reflecting ion optical device includes electrostatic field generating means configured to generate electrostatic field defined by a superposition of first and second distributions of electrostatic potential ΦEF, ΦLS. The first distribution ΦEF subjects ions to energy focusing in a flight direction and the second distribution ΦLS subjects ions to stability in one lateral direction, to stability in another lateral direction for the duration of at least a finite number of oscillations in the one lateral direction and to subject ions to energy focusing in the one lateral direction for a predetermined energy range.

The invention provides an automatic height fixing control method for an unmanned spacecraft operation based on a two-dimensional laser scanner. The adopted technical scheme, by which a problem is solved, is as follows: arranging the two-dimensional laser scanner on an unmanned spacecraft airframe, irradiating and scanning the area in front of the airframe to obtain a height from the airframe to the ground and topographic scan data; leading-in data obtained by the laser scanner into an embedded control panel in real time to perform related computation, calculating whether a collision possibility or a dangerous obstacle exists in a flight direction combining with airframe posture angle data transmitted from an airframe inertial posture measurement unit; making the embedded control panel send a climbing command to a flight controller if a calculated result proves that a collision hidden danger exists in front of the spacecraft. The automatic height fixing control method of the invention has beneficial effects that the unmanned spacecraft has a certain capability of perceiving the ground, is capable of detecting the collision hidden danger from the ground when performing a low-altitude operation, and ensures that the unmanned spacecraft can take measures in time to escape from the obstacle.