83results about How to "Reduce flight time" patented technology

An autonomous-flight unmanned aerial vehicle system comprises a master controller and ground station equipment. The master controller comprises a data acquisition module, a data processing module anda communication module. Flight control and flight management functional requirements of unmanned aerial vehicles in different models can be realized through correction of an internal procedure and a peripheral circuit of the master controller. The system is characterized in that the ground station equipment is responsible for configuration parameter and flight route planning electronic fence setupand navigation mode configuration of each single unmanned aerial vehicle, and the master controller realizes autonomous flight including autonomous obstacle avoidance and breakpoint endurance of theunmanned aerial vehicles according to waypoint files, flight parameters and safety parameters generated by the ground station equipment.

Method and apparatus for unmanned aerial maritime float vehicle that sense and report relevant data from physical and operational environment. The apparatus is comprised of an unmanned aerial vehicle and cabled unmanned underwater vehicle. The method wherein a end-user's controller is coupled wirelessly to the unmanned aerial vehicle transceiver to allow relevant live data to be collected from sky and ground, Upon landing on a water's surface the cable is repelled and control signals and data are transmitted to the cabled unmanned underwater vehicle transceiver, thus high speed feedback and sensor signals can be transmitted from the cabled UUV back to the UAV then both the UUV and UAV high speed feedback and sensor signals are wirelessly sent back to the user's controller through the UAV.

A magnetic disk drive capable of shortening a flying time of a magnetic head flying over a magnetic disk and reducing the number of load/unload operations. The disk drive includes a non-volatile memory for temporarily storing data corresponding to a write command supplied from a host. Data corresponding to a plurality of write commands are stored in the non-volatile memory. The head loading is suspended until a predetermined condition is satisfied. When the predetermined condition is satisfied, all the data stored in the non-volatile memory are written in the magnetic disk sequentially at a time. Thereby it is possible to shorten the flying time of the magnetic head flying over the magnetic disk and reduce the number of load/unload operations.

The invention discloses an unmanned aerial vehicle flight trajectory optimization method based on machine learning in an edge computing network. The method comprises the following steps: in a cycle, an unmanned aerial vehicle departs from a position where a server is deployed, sequentially passes through all ground terminals and completes a communication task, and then returns to the initial position; when the unmanned aerial vehicle takes off, a flight scheduling table is calculated according to the position distribution of the ground terminals, and then the unmanned aerial vehicle flies through all the ground terminals in sequence according to the flight scheduling table; and in the flying process of the unmanned aerial vehicle, a local optimal trajectory of the unmanned aerial vehicle is calculated by utilizing a random method and a machine learning method in an iteration mode, the local optimal trajectory is added into a global optimal trajectory q, and the unmanned aerial vehicleflies along the global optimal trajectory q. According to the method, the flight distance and the flight time of the unmanned aerial vehicle can be effectively reduced and shortened, the flight cyclecan be shortened, and the transmission efficiency can be improved.

The invention discloses an accurate agricultural UAV control method for based on independent start/stop, according to requirements, of working units. The method comprises the following steps that 1) field block data and working parameters are input; 2) an initial value of a stepping angle of theta are set; 3) a working direction is determined, and a row center line is calculated; 4) unit center lines are obtained; 5) an initial path and a corresponding unit working state are solved; 6) a path which enables a minimal sum of the total traversal distance is solved, and stored as an optimal path in the working direction; 7) whether theta is lower than 180 degree is determined, if YES, one stepping angle is added to theta and the step 3) is returned to, and if NO, a next step is turned to; and 8) optimal paths corresponding to different values of theta are compared, the shortest optimal path is selected as a final work path, the final work path is stored corresponding to the unit working state, and flight control information of a UAV is obtained. Thus, the agricultural UAV is controlled accurately when the UAV works in the field, especially in an area near the boundary of a field, and the utilization rate of consumables as pesticides and fertilizers is improved.

The invention provides a quadrotor aircraft trajectory tracking control method based on nonlinear guidance, and belongs to the technical field of aircraft control. First a straight path coordinate system, an arc path polar coordinate system and an inertial coordinate system are established for a quadrotor aircraft; then the required height and the expected course angle, pitch angle and lateral acceleration for tracking a trajectory of the quadrotor aircraft are calculated; a height controller of the quadrotor aircraft obtains the required height for tracking the trajectory, an attitude angle controller obtains the expected course angle, a pitch angle controller obtains the expected pitch angle, a roll angle controller obtains the expected lateral acceleration, and finally the quadrotor aircraft flies according to a predetermined trajectory under the control of the height controller, the attitude angle controller, the pitch angle controller and the roll angle controller. The quadrotor aircraft trajectory tracking control method based on nonlinear guidance solves the problems that existing quadrotor aircraft tracking control cannot ensure constant-speed flight and response delay is large. The method provided by the invention can be used for quadrotor aircraft trajectory tracking control.

A liquid ejecting apparatus includes: a liquid ejecting head having a nozzle formation surface in which a nozzle is formed that causes a liquid to be ejected through the nozzle toward a landing target by driving a pressure generation unit; a support unit that supports the landing target that is disposed at a landing-capable distance from the nozzle formation surface of the liquid ejecting head; and a liquid droplet collection unit disposed in a location that is distanced from an ejection region. Here, the liquid droplet collection unit has a landing surface on which the liquid lands when carrying out flushing operations; and the distance between the landing surface and the nozzle formation surface of the liquid ejecting head is set to be smaller than the landing-capable distance, and the nozzle formation surface and the landing surface are set to the same voltage at least during the flushing operations.

The invention discloses an air route planning method for multi-unmanned aerial vehicle target positioning, which is used for solving the technical problem of poor practicability of an existing unmanned aerial vehicle air route planning method. According to the technical scheme, the method comprises the steps of firstly, enabling a navigation system of an unmanned aerial vehicle to obtain the position information of the unmanned aerial vehicle, and searching to obtain the approximate position of a ground fixed target; and obtaining the flight speed v, the maximum roll angle and the radius R ofa trajectory circle flying around the fixed target of the unmanned aerial vehicle as the initialization parameters. Under the condition that the initial positions of the multiple unmanned aerial vehicles are random, it can be guaranteed that the multiple unmanned aerial vehicles can rapidly reach the space above the target, and an equidistant formation configuration on a trajectory circle is rapidly formed. According to the method, the information needed by planning is little, the engineering implementation is easy, the calculated amount is very small, and the planning speed is high; the formed planned road section only has a straight line section and a curved line section, the flight distance is as short as possible, the flight time is as short as possible, and the practicability is good.

The invention relates to a design method of an escape orbit starting from a Halo track and used for detecting a deep space target. The method is especially suitable for design of the escape orbit starting from the Halo track and used for conducting a deep space detecting task and belongs to the technical field of aerospace engineering. First, a minor celestial body periapsis state of interior extent unstable disturbance manifold of a task given Halo track is obtained through calculation; then, according to minor celestial body escaping hyperbola overspeed required by interplanetary transfer required by the task, maneuvering pulse required to be exerted at the position of disturbance manifold periapsis is solved, and flying time from the periapsis to a minor celestial body affecting ball is solved; and finally, contour maps of velocity increment and flying time are drawn respectively, and the escape orbit meeting a task requirement is selected from the contour maps. On the basis of low fuel consumption, flying time for escaping from the Halo track is shortened, and ephemeris constraint of other celestial bodies is not required to be introduced. The degree of freedom of the escape orbit starting from the Halo track is increased by introducing the disturbance manifold, and solution space of a traditional design method is expanded.

A hybrid gun device composed of two barrels (1,10) that accept energy from combustion of standard propellant (6), one barrel (10) being operative to produce a high intensity electric current to add accelerating energy to a projectile (7) in the second barrel (1) and at least one coil (8) stage to convert energy between electrical and kinetic to cause the projectile (7) to be launched at hypervelocity.

The invention belongs to a field of flight control technology and discloses an emergency return landing speed command set design method. The method includes (1), constructing a grid of mass, rolling angle, airport height, height and speed parameters, calculating an attack angle, an elevator, a lift-drag ratio, a track angle and a submerge rate of constant speed gliding of an aircraft, determining the maximal lift-drag ratio rate and the idle gliding maximal available speed changing along with mass, rolling angle, airport height and height, dividing a speed range between the maximal lift-drag ratio rate and the idle gliding maximal available speed into N+1 parts, adding the maximal lift-drag ratio rate and the idle gliding maximal available speed for creating a N+2 grade speed command set, wherein the content of each grade of the speed command set includes the attack angle, the elevator, the lift-drag ratio, the track angle and the submerge rate corresponding to the speed of said grade; (3) recording the N+2 grade speed command set by the aircraft, and selecting an appropriate speed command set grade for execution according to the mass, the airport height, the height, the speed and the distance between the aircraft and the airport when emergency aircraft return landing is required.

The invention relates to a method and a mapping meter for mapping flight time and momentum energy of a refraction type charged particle. The method comprises the following steps: 1) forming a reflection electric field which is uniform along axial direction in a vacuum test tube; 2) generating a charged particle by a charged particle source at one end of the vacuum test tube; 3) performing decelerated motion in the reflection electric field by the charged particle till an axial speed is reduced to zero; 4) immediately performing contrary accelerated motion in the reflection electric field by the charged particle till the charged particle arrives at a position sensing detector at the position of the charged particle source; and 5) detecting and recording the position information (x, y) and the flight time ttota1 of the charged particle by the position sensing detector, thereby finally mapping initial momentum and energy Epsilon i of the charged particle. The method and the mapping meterprovided by the invention are used for prolonging the flight time of the charged particle, by aiming at the bottleneck at the aspect of comprehensively promoting three parameters of energy resolution, energy detection range and charged-particle collecting efficiency of an existing charged particle flight time and momentum energy spectrometer.

The invention discloses a multi-rotor unmanned aerial vehicle route planning and aerial photography method suitable for a strip-shaped measuring area, and relates to the technical field of unmanned aerial vehicle autonomous control. In order to solve the problem that in the prior art, when an unmanned aerial vehicle is used for surveying and mapping a strip-shaped area, excessive flight sortie exists, the electric quantity loss of the unmanned aerial vehicle is serious, by adopting the method, the line segment route planning problem of the multi-rotor unmanned aerial vehicle in the irregular strip-shaped measuring area can be solved; the flight sortie can be reduced on the premise of ensuring the availability of flight results; take-off and landing time of an airplane is shortened, invalidloss of an airplane battery is reduced, the working efficiency of field flight personnel is improved, the redundancy coverage rate of the airline is reduced, the effective rate of the airline is increased, and the ortho-image mapping precision is improved in a parallel airline mode, so that the flight cost of a project is reduced, and the economic benefit of the project is improved.

The invention discloses a hybrid continuous small thrust trajectory design method adopting electric propulsion/solar sail propulsion. Firstly, a virtual gravitational field dynamics model is established. Secondly, the dynamic model of tangential thrust orbit in virtual gravitational field is established and its analytical solution is solved. Then the accuracy of the analytical solution is analyzed. Finally, the orbit optimization model is established, and the hybrid continuous small thrust method of electric propulsion/solar sail propulsion is used to optimize the orbit. Under the condition ofguaranteeing the accuracy, the invention can greatly reduce the calculation amount, can reduce the thrust required for realizing the orbit transfer, and expands the application range of the small thrust orbit.

An internal combustion engine is provided with a roughly concave cylinder head, wherein a ridge descends into the combustion chamber. A first wall is formed from the ridge to a cylinder periphery to form a seat for an air intake valve. A second wall is formed from the ridge to the opposite cylinder periphery to form a seat for one or more exhaust valves. The valves must criss-cross to open/close. The result is a more efficient flow of intake air and exhaust air to and from the combustion chamber which creates more horsepower. A plug compatible cylinder head can be installed on an engine to get added horsepower without a supercharger.

Monitoring apparatus 2 for person recognition in a monitoring region 7, having at least one camera 3 for recording an image sequence of a portion 10 of the monitoring region 7, wherein the image sequence comprises a plurality of monitoring images, having a person recognition module 6, wherein the person recognition module 6 has at least one recognition feature of a person that is to be located and is configured to search for the person to be recognized based on the monitoring images and the recognition feature, wherein the camera 3 has a fisheye lens 4.

The invention provides a post-earthquake unmanned aerial vehicle emergency material distribution method and device, and relates to the technical field of path planning. The method comprises the following steps: acquiring disaster relief point information, multiple site information, and unmanned aerial vehicle information; based on the disaster relief point information, the multiple site information, and the unmanned aerial vehicle information, conducting a multi-site multi-unmanned aerial vehicle distribution model with the purpose of minimizing the sum of demand weighted arrival times; solving the multi-site multi-unmanned aerial vehicle distribution model through a hybrid genetic algorithm, and obtaining an optimal task planning scheme for each unmanned aerial vehicle to carry out material distribution for one or more victim gathering points. According to the method and the device, for emergency material distribution after an earthquake disaster, the victim gathering points for material distribution of different unmanned aerial vehicles are determined, and a sequence of distribution to the victim gathering points by a plurality of unmanned aerial vehicles starting from different sites is optimized, so that the flight duration of unmanned aerial vehicle post-disaster material distribution is reduced, the material distribution efficiency is improved, and the use efficiency of heterogeneous unmanned aerial vehicles is maximized, and high-quality solutions are obtained.

The application relates to an unmanned-aerial-vehicle-based internet-of-things communication system and method. The system comprises an internet-of-things terminal, an unmanned aerial vehicle, and anunmanned aerial vehicle base. The unmanned aerial vehicle is provided with a first data transceiver unit in communication with the internet-of-things terminal, an artificial intelligence unit for planning a flight path of the unmanned aerial vehicle, and a basic flight control unit for controlling the flight operation of the unmanned aerial vehicle. A second data transceiver unit in communicationwith the unmanned aerial vehicle and a power management unit for charging the unmanned aerial vehicle are arranged on the unmanned aerial vehicle base. And the unmanned aerial vehicle base is in communication connection with a background. The communication between the internet-of-things terminal and the background is realized by carrying data by the unmanned aerial vehicle; and problems that the internet of things can not be built in an area without signal coverage, configuration is not flexible, the system is only compatible with one kind of communication mode, the cost and environment requirement are high in large-area application and networking, and the animals are affected according to the existing internet-of-things communication system are solved.