101results about How to "Reduce flight costs" patented technology

A safe lander consists of a flight airplane, transducer multi-path multiplexing receiver and emitter set on said airplane, digital processor/computer of land based simulator, flight control unit of land based airplane simulator, remote navigation electronic interface unit, land based airplane simulator, unique airplane identification ID and configuration unit, analysis unit of land based processing station, two-way RF communication unit of space to ground and ground to space, and remote pilot display set on land based simulator.

The invention discloses a miniature SAR remote sensing observation method based on a multi-rotor unmanned aerial vehicle. Systems used in the method comprise a multi-rotor unmanned aerial vehicle system and a miniature SAR observation system. The miniature SAR observation system is composed of an SAR radar host, an IMU inertial navigation system, a radar radio frequency antenna, a GPS module, a radar control device, and a battery module, wherein the radar control device is connected with the SAR radar host through a USB3.0 or serial port, the IMU inertial navigation system and the battery module are connected with the SAR radar host through whole machine cables, and the GPS module and the radar radio frequency antenna are connected with the SAR radar host through a coaxial cable and a radio frequency coaxial cable respectively. The miniature SAR observation system is connected with the multi-rotor unmanned aerial vehicle system through the GPS module. Through the method, the flight cost of SAR image acquisition is reduced effectively, and rapid deployment and fast imaging of the miniature SAR observation system are realized. The method has the advantages of simple operation, convenient use and low price.

The invention provides a fixed wing type hybrid power motorplane applied to the technical field of engine products. A propeller (3) is installed on a fuselage (1) of the fixed wing type hybrid power motorplane and is connected with a driving motor (4), and the driving motor (4) is connected with a power battery (5) and further connected with a driving motor control component (6) capable of controlling the driving motor (4). An engine (7) is further arranged in the fuselage (1) and is connected with a generator (8), the generator (8) is connected with the power battery (5) and connected with the driving motor control component (6) at the same time, and the engine (7) is connected with an engine control component (9) capable of controlling the engine (7). According to fixed wing type hybrid power motorplane, electric energy and fuel oil can be alternately used, various plane performance indexes can be effectively met, energy consumption can be reduced, flying cost can be reduced, and environmental pollution can be relieved.

The invention discloses an unmanned aerial vehicle route planning and obstacle avoidance method, which comprises the steps of S1, establishing a two-dimensional space model, and setting space model data according to a flight starting point and a flight ending point; S2, obtaining a global offline air route by utilizing the space model data, and setting a flight air route as a global offline air route; S3, the unmanned aerial vehicle flying along the flight route, and monitoring whether a dynamic obstacle appears on the flight route or not in real time through a sensor; S4, when a dynamic obstacle appears, entering the next step; if no dynamic obstacle appears and the flight end point is not reached, entering the step S3, and if the flight end point is reached, entering the step S8; s5, initializing a pigeon flock algorithm by adopting an adjoint matrix method with constraints, and then performing local airway planning by using the pigeon flock algorithm; s6, smoothing the local air route by using the B spline curve; s7, the flight route being a combination of a global offline route and a local route, and executing the step S3; and S8, completing a flight mission, and ending the process.

A mechanical device that performs single, orthogonal, alternate, and independent movements which, adapted in an apparatus, can be applied to the prevention of lower limb thrombosis suffered by people who spend long hours in a sitting position. The device includes a solid cylinder shaped as a horizontal axis with a solid, centered, and jointly-moving sphere with grooves on its surface, along which runs a guiding bolt that guides the movement all along the grooves. The guiding bolt is joined to one of the arms of a fork-shaped piece. On the other arm of the fork, there is a ball-holding cavity with a spring to push a ball into a depression on the sphere surface opposite to the grooves. The guiding grooves engraved on the piece, which are read by the guiding bolt, are transferred to the pedals adhered to the gym apparatus.

The invention discloses an unmanned aerial vehicle group path planning method which comprises the following steps: firstly, acquiring information of an unknown environment, including positions of a starting point and a target point, coordinates of an obstacle, possible radar and missile risks and the like; when the unmanned aerial vehicle group plans a path, needing to consider the performance ofthe unmanned aerial vehicle, such as a deflection angle, a pitch angle and a flight height; on the basis, enabling the unmanned aerial vehicle to select a path preferentially through calculation of aparticle swarm optimization algorithm, and achieving path planning of the whole unmanned aerial vehicle group. According to the invention, path planning of the unmanned aerial vehicle group in a denserisk environment can be realized, so that the unmanned aerial vehicle group can fly efficiently to cooperatively complete tasks. Based on the path planning of the unmanned aerial vehicle group, the research on the path planning method of the unmanned aerial vehicle group is carried out from the two aspects of improving the safety and high efficiency of the air traffic system, and the method has important significance in ensuring the flight safety of the unmanned aerial vehicle, reducing the flight cost, increasing the airspace capacity and improving the operation efficiency of the air trafficsystem.

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 colorless and small odor of airplane cleaning agent which is used for daily maintenance and repair of civil aircrafts and belongs to the field of chemical materials. The cleaning agent is prepared by SDBS (sodium dodecyl benzene sulphonate), emulsifier OP-10, coconut oil diethanol amide and inorganic base according to certain proportions. The product of the formula can remove antiseptic oil, oil stain, carbon deposition and dust on the external surface of the airplane parts completely, does not damage the material of the airplane parts, does not leave any trace, does not cause corrosion to aluminum and does not cause hydrogen brittleness. As is proved by wide use of domestic main aviation repair enterprises, the product of the formula has excellent comprehensive properties of rapid cleaning, safety, no combustion and convenient storage and transportation, and the product has obvious market competition advantages and good economic and social benefits.

The invention discloses an in-flight auto-ignition control method of an engine of an unmanned aerial vehicle. The method comprises: (11), detecting whether a ground control station is out of control, or whether the engine of the aerial vehicle is subjected to accidental flameout and shut down; (12), if the ground control station is out of airplane control ability, or the engine of the aerial vehicle is subjected to accidental flameout and shut down, executing the step (13); (13), detecting whether the communication link between the unmanned aerial vehicle and the ground control station is normal, if the communication link between the unmanned aerial vehicle and the ground control station is normal, executing the step (14); (14), detecting whether the engine working condition information and the aerial vehicle flight state meet operation requirements, if the engine working condition information and the aerial vehicle flight state meet the operation requirements, executing the step (15); and (15), detecting whether a throttle servo, an accelerator servo and a task servo of the engine can work normally, if the throttle servo, the accelerator servo and the task servo of the engine can work normally, carrying out an ignition command, and restarting the engine; if the throttle servo, the accelerator servo and the task servo of the engine cannot work normally, stopping sending the ignition command. The method can be applied to reignition and starting of the unmanned aerial vehicle after fault recovery, the aerial vehicle can be effectively protected, and the flight cost is reduced.

The invention discloses an unmanned aerial vehicle group formation method based on a Boid model, and belongs to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle group formation method comprises the steps of respectively assembling and configuring quad-rotor unmanned aerial vehicles in the unmanned aerial vehicle group, and sensing state information of other unmanned aerial vehicles in the detection radius range through an information acquisition module; dividing a space area in the detection radius range of the unmanned aerial vehicle I, and judging which area the other unmanned aerial vehicles in the detection radius range are located; when the unmanned aerial vehicle I does not conflict with other unmanned aerial vehicles, and when no other unmanned aerial vehicle exists in the conflict area, adjusting the flight speed and direction of the next time step by the unmanned aerial vehicle I according to the states of the unmanned aerial vehicles in the consistent area and the attraction area; and utilizing the flight speed of each unmanned aerial vehicle at the current time step and the synchronism Va of the direction computer group, and completing autonomous cluster regulation and control when Va is smaller than a threshold value. Control continuity and stability of the unmanned aerial vehicle group in the formation state are ensured, flight safety isensured, the flight cost is reduced, and the operation efficiency of the air traffic system is improved.

The invention discloses a cesium light pump magnetic measuring method based on a fixed-wing unmanned aerial vehicle. The method includes: presetting a testing qualification standard, conducting performance testing on the unmanned aerial vehicle, and if testing is qualified, establishing signal connection between a ground measurement and control station and the unmanned aerial vehicle; if the testing is unqualified, conducting the performance testing of the unmanned aerial vehicle again; after the unmanned aerial vehicle reaches measurement height, calculating magnetic compensation coefficient;after magnetic compensation is completed, respectively transmitting magnetic measuring data measured by a cesium light pump magnetometer and navigation data measured by a laser altimeter, a GPS and an IMU to a data collection box through a serial port; after the data collection box receives corresponding magnetic measuring data and navigation data, transmitting the same to a field data preprocessing system for data processing; performing aeromagnetic interpretation on processed data. By the method, measuring accuracy, working efficiency and flying safety are improved, and weight, size and cost of the unmanned aerial vehicle are reduced.

The invention provides an unmanned aerial vehicle obstacle avoidance method and system based on a speed potential field, and is used for controlling an unmanned aerial vehicle to effectively avoid a high-speed moving obstacle, and the method comprises the steps: detecting the collision possibility of the unmanned aerial vehicle and the obstacle according to the position and speed of the unmanned aerial vehicle and the position and speed of the obstacle; if the collision possibility exists between the unmanned aerial vehicle and the obstacle, calculating the gravitational force generated by the gravitational field to the unmanned aerial vehicle, the repulsive force generated by the improved repulsive force field to the unmanned aerial vehicle and the speed potential field force generated by the speed potential field to the unmanned aerial vehicle; according to the gravitational force, the repulsive force generated by the improved repulsive force field to the unmanned aerial vehicle and the speed potential field force, calculating the resultant force borne by the unmanned aerial vehicle in the ith step, wherein i is a positive integer; according to the resultant force borne by the unmanned aerial vehicle in the ith step, calculating the direction unit angle of the unmanned aerial vehicle in the ith step, calculating the velocity vector, the pitch angle and the yaw angle of the next movement of the unmanned aerial vehicle according to the direction unit angle, and controlling the unmanned aerial vehicle to avoid obstacles.

The invention discloses a dual-redundancy electromechanical actuator which is composed of a base (3), a left supporting plate (4A), a right supporting plate (4B), a cover body (5), a six-phase fault-tolerant motor (1), a planetary roller lead screw assembly (2), a left end transmission assembly and a right end transmission assembly. The left end transmission assembly and the right end transmission assembly are the same in structure. The transmission assembly comprises a helical spur gear, a rotating shaft, an idle gear and an electromagnetic brake. According to the invention, the six-phase fault-tolerant motor (1) is matched with the helical gear to realize linear output of the planetary roller screw assembly (2). Through the left end transmission assembly and the right end transmission assembly which are installed at the two ends of the motor shaft (1A) respectively, the size and the weight of the electromechanical actuator are reduced under the independent transmission mode of the left end and the right end.

The invention discloses a rapid formation method for an unmanned aerial vehicle fleet. The method comprises the steps: generating a topological structure of a communication connection network betweenunmanned aerial vehicles; on the basis that the network degree distribution is not changed and no extra consumption is increased, adjusting the topological structure of the communication connection network, so that the communication connection network obtains higher algebraic connectivity; therefore, after the topological structure of the communication connection network is determined, enabling each unmanned aerial vehicle to acquire flight data of a neighbor unmanned aerial vehicle through a communication connection network; after the flight data of the neighbor unmanned aerial vehicle is acquired, enabling the unmanned aerial vehicles to fly to the central position of the neighbor unmanned aerial vehicles by controlling the unmanned aerial vehicles, so that the unification of the position and the speed of the unmanned aerial vehicle fleet can be realized step by step; and finally, realizing the rapid formation control of the unmanned aerial vehicle group. According to the method, theproblem of rapid formation of the unmanned aerial vehicle fleet on the basis of fixed communication connection network degree distribution and no increase of extra consumption can be solved, the algorithm complexity is low, the calculation precision is high, and rapid formation of the unmanned aerial vehicle fleet can be effectively realized.

The invention relates to a magnetic suspension aircraft which belongs to the technical field of an aircraft with the power device type as the characteristic, manned flight of the aircraft can be realized by magnetic force generated between a fixed magnetic field and a flight device and a power source in the flight device so as to solve the problem of high cost and complex operation of a conventional aircraft. The aircraft includes the flight device, a fixed magnet and a protecting device; the flight device comprises an enclosed space formed by an upper shell and a lower shell, the lower shell is provided with a power source and a magnet in annular distribution, the power source comprises a motor, a motor bracket, an electronic regulator and a propeller; the fixed magnet is located in protecting device, the fixed magnet has the same polarity, the magnet has the same polarity, adjacent sides of the fixed magnet and the magnet are same in polarity; and the protecting device includes a protective guard, an inflatable layer attached to the protective guard, and a baffle plate located above the fixed magnet. The magnetic suspension aircraft has the advantages of low cost, simple operation and high safety performance.

The invention discloses a flight device and a flight method thereof. The flight device comprises an aircraft and a traction device used for pulling the aircraft to the air. The aircraft is provided with the air power lifting surface and a flight driving device used for providing flight power for the aircraft. The traction device comprises a traction body and a traction rope connected with the traction body and the aircraft. The flight device further comprises a flight attitude adjusting device. When the traction rope is separated from the aircraft in the air, the flight attitude adjusting device adjusts the flight attitude of the aircraft, and the aircraft flies under the effect of the flight driving device and the air power lifting surface. According to the flight device designed through the mode, the high cost of ground runway construction is saved, the flight cost is reduced greatly, and take-off of the aircraft is facilitated.

The invention relates to a fluorocarbon coating-containing aircraft wing shell, which includes a skin substrate and a protective coating. The protective coating comprises a layer of zinc yellow acrylic polyurethane primer and two layers of fluorocarbon finish paint. The A component of the fluorocarbon finish paint consists of: high hydroxyl fluorine-containing acrylic resin, color filler, nano-magnesium oxide, nano-titanium dioxide, a leveling agent, a defoaming agent, a dispersing agent, a catalyst and a solvent. The aircraft wing shell provided by the invention can better adapt to current increasingly harsh flight conditions, thus improving the flight safety.

The scheme of the invention discloses an aerial acceleration type drum-type runway stopper which is a mechanical roller device. The runway stopper comprises multiple groups of roller sets, wherein each roller set comprises a driven roller and a driving roller; the driving roller can independently rotate at high speed; each roller set is provided with a braking device. When an aircraft slides at high speed and is close to the runway stopper, the driving rollers are started and clockwise rotate at high speed, the sliding wheels of the aircraft run onto the driven rollers under the function of inertia, when the sliding wheels of the aircraft are contacted with the driving rollers, as the driving rollers are rotating at high speed in the direction opposite to the sliding wheels, the forward inertia of the sliding wheels is transferred, the sliding wheels are supported above the driven rollers and driving rollers and rotate in the air, and the motion of the aircraft relative to the ground stops. As the aerial accelerated movement of the sliding wheels and the roller sets release inertial energy, the inertia force of the aircraft disappears instantly, and the aircraft is stopped. The aerial acceleration type drum-type runway stopper can stop the aircraft at any position within the sliding distance of the aircraft, and particularly can stop large-scale and heavy aircrafts within a short distance.

The invention discloses a trust-based task unloading method. The trust-based task unloading method is divided into two parts. The method comprises the steps that 1, Internet of Things devices with edge service calculation requirements in a network are clustered, all the Internet of Things devices in a cluster can communicate with an unmanned aerial vehicle, and devices outside the cluster can transmit tasks to the devices in the cluster in a multi-hop mode and then unload the tasks to the unmanned aerial vehicle; the clustering mode can reduce the unmanned flight cost and expand the range of edge services; since the task outside the cluster only needs to be transmitted to any device in the cluster, overlarge data load of a single cluster head can be avoided. 2, a trust evaluation mechanism based on backtracking analysis is provided, active trust based on the unmanned aerial vehicle is introduced, trust evaluation is carried out on the Internet of Things equipment, and therefore the effectiveness of task unloading is guaranteed. In combination with a trust-based task transmission routing protocol, reliable equipment is selected for task relay forwarding or task unloading, smooth completion of a calculation task is ensured, and the packet loss rate of a network is reduced.

The invention discloses a novel oil-firing wind power airplane. The novel oil-firing wind power airplane comprises an airplane body, a left wing and a right wing, wherein more than one left wind driven generator is arranged on the middle rear portion of the lower portion of the left wing, each left wind driven generator comprises more than one set of left fan blades, each set of left fan blades are installed on a left rotary shaft, the rear end of each rotary shaft is in transmission connection with a power input shaft of the corresponding left wind driven generator, the left wind driven generators are fixed to the left wing, more than one right wind driven generator is arranged on the middle rear portion of the lower portion of the right wing, each right wind driven generator comprises more than one set of right fan blades, each set of right fan blades are installed on a right rotary shaft, the rear end of each right rotary shaft is in transmission connection with a power input shaft of the corresponding right wind driven generator, and the right wind driven generators are fixed to the right wing. According to the novel oil-firing wind power airplane, energy consumption and flight cost can be reduced, exhaust emission and other pollutant emission are reduced, the carrying capacity is high, the weight is relatively smaller, and the space for airplane parking is small.