73results about How to "Stable flight attitude" patented technology

This invention discloses one forest measurement method without human aviation cameral remote sensor, which adopts aviation device as remote platform without human and integrated digital codes camera, difference GPS and top platform, wherein, it uses digital camera technique to get high earth resolution rate without human remove image with large proportion rules fully in use of high flexible machine without special plane spot and capable of flying under clouds.

The invention relates to the technical field of unmanned gyroplane autonomous tracking, in particular to an unmanned gyroplane moving target autonomous tracking device based on a pan-tilt camera and an airborne sensor. The unmanned gyroplane moving target autonomous tracking device comprises an aircraft and a ground station. The aircraft comprises an aircraft controller, an aircraft propeller motor connected with the aircraft controller, and a pan-tilt motor. The pan-tilt motor is connected with the pan-tilt camera. A wireless image transmission module and a wireless data transmission module are arranged between the aircraft and the ground station. The aircraft and the ground station are connected through the wireless image transmission module and the wireless data transmission module. Images obtained by the airborne pan-tilt camera serve as input of a system, coordinates of a target in the images are obtained on the ground station through a Struck algorithm, modeling is conducted on the coordinates of the target through a uniformly accelerated motion (CA) model, the control quantity of a pan-tilt is designed according to the coordinates, estimated through modeling, of the target, and accordingly tracking instantaneity and smoothness of the pan-tilt camera are guaranteed.

The invention discloses a multi-rotor aircraft driven by duct lift fans with diversion helms. The multi-rotor aircraft comprises the multiple duct lift fans with diversion helms, and an aircraft fuselage, wherein the aircraft fuselage comprises a frame, a landing gear, a power module, a flight control module , a load cabin and other function modules; the duct lift fans with the diversion helms are mounted on the aircraft fuselage and mainly consist of propellers, propeller driving units, the diversion helms, diversion helm driving units, ducts and the like, and the ducts are arranged at the peripheries of the propellers and used for improving the efficiency of the propellers, protecting the propellers and reducing the noise of the propellers; the propellers are driven by the propeller driving units; and the diversion helms driven by the diversion helm driving units are arranged on the air inlet sides or the air outlet sides of the duct lift fans.

The invention relates to an aircraft (1), preferably an unmanned aircraft (UAV), drone, or unmanned aerial system (UAS), comprising a rigid wing (2), which enables aerodynamic horizontal flight, and at least four rotors (4, 4'), which are driven by means of controllable electric motors (5) and which can be pivoted between a vertical starting position and a horizontal flight position by means of a pivoting mechanism (7), wherein all electric motors (5) and rotors (4) are arranged on the wing (2).

The invention discloses a collision resistant quad-rotor spherical unmanned aerial vehicle system comprising a flight platform, a mission load and ground equipment. The flight platform executes a flight mission, the mission load is carried on the flight platform for detecting, and the ground equipment conducts remote control, remote measuring and data transmission on the flight platform or the mission load. The flight platform comprises an integrally-arranged spherical frame mechanism, an internal aircraft body and a supporting mechanism. The spherical frame mechanism is overall of the structure of a longitude and latitude frame of a tellurion. The supporting mechanism comprises an annular connecting piece located at the center of the spherical frame mechanism, and two supporting pipes arranged along the rotation axis of the tellurion. The annular connecting piece and the spherical frame mechanism are connected to be a whole through the supporting pipes, and the gravity center of the flight platform mounted on the annular connecting piece is lower than that of the annular connecting piece. An integrally-arranged annular protective structure is provided for the aircraft body, so that the flight platform is good in collision resistance and still has high survival ability and adaptability in the complex environment.

The invention relates to an unmanned patrol aircraft for power transmission lines. The unmanned patrol aircraft comprises an aircraft body, a camera system, a cloud deck, a nanometer battery, an aircraft control system, a wireless transmission system, a GPS positioning system and a ground receiving, controlling and managing system. The unmanned patrol aircraft has four ailerons which are symmetrically installed at two sides of a main beam; the unmanned patrol aircraft has the advantages of stable flight, a fast flight speed, high flexibility and great loading capacity; front and rear beams are of segmented design, which facilitates adjustment and wiring. The aileron horns of the ailerons are movably connected with an aileron fixing frame through bolts; the aileron fixing frame is equipped with folding positioning seats; the aileron horns rotate with the bolts as centers and are limited through the folding positioning seats; such a structure enables the aileron horns to be parallely drawn close onto the main beam after folding, so the unmanned patrol aircraft has a small size and is easy to carry. After the front and rear aileron horns are open, lines among center points of four motors on the front and rear aileron horns form a square, and such a structure enables the aircraft to maintain balanced flight and to have reduced current loss and long flying time.

The embodiment of the invention discloses an unmanned aerial vehicle remote sensing system and an unmanned aerial vehicle remote sensing method. The unmanned aerial vehicle remote sensing system comprises a first supporting bearing, a second supporting bearing, a first motor, a second motor, a third motor, a first azimuth angle adjustment unit, a second azimuth angle adjustment unit, a third azimuth angle adjustment unit, an azimuth angle control unit, a three-axis inertial stabilization platform, a rotor unmanned aerial vehicle and a digital aerial photography camera, wherein the three-axis inertial stabilization platform is respectively connected with the rotor unmanned aerial vehicle and the digital aerial photography camera; the azimuth angle control unit is respectively connected with the first azimuth angle adjustment unit, the second azimuth angle adjustment unit and the third azimuth angle adjustment unit; the first azimuth angle adjustment unit is respectively connected with the first supporting bearing and the first motor; the second azimuth angle adjustment unit is respectively connected with the second supporting bearing and the second motor; and the third azimuth angle adjustment unit is connected with the third motor. According to the unmanned aerial vehicle remote sensing system disclosed by the invention, the aerial photographing precision and efficiency can be improved.

The invention provides an unmanned aircraft releasing mechanism. The unmanned aircraft releasing mechanism comprises a steering engine, a tiller, a transmission rod and a mounting block, wherein the steering engine comprises an output shaft; one end of the tiller is fixedly connected to the output shaft; one end of a connecting rod and the other end of the tiller are in hinged connected with a latch rod, and one end of the latch rod is hinged to the other end of the connecting rod; the mounting block is fixedly mounted on the steering engine; a clamping slot is formed in the middle of the mounting block; a through hole is formed in the mounting block in the horizontal direction; the other end of the latch rod penetrates through the through hole and extends into the clamping slot; the inner wall of one side, away from the tiller, of the clamping slot is abutted against the other end of the latch rod; and driven by the steering engine, the latch rod can do reciprocating motion in the through hole. The unmanned aircraft releasing mechanism provided by the invention is stable to fly and long in cruising duration.

The invention relates to the technical field of aircrafts and particularly relates to a water spraying aircraft which comprises an aircraft shell, a driving mechanism, a water supply mechanism and water spraying mechanisms, wherein the water supply mechanism is connected with the water spraying mechanisms, and the water spraying mechanisms are mounted on the aircraft shell in a deflectable way along the vertical direction; and the driving mechanism comprises a plurality of driving assemblies, and each of the driving assemblies is respectively connected with a water spraying mechanism so as to supply acting forces in multiple directions for the water spraying mechanisms. During use, the plurality of driving assemblies apply acting forces in different directions and sizes to the water spraying mechanisms, the water spraying mechanisms can deflect in different directions under the effect of multiple acting forces, the water sprayed from the water spraying mechanisms supplies a reverse thrust to an aircraft body, the magnitude of the thrust is adjusted according to the water supply quantity, the control on the flight attitude of the aircraft can be realized by virtue of the effects of the driving mechanism and the water supply mechanism, and the attitude of the aircraft does not need to be adjusted by adjusting the center of gravity according to the attitude of a person, so that unmanned driving can be realized, and the operation is simple.

The embodiment of the invention discloses an unmanned aerial vehicle remote sensing device and method. The unmanned aerial vehicle remote sensing device comprises a first support bearing, a second support bearing, a first motor, a second motor, a third motor, a first azimuth regulation unit, a second azimuth regulation unit, a third azimuth regulation unit and an azimuth control unit, wherein the azimuth control unit is connected with the first azimuth regulation unit, the second azimuth regulation unit and the third azimuth regulation unit respectively; the first azimuth regulation unit is further connected with the first support bearing and the first motor respectively; the second azimuth regulation unit is connected with the second support bearing and the second motor respectively; the third azimuth regulation unit is connected with the third motor. Due to the application of the unmanned aerial vehicle remote sensing device disclosed by the invention, the accuracy and efficiency of aerial photography can be improved effectively.

The invention relates to a vertical takeoff power supply system, a fixed wing unmanned aerial vehicle and a working method. The vertical takeoff power supply system comprises a power source power supply device located on the ground. The power source power supply device is suitable for keeping supplying power to the unmanned aerial vehicle when the unmanned aerial vehicle vertically takes off. After the unmanned aerial vehicle reaches the preset height, the unmanned aerial vehicle is separated from power supply of the power source power supply device. The power source power supply device is used for continuously supplying power to the unmanned aerial vehicle when the unmanned aerial vehicle vertically takes off, the requirement for vertical takeoff electric energy is met, electric energy consumption of the unmanned aerial vehicle is greatly reduced, the cruising mileage of the unmanned aerial vehicle is increased, and the cruising time of the unmanned aerial vehicle is prolonged.

The invention discloses a method and device for calibrating a flying control gyroscope, an electronic device and a storage medium, and relates to the technical field of unmanned aerial vehicles. A zero deviation value of the gyroscope can be calculated in real time, jumps of the gyroscope data used for navigation solutions are avoided, meanwhile, the deviation of zero deviation in successive starting of the gyroscope is also avoided to ensure that the flight posture is stable and normal flight is achieved. The method comprises the following steps of: acquiring an output angular velocity of thegyroscope for each time and a counting value corresponding to the angular velocity; detecting whether an aircraft to which the flight control belongs is in a static state or not according to the output angular velocity of each gyroscope; if the aircraft to which the flight control belongs is determined to be in the static state, accumulating the angular velocity output by the gyroscope for each time according to the counting value corresponding to the angular velocity to obtain an average value to obtain a gyroscope zero deviation corresponding to the counting value; and if the counting valuecorresponding to the angular velocity reaches a preset value, finishing gyroscope calibration and outputting the zero deivation corresponding to the counting value.

The invention discloses a power supplying system for an electric car. The power supplying system for the electric car comprises a plurality of power transmitting rods, power transmitting rails, guide rail vehicles, air vehicles and guide wires, wherein the power transmitting rods are fixedly installed on the two sides of a road, the power transmitting rails are installed between the power transmitting rods, the guide rail vehicles are installed on the power transmitting rails in a rolling or slidable mode and electrically connected with the power transmitting rails, each air vehicle can stop on the electric car and electrically connected with the electric car, and the guide wires are connected between the guide rail vehicles and the air vehicles and used for transmitting electric energy from the power transmitting rails to the electric car. According to the power supplying system for the electric car, the function that the electric car can be charged with no-needing stopping is achieved, through the match of the air vehicles and the guide rail vehicles, the fact that the electric energy can be transmitted from the power transmitting rails to the electric car is achieved, in this way, the electric car can be separated from the air vehicles at any time under the condition of full of electricity or the other conditions, and free traveling of the electric car cannot be limited.

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 an electric unmanned helicopter, and aims to provide the electric unmanned helicopter having advantages of simple structure, easy disassembly and assembly, good interchangeability, high integration, good functionality, light weight, strong load capacity, long endurance, good stability, small vibration, adjustable gravity center and the like. The electric unmanned helicopterprovided by the invention comprises a front end module, a middle end module and a rear end module which are sequentially connected, wherein the front end module comprises a left carbon fiber board and a right carbon fiber board which are symmetrically arranged; an image and data transmission device, an electronic speed regulating device and a load mounting board are arranged between the left carbon fiber board and the right carbon fiber board; the middle end module comprises an upper carbon fiber board, a lower carbon fiber board arranged below the upper carbon fiber board, and main power systems arranged on the upper carbon fiber board and the lower carbon fiber board; the rear end module comprises a tail tube and a tail rotor system arranged at a tail end of the tail tube. The electricunmanned helicopter provided by the invention is applied to the technical field of electric unmanned helicopters.

A pair of large propellers is used for constructing ''reversing propellers with a common rod'', rotating shafts of two propeller disks and a rod form an isoceles triangle, the lower surfaces of the two propeller disks are positioned at an arc line, and the length of the rod is longer than the diameter of the propeller disks; a pair of small propellers is used for constructing ''reversing propellers with a common shaft'', and the small propellers are made in the shape of arcs; through several carbon fiber tubes and connecting fixing pieces, the ''reversing propellers with a common rod'' and the ''reversing propellers with a common shaft'' form a four-rotor unmanned aerial vehicle structure which is in mirror symmetry in left and right and asymmetrical in front and back, and the rod is perpendicular to the shaft; the direction of downwash flow is the direction of an outward normal of cambered surfaces; therefore, the four-rotor agricultural unmanned aerial vehicle with the blades in cambered surface distribution is named. Compared with a four-rotor unmanned aerial vehicle with blades in the structure of horizontal distribution and central symmetry sold in the market, the four-rotor agricultural unmanned aerial vehicle with the blades in cambered surface distribution has the advantages that the flow rate of the downwash flow is effectively reduced, the area of the downwash flow is enlarged, crops are protected, and the working performance is improved.

The invention provides a spiral line mobility model construction method based on an SDN, which is used for solving the problems of unsmooth track and inaccurate coverage of an existing model in searchand rescue scenes. According to the scheme, the method comprises the following steps: 1) constructing an application layer including a search and rescue control center and a field command vehicle forcommanding a search and rescue team to enter a disaster area; 2) constructing a control layer to collect emergency events occurring in a scene, calibrating priorities of the emergency events, sortingthe emergency events, and generating a target area search list according to an event sequence; 3) generating unmanned aerial vehicle moving track data according to the region search list provided bythe control layer, and establishing a data layer; 4) enabling the application layer, the control layer and the data layer to jointly form an SDN-based spiral line mobility model, and employing the model to complete the coverage of the disaster area. According to the invention, the smoothness of the flight path is ensured, and the accurate search of the target area is realized; the system can be used for searching and rescuing victims in disaster scenes and providing temporary aerial base stations for the victims.

The invention provides a guide spray pipe of a rotary detonation combustion chamber. The guide spray pipe comprises a rotary detonation combustion chamber body and a guide spray pipe body. Inert media are jetted at one side of an ignition system, and detonation waves can only be propagated in the reverse direction away from the inert media after ignition so as to control the rotational flow direction of outlet airflow. The guide spray pipe is arranged at a combustion chamber outlet, a guide blade of the guide spray pipe is fixed by a guide spray pipe outer ring and a center body, a front half section mean camber line of the blade is bent, the front edge direction is consistent with the airflow deflection angle of the combustion chamber outlet, and a rear half section mean camber line is a straight line, and the direction is consistent with the axial direction of the combustion chamber; and the circumferential velocity of the airflow at the combustion chamber outlet is deflected to be the axial velocity, and the expansion acceleration continues until the airflow is discharged in the axial direction. According to the guide spray pipe, the circumferential kinetic energy of the airflow in the rotary detonation combustion chamber can be effectively utilized, so that the torque generated by rotational flow in the original exhaust process can be eliminated, the flight attitude of an aircraft can be stabilized, and the overall propulsion performance can be improved. The guide spray pipe can be used in the fields of detonation propulsion and the like.

The invention provides a water surface flapping wing flying robot. The water surface flapping wing flying robot comprises a main body supporting frame, flapping wings, a driving system and a water surface supporting system, the main body supporting frame is located on the upper portion of the robot, the driving system comprises a motor, a gear speed reduction set, a crank sliding block mechanism and two four-bar mechanisms, the motor is installed on the lower side of the main body supporting frame, and the gear speed reduction set is installed in the main body supporting frame; the crank sliding block mechanism and the four-connecting-rod mechanisms are installed above the main body supporting frame, the two four-connecting-rod mechanisms are symmetrically arranged on the two sides of the crank sliding block mechanism, and the two four-connecting-rod mechanisms are both connected with the output end of the crank sliding block mechanism; two flapping wings are arranged and are symmetrically arranged on the left side and the right side of the main body supporting frame and connected to the output ends of the four-connecting-rod mechanisms on the corresponding sides, and the water surface supporting systems are installed under motors of the driving systems. Water surface floating and flapping wing flying are combined, the near-water space movement range of the robot is expanded, and maneuverability and flexibility are enhanced.

The invention discloses a power bearing structure for an unmanned aerial vehicle, belonging to the technical field of the unmanned aerial vehicle, comprising a bearing component, a shock absorbing component and a power mechanism. The load bearing member includes a first support arm and a second support arm. The shock absorbing member includes a first stop lever, a second stop lever, a first resilient assembly, and a second resilient assembly. The first elastic assembly is sleeved on the exterior of the first limit lever, and the second elastic assembly is sleeved on the exterior of the secondlimit lever. The power mechanism comprises a first steering gear and a second steering gear, and the first steering gear comprises a first housing and a first rotating shaft; the second steering gearincludes a second housing and a second shaft. The invention can shoot the glass doors and windows at any time when the unmanned aerial vehicle is in various flight positions. Reducing the recoil forceproduced by shooting and stabilizing the flight attitude of unmanned aerial vehicle (UAV) are beneficial to the technical effect of helping the trapped people to escape in high-rise residential buildings in time.

The invention provides a fixed-wing unmanned airplane release mechanism. The fixed-wing unmanned airplane release mechanism includes a steering machine, a steering wheel, a transmission rod, and a mounting block, wherein the steering machine comprises an output shaft; one end of the steering wheel is fixedly connected to the output shaft; a latching rod is hinged to one end of a connecting rod andthe other end of the steering wheel; one end of the latching rod is hinged to the other end of the connecting rod; the mounting block is fixedly mounted on the steering machine, a clamping groove isformed in the middle of the mounting block, a through hole is formed in the mounting block in the transverse direction, and the other end of the latching rod penetrates the through hole and extends into the clamping groove; the inner side wall, away from the steering wheel, of the clamping groove abuts against the other end of the latching rod; and the steering machine can drive the latching rod to reciprocate in the through hole. The unmanned airplane release mechanism is stable in flight and long in duration of flight.

The invention provides a fixed-wing unmanned airplane release mechanism. The fixed-wing unmanned airplane release mechanism includes a steering machine, a steering wheel, a transmission rod, and a mounting block, wherein the steering machine comprises an output shaft; one end of the steering wheel is fixedly connected to the output shaft; a latching rod is hinged to one end of a connecting rod andthe other end of the steering wheel; one end of the latching rod is hinged to the other end of the connecting rod; the mounting block is fixedly mounted on the steering machine, a clamping groove isformed in the middle of the mounting block, a through hole is formed in the mounting block in the transverse direction, and the other end of the latching rod penetrates the through hole and extends into the clamping groove; the inner side wall, away from the steering wheel, of the clamping groove abuts against the other end of the latching rod; and the steering machine can drive the latching rod to reciprocate in the through hole. The unmanned airplane release mechanism is stable in flight and long in duration of flight.