51results about How to "Slow flight" patented technology

The invention relates to a folding type unmanned plane. The unmanned plane comprises a fuselage and wings, wherein the wings are installed symmetrically on two sides of the fuselage; one end of each wing is hinged on a wing main shaft installed coaxially at the middle part inside the fuselage; wing access through-grooves are formed horizontally in two sides of the fuselage in the installation positions of the wings; and the wings are driven and controlled by an motor-driven or pneumatic device installed at the lower part inside the fuselage and rotate around the wing main shaft. The folding type unmanned plane can be used flexibly and rapidly; is mutifunctional, low in flight speed and altitude, high in response speed and wide in application range; can facilitate operation of a staff; has 'zero' preparation time; and can be applied to tasks such as exploration, search, rescue and measurement.

The invention provides a control method for UAV landing and a UAV, relating to the control field of UAVs. The embodiment of the invention can realize automatic recovery of the UAV, and can improve therecovery precision through carrying out corresponding control operations in the recovery process of the UAV. The method comprises the steps of: acquiring a recovery instruction by means of the UAV, and determining a designated landing point according to the recovery instruction; detecting a horizontal distance between the UAV and the designated landing point; performing a deceleration operation after determining that the horizontal distance between the UAV and the designated landing point meets a preset condition; controlling an engine of the UAV to rotate reversely when determining that a flight speed of the UAV is reduced to be within a preset speed range, so as to provide the UAV with reaction thrust; determining whether flight parameters of the UAV meet recovery requirements after theUAV enters a preset region; and executing a landing operation after determining that the flight parameters of the UAV meet the recovery requirements. The control method is used for controlling the UAV.

The invention discloses a mooring rope buoy hooking aerial low-speed unmanned aerial vehicle non-destructive recycling system and method, relates to the field of low-speed unmanned aerial vehicle recycling, and aims to solve the problem of poor adaptability of an aerial recycling mode of an existing fixed-wing unmanned aerial vehicle. A buoy and a capture device are arranged outside an aerial carrier, the aerial carrier keeps angular speed v and runs along a circular trace with a radius R, so that the buoy can keep the angular speed v and runs along a circular trace with a radius r, R>r, a navigation system acquires the movement trace of the buoy and transmits trace signals to a low-speed unmanned aerial vehicle, the low-speed unmanned aerial vehicle enters the circular trace with the radius r according to the trace signals and gradually approaches the buoy until a hooking device is connected with the capture device in a mounted manner, the low-speed unmanned aerial vehicle is recycledinto a cabin of the aerial carrier, and recycling of the low-speed unmanned aerial vehicle is finished. The system and the method are applicable to aerial underway recycling of the low-speed unmannedaerial vehicle without autonomous landing capacity.

The invention relates to the field of nuclear safety, and provides an intelligent searching device for a radioactive source, and an operating method of the intelligent searching device. The searching device comprises an aircraft, a radiation dose rate detector, a radioactive source position sensitive detector, a signal processing and analysis module, a remote communication module, an infrared radar, a video camera, a lithium battery pack, and a monitoring control module. The searching device is provided with the aircraft, the radiation dose rate detector and the radioactive source position sensitive detector, and can achieve the quick, high-efficiency and automatic searching of the radioactive source through an intelligent searching algorithm.

The invention discloses a landing buffering device for an unmanned aerial vehicle. The landing buffering device comprises an outer bag and an inner bag which is composed of an inflation framework. After being inflated, the inflation framework of the inner bag comprises four cylindrical main air columns in the same shape, the top surfaces of the main air columns are located on the top plane, and the bottom surfaces of the main air columns are located on the bottom plane. The main air columns are connected through side air columns and the projections of the side air columns on the top plane are distributed along the sides of a rectangle. The outer bag is used for wrapping the inner bag and is in a rectangular solid shape or a cube shape after being inflated, the height of the outer bag is larger than or equal to that of the main air columns, and the projection of the outer bag on the top plane covers the projections of the main air columns and the side air columns. The landing buffering device for the unmanned aerial vehicle can be in a fixed square shape after being inflated, the fixed shape of the unmanned aerial vehicle can be guaranteed in the landing process of the unmanned aerial vehicle, even though the unmanned aerial vehicle is affected by air resistance, the unmanned aerial vehicle does not impact on the ground directly, and therefore the good unmanned aerial vehicle protection effect can be achieved.

The invention provides an agricultural plant-protection levitation-type flight work platform, which solves the problems of the existing aircraft that the safety coefficient is not high and safety potential danger exists. The agricultural plant-protection levitation-type flight work platform comprises a levitation lifting body, a propelling part and a lifting part, wherein the lifting part is embedded in a central duct of the levitation lifting body and used for adjusting the operation height of the work platform in real time; and the levitation lifting body is connected with the propelling part, and the propelling part is used for supplying thrust and steering force needed by the flight. The agricultural plant-protection levitation-type flight work platform has the advantages of safety in use, low flight height, controllability in flight speed and suitability for distributing the plant-protection preparation and can prevent the problems such as the threat of facilities or personnel on the ground brought by the flight accident easily caused by the low safety coefficient and safety potential danger of the existing aircraft in the flight process; and through the control of a uniform command of a subarea control station, on the premise that the normal operation effect of the agricultural facilities is not influenced, completely-unmanned and automatic high-efficient agricultural plant-protection operation can be effectively realized.

The invention discloses a Cerenkov radiation device and a manufacturing method thereof, and a radiation extraction method. The Cerenkov radiation device comprises a metal cycle nanometer slit structure, a hyperbolic metamaterial structure and an electron-emitting source, wherein the hyperbolic metamaterial structure is arranged on an upper surface of the metal cycle nanometer slit structure; the electron-emitting source is arranged on an upper surface of the hyperbolic metamaterial structure; and the electron-emitting source includes an anode, a cathode and a grid electrode. The Cerenkov radiation device does not need a high voltage. A characteristic that a phase velocity of light in the hyperbolic metamaterial structure can be reduced by several orders of magnitudes compared to a velocity in a traditional material is used so that a required electronic flight speed generated by Cerenkov radiation can be greatly reduced; and then production cost generated by the Cerenkov radiation device is decreased and safety performance is increased.

The invention discloses a method for automatically identifying crop diseases by a plant protection unmanned aerial vehicle. The method comprises the following steps that: obtaining image information shot by the unmanned aerial vehicle on a preset proceeding route, and comparing the image information with a preset database; when the comparison result of the image information is a disease picture, reducing the flight speed of the unmanned aerial vehicle, and increasing the pesticide spraying amount of the unmanned aerial vehicle; and obtaining position information when the unmanned aerial vehicle shots the image information, and according to the position information, generating prompt information. The invention also relates to a device for automatically identifying crop diseases by the plantprotection unmanned aerial vehicle. The unmanned aerial vehicle is controlled to reduce the flight speed and increase the pesticide spraying amount, and pesticide spraying intensity is enlarged for crops on the positions of plant diseases and insect pests so as to reduce plant diseases and insect pests.

The invention discloses a multi-grain-size uniform spherical powder batch preparation device and method based on uniform metal droplet spraying. The multi-grain-size uniform spherical powder batch preparation device and method based on uniform metal droplet spraying are used for solving the technical problem that an existing uniform spherical metal powder preparation method is low in productivity. According to the technical scheme, electric signals are input into piezoelectric ceramics to generate mechanical vibration of the piezoelectric ceramics, generated mechanical vibration enables molten metal at nozzles to generate a certain speed, and accordingly a certain amount of metal fluid is sprayed out, and fluid sprayed each time forms a metal droplet. By controlling the pressure of the molten metal in the device and vibration of the piezoelectric ceramics, the droplets uniform in size and consistent in thermal history can be obtained. The flying speed of the droplets prepared through the method is low, the droplets can completely solidify within a very short flying distance, and the droplets are small in vibration and high in degree of sphericity. The multiple piezoelectric ceramics are installed on the device in the longitudinal direction and the transverse direction, and meanwhile, the multi-spraying-hole nozzles of different sizes are used for preparing a large amount of multi-grain-size uniform spherical powder at a time.

The invention discloses a charging, blocking and slag pressing structure of demolition blasting blast-holes of a reinforced concrete beam and a demolition blasting method. The demolition blasting method is characterized in that the technical measures of disconnecting stirrups arranged at one side or two sides of the reinforced concrete beam, blocking the blast-holes by using gypsum which is mixed with an adhesion agent and pressing the blast-holes by using water bags are adopted, and thus the contradiction between the demolition blasting effect of the reinforced concrete beam and safety as well as between the demolition blasting effect and environment protection is well solved. The charging, blocking and slag pressing structure and the demolition blasting method, disclosed by the invention, have the beneficial effects that the technical measures are jointly adopted, thus the bounding stress of the stirrups on concrete during blasting is reduced, the blasting and crushing effect is improved, and blasting safety protection and blasting dust control are facilitated; the construction is convenient, the explosive consumption and the post processing and cleaning cost are reduced, and significant economic and environment benefits are obtained.

The invention discloses a solid carrier rocket sub-stage capable of being recycled and reused. The solid carrier rocket sub-stage comprises a sub-stage body, an inflatable heat protection structure and a solid rocket engine; the inflatable heat protection structure comprises a front-end airbag which covers the windward side of a front cabin section under an expanding state and is in a shape of a rotating body, and the front-end airbag comprises a flexible heat-insulating layer and a heat-proof coating which are sequentially arranged from inside to outside; and the solid rocket engine comprisesa combustion chamber shell with a cavity allowing a grain to be placed, and a combustion chamber heat protection structure is arranged on the inner wall of the combustion chamber shell. By adopting the inflatable heat protection structure with heat protection, deceleration and buffering combined, the front-end airbag can maintain the good aerodynamic shape, the sub-stage is not damaged due to pneumatic heating and large landing impact force in the reentry process, and can be recycled, through re-charging, replacing of disposable parts and the like of the rocket engine, the sub-stage and the engine thereof can be reused, and thus the launching cost of a solid carrier rocket is lowered.

The invention relates to a double-wing superaltitude pilotless aircraft which flies in relative static condition used for carrying an aerial wireless mobile communication base station device, and the pilotless aircraft overcomes the defect that a subsonic pilotless aircraft or a supersonic pilotless aircraft is not suitable for an aerial base station bearing platform because the speed is too high. The invention comprises a pilotless aircraft body; the adoption of the structure of double wings or double vertical tails is suitable for the flying in a superaltitude and low air mass density environment; and the maximum lift force and a lift-off limit of an altitude of 20-30 km is achieved. The pilotless aircraft body of the invention further comprises the adoption of a double-set supply system of oxidant of fuel, liquid oxygen and the like, thereby ensuring normal flying of the pilotless aircraft body in a superaltitude and low air mass density environment, and providing the needed power; and the motor can be a single-station motor or a double-station motor. The pilotless aircraft body of the invention can be particularly suitable for superaltitude, low air mass density and anoxic environments; the stability and the safety of the aircraft can be guaranteed in appropriate low-velocity flying; the flying in relative static condition is accomplished; and the task of receiving and transferring communication signals of 3G and 4G is fulfilled.

The invention relates to a terrestrial, marine and aerial remote control electric simulation model airplane, which belongs to sports entertainments, children toys and science popularization devices for students in middle and primary schools, and is characterized in that two lower end faces of a left pontoon alighting gear (1) and a right pontoon alighting gear (2) are fixedly provided with two damping airplane wheels (3) respectively, the upper end faces of the left pontoon alighting gear (1) and the right pontoon alighting gear (2) are provided with a mounting fixed folding wing groove (4) respectively, a folding wing (5) is put into and mounted in the fixed folding wing groove (4) and is fixed by a rubber band (6), two rubber bands (7) are crossed to fix the folding wing (5) under a plane body (8), and the front part of an airscrew (10) is fixedly provided with an elastic safe cowling (9). Compared with a common model airplane, the terrestrial, marine and aerial remote control electric simulation model airplane also has the following three outstanding characteristics: firstly, the elastic safe cowling is arranged in front of the model airplane to prolong the service life of the model airplane; secondly, according to the requirement, the model airplane can be disassembled and assembled in a short time; and thirdly, the model airplane has light weight and low flying speed and can run and fly on a small field and a small water surface. With the three outstanding characteristics, the product of the model airplane has good application range and extensive market prospect in adult sports entertainment, the children toys and the science popularization devices for the students in the middle and primary schools.

A vertical take-off and landing unmanned plane includes a fuselage, wings, a first motor, a first propeller, a second motor and a second propeller, the first motor comprises a first motor bearing, the angle between the first motor bearing axis and the fuselage axis is 0-degree, the first propeller is connected with the first motor bearing; the second motor includes a second motor bearing, the angle between the projection line of the second motor bearing axis on the fuselage symmetry plane and the fuselage axis is greater than 0-degree, and the second propeller is connected with the second motor bearing. The first motor of the vertical take-off and landing unmanned plane drives the first propeller to produce a force parallel to the fuselage axis, so that the vertical take-off and landing unmanned plane can horizontally fly at high speed. The second motor can drive the second propeller to produce a lifting force, so that the vertical take-off and landing unmanned plane can achieve zero horizontal flight taking off and landing or hovering in the air.

The invention discloses a multi-unmanned aerial vehicle gas leakage source positioning method based on an improved particle swarm algorithm. The multi-unmanned aerial vehicle gas leakage source positioning method is mainly used for efficiently and accurately positioning a gas leakage source. The method is combined with human psychology, so that the method is more intelligent. People become more careful when approaching success. The mind of a person is simulated, particles become careful when being closer to a pollution source, the speed of the particles is slowed down, and the particles move carefully. According to the method, a basic particle swarm algorithm is adopted in the initial stage of iteration, so that a particle swarm searches in a large range in a gas leakage area. When particles exceed a threshold value, layered iteration is started. The residual electric quantity of the unmanned aerial vehicle and the influence of the searched gas leakage source are taken as measurement indexes of a prudent factor, the prudent factor is added when the speed of a positive particle layer is updated, so that particles are subjected to more detailed local search, and the driving effect of the positive particle layer is added when the speed of a negative particle layer is updated, so that the search efficiency is improved, and efficient positioning of a gas leakage source is realized.

The invention relates to a disposal system for controlling the maximum allowable speed of an unmanned aerial vehicle, comprising: a control computer, a speed sensor, a rudder surface control system, a throttle control system and / or a parachute system connected through the computer. Among them, it is equipped with a control computer that provides a timing interruption not greater than 120ms, and is equipped with a maximum speed fault handling program component that judges whether it is necessary to control the aircraft speed according to the speed provided by the airspeed sensor. The program component is composed of a speed over-limit control module for controlling computer timing interruption start and a maximum speed fault handling control module. On the one hand, the invention limits the flight of the aircraft within the maximum allowable flight speed range; on the other hand, when the aircraft speed exceeds the maximum speed and fails to be controlled, the aircraft pitch angle is controlled by the program components so that the aircraft is always within the allowable speed range Fly, or control the plane to return home or open the parachute in time to avoid flight accidents caused by the speeding of the plane.

The invention discloses a Ubuntu-based control system and method for improving the flight efficiency of an unmanned aerial vehicle. The system is composed of an acquisition device, an unmanned aerialvehicle, a flight control device, a wireless data transmission device, a wireless image transmission device, a PC-side ground station. The acquisition device arranged at the unmanned aerial vehicle isused for collecting a large-area panoramic image around the unmanned aerial vehicle and sending the panoramic image data to the flight control device; the flight control device arranged at the unmanned aerial vehicle is used for controlling the flight track of the unmanned aerial vehicle and sending the panoramic image data to the PC-side ground station; the PC-side ground station is used for displaying the panoramic image collected by the acquisition device; the wireless data transmission device is used for transmitting flight parameters between the PC-side ground station and the flight control device; and the wireless image transmission device is used for transmitting panoramic image data between the PC-side ground station and the flight control device. Therefore, the unmanned aerial vehicle is able to increase the flight speed when flying over a non-interest area and reduce the flight speed when flying over an area of interest, so that the electricity of the battery is saved and the flight efficiency is improved.

The invention discloses an airborne sounding aircraft, which comprises a casing, a pitot tube is arranged at the front end of the casing, a folding airfoil is arranged on the outer surface of the middle part of the casing, an air rudder plate and a steering gear are placed on the outer surface of the rear end of the casing The casing is provided with a detection communication device, a battery, a fuel tank, an autopilot and a turbojet engine, the detection communication device is electrically connected to a pitot tube, and the casing is also connected to an air intake. The invention can be mounted on a high-altitude and long-endurance drone, and the drone can be used to detect the wind speed, wind direction, temperature, pressure, and humidity data inside the typhoon, and use the drone as a relay platform to transmit the data back to the command center. Realize remote, fast, accurate, safe and flexible detection of typhoon.

The invention discloses an anti-splashing metal cutting device, and relates to the technical field of metal cutting. The technical problems that in the prior art, sparks generated during cutting of acutting machine are that high-speed friction produces high temperature to instantaneously burn powder brought down by a saw blade and the burnt power leaves the saw blade at a high speed under the action of centrifugal force to splash to the periphery of a cutting environment, traditional cooling water can only reduce the temperature of the powder and cannot prevent the powder from splashing, andthicker powder can continue to burn in the flying process are solved. A cutting workbench is arranged on the upper part of a cutting base, the cutting workbench is connected with the cutting base through bolts, a laser cutting machine box is arranged on the upper part of the cutting workbench, the laser cutting machine box is fixedly connected with the cutting workbench, a mechanical cutting shaftarm is arranged on the upper part of the laser cutting machine box, the mechanical cutting shaft arm is connected with the laser cutting machine box through screws, and a laser cutting machine head is arranged at one end of the mechanical cutting shaft arm.

The invention discloses an unmanned aerial vehicle-mounted window breaking bomb. The unmanned aerial vehicle-mounted window breaking bomb comprises a shell, a conical warhead located at the front endof the shell and a rocket engine located at the tail end of the shell. The rocket engine is used for providing flight power for the window breaking bomb. At least two prefabricated grooves are formedin the inner wall of the conical warhead. Through the mode of using the rocket engine to provide the flight power for the window breaking bomb, the window breaking bomb can impact a glass window witha higher flight speed, a larger impact force and a more accurate impact position, and thus the window breaking reliability of the window breaking bomb is improved. By forming the prefabricated groovesin the inner wall of the conical warhead, the structural strength of the corresponding position of the conical warhead can be decreased. After impacting the glass window, the conical warhead is automatically separated along the prefabricated grooves, so the aerodynamics of the bomb is changed, and a remaining bomb body stops flying linearly and falls to the ground with the flight direction changed rapidly, thereby ensuring avoidance of secondary damage after the window breaking bomb enters a room.

The invention relates to an obstacle avoidance method for unmanned aerial vehicle routing inspection safe return. The method comprises the steps of collecting image information to judge the actual height of an unmanned aerial vehicle; readjusting the maximum flight height and the maximum flight speed according to the absolute distance between the unmanned aerial vehicle and the stop point; if the distance between the object in the environment and the unmanned aerial vehicle is smaller than the critical safety distance, enabling the central control processor to control the unmanned aerial vehicle to move; and when the unmanned aerial vehicle enters the parking stage, enabling the central control processor to control the unmanned aerial vehicle to land at the parking point. According to the invention, by collecting the image information of the surrounding environment of the unmanned aerial vehicle, the surrounding environment information of the unmanned aerial vehicle can be quickly obtained, so that the central control processor can quickly obtain the flight height and the flight speed of the unmanned aerial vehicle according to the actual situation, and meanwhile, obstacles appearing in the flight process of the unmanned aerial vehicle are predicted in advance, the situation that the unmanned aerial vehicle is damaged or crashed due to collision between the unmanned aerial vehicle and the obstacle can be effectively avoided, and the inspection efficiency of the unmanned aerial vehicle is effectively improved.

The invention relates to the field of unmanned aerial vehicle obstacle avoidance methods, in particular to an obstacle avoidance detection system for an unmanned aerial vehicle, which comprises a main detection module, a processing module, a flight control module, a background server, a positioning module and an auxiliary detection module, the main detection module detects obstacle information in front of the unmanned aerial vehicle; the processing module obtains parameter information from the obtained obstacle information; the flight control module controls the unmanned aerial vehicle to avoid obstacles according to the parameter information; the positioning module carries out real-time positioning on the flight position of the unmanned aerial vehicle, the processing module judges the probability that net wall obstacles exist in the flight environment of the unmanned aerial vehicle according to the flight position, when the probability is larger than a preset value, the processing module preliminarily judges whether the net wall obstacles exist or not, and if yes, auxiliary permission information of the auxiliary detection module is obtained from the background server; the processing module sends a starting signal to the auxiliary detection module; and the auxiliary detection module pumps air according to the starting signal to carry out auxiliary detection on obstacles. The probability that the unmanned aerial vehicle collides with a net wall obstacle is reduced.

The invention discloses a tandem wing layout solar unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles and comprises a fuselage, a cabin is arranged at the front end of the fuselage, and a fuselage rod is arranged at the rear end of the fuselage; an upper wing and a lower wing which are arranged on the upper side and the lower side of the cabin respectively, and the upper wing and the lower wing are connected through side plates arranged on the two sides of the cabin to form a frame type structure; solar cell panels which are laid on the upper surfaces of the upper wing and the lower wing; an empennage which is arranged at the tail part of the fuselage rod; a propeller which is arranged at the front end of the cabin; and an undercarriage which is arranged on the lower side of the tandem wing layout solar unmanned aerial vehicle; the tandem wing layout solar unmanned aerial vehicle is provided with the upper wing and the lower wing, the effective wing area is increased, and the wing load is low; the wing area is increased, and the laying area of the solar cell panel is enlarged; the upper wing and the lower wing are connected through the side plates to form a frame structure, the structural rigidity is improved, and wing deformation is reduced; the flight speed and the flight power consumption are reduced.

The invention discloses a solar unmanned aerial vehicle which comprises an unmanned aerial vehicle main body, wings are symmetrically mounted at the top of the unmanned aerial vehicle main body, a mounting groove is formed in the top of the unmanned aerial vehicle main body, a photovoltaic panel is mounted in the mounting groove, the photovoltaic panel is electrically connected with the unmanned aerial vehicle main body, and control blocks are mounted at the two ends of the photovoltaic panel; and a control groove is formed in one side of each control block, and the control blocks are rotatably connected with the inner wall of the mounting groove. According to the solar unmanned aerial vehicle device, the problems that the utilization efficiency of a photovoltaic panel is reduced and the reliability of solar standby energy is reduced when obstacles adhere to the surface are solved, the shock resistance is enhanced, the problem that internal parts are prone to being damaged when the unmanned aerial vehicle collides with the obstacles in the air can be avoided, the service life of the unmanned aerial vehicle is prolonged, the heat dissipation capacity is enhanced, and the unmanned aerial vehicle can adapt to long-time flight in a high-temperature environment.