31results about How to "Flying fast" patented technology

The invention provides a forest fire prevention unmanned aerial vehicle patrol early warning system and method based on edge calculation, and relates to the technical field of unmanned aerial vehicle patrol early warning. The patrol early warning system comprises an unmanned aerial vehicle platform, a data acquisition module, a data processing and analysis module, a communication and early warning module and a ground control and scheduling platform. According to the invention, calculation and data storage are close to a data source through edge calculation, the data collected by the unmanned aerial vehicle is processed in real time at an edge calculation node without being transmitted to a remote cloud and returning a result, the data processing and response time is greatly shortened, fire hazards can be found in seconds or even shorter time, and early warning can be given out. And the system can analyze data in real time in the flight process of the unmanned aerial vehicle, provides real-time decision support for a ground control center, and can quickly formulate a fire-fighting scheme according to information such as fire behavior and wind direction when a fire occurs, so that the fire-fighting efficiency is improved.

The invention provides a Raney nickel electrode preparation method which comprises the following steps: 1, taking nickel powder with the particle size of 15-75 microns, nickel powder with the particle size of 75-150 microns and aluminum powder with the particle size of 15-75 microns, pouring the nickel powder, the nickel powder and the aluminum powder into a mixer, uniformly mixing without segregation phenomenon, and enabling the nickel powder, the nickel powder and the aluminum powder to respectively account for 70%-79%, 1%-10% and 20%; secondly, a plasma spraying technology is adopted, the temperature is regulated and controlled, so that the nickel powder and the aluminum powder with the particle size being 15-75 micrometers reach a molten state, and the nickel powder with the particle size being 75-150 micrometers reach a semi-molten state; spraying to a nickel net, and activating, cleaning and cutting to obtain a Raney nickel electrode; the nickel powder and the aluminum powder with different particle sizes are reasonably matched in the powder formula, the particle flying speed in spraying is properly increased, the spraying temperature is balanced, the powder with different particle sizes reaches different molten states, and therefore the large-particle nickel powder forms a good support in the coating, the bonding strength of the coating is remarkably improved, and the service life of the coating is prolonged. And the catalyst is not easy to fall off in the use process, so that the efficiency and the stability of the water electrolysis hydrogen production equipment are improved.

The invention relates to an airport aid-to-navigation light inspection method based on an unmanned aerial vehicle technology, and relates to the technical field of aid-to-navigation light inspection, and the method comprises the following steps: S1, setting standard parameters; s2, the unmanned aerial vehicle executes a flight task, and images are collected from multiple angles; s3, obtaining the mass center of the navigation aid lamp; s4, calculating actual geographic coordinates of the navigation aid lamp; s5, comparing the position coordinate information of the navigation aid lamp; s6, brightness attenuation detection of the navigation aid lamp; and S7, carrying out statistical feedback, and carrying out the step S2. The airport navigational light inspection method has the effects of reducing and improving the airport navigational light inspection cost and improving the airport navigational light inspection efficiency.

The invention provides a dual-rotor water-air amphibious unmanned aerial vehicle with a plume-like electric eel structure, which comprises a main body assembly, and the main body assembly comprises a triangular bracket, a fuselage main body, an electric eel driving mechanism, a rotary connecting piece, a U-shaped clamping groove, the plume-like electric eel structure and a load platform. According to the unmanned aerial vehicle, the line-like electric eel structures are arranged on the two sides of the fuselage main body, so that the unmanned aerial vehicle can enter and exit water without an underwater propeller or mode switching, and the structures are low in movement energy consumption, so that the unmanned aerial vehicle has the capability of working for a long time and can be flexibly switched between an air mode and a water mode; meanwhile, the system has excellent performances such as ultra-silence, high endurance and high efficiency; according to the invention, the attitude control is realized through a double-rotor structure consisting of the waterproof brushless motor, the output shaft and the folding propeller assembly and through the tilting mechanisms which are mounted front and back, the tilting mechanisms enable the rotors to deflect, different attitudes and motions can be realized through different tilting directions and tilting speeds, and the attitude stability and the motion control are enhanced.

The invention discloses a sea-land-air triphibian robot, and belongs to the technical field of unmanned operation equipment, the sea-land-air triphibian robot comprises a bottom plate, a wing conversion mechanism and a flight control assembly are fixedly connected to the bottom plate, and an underwater operation mechanism is fixedly connected to the bottom of the bottom plate; a first propulsion propeller is fixedly connected to the tail end of the bottom plate, a wing bracket is fixedly connected to the front end of the bottom plate, wings are hinged to the two sides of the wing bracket through spherical hinges, a rotor mechanism is fixedly connected to the wings, and an undercarriage is fixedly connected to the tail end of the rotor mechanism; the wing conversion mechanism drives the wings to stretch out, draw back and rotate with the spherical hinge as the axis. The unmanned aerial vehicle can realize cross-domain collaborative operation, can take off and work under various conditions such as a ship-based condition, a land-based condition and a sea-based condition, is compact in overall structure and convenient to transport, solves the problems that a traditional fixed-wing unmanned aerial vehicle is too large in transportation size and needs a large take-off and landing site, and also solves the problem that a traditional rotor unmanned aerial vehicle is low in flight speed.

The invention discloses an unmanned aerial vehicle flight path planning method and system for electric power operation and maintenance, and relates to the technical field of path planning. The method comprises the steps of collecting data in a to-be-planned flight area; acquiring a three-dimensional point cloud map of the global environment; obtaining a flight path planning area; determining a final flight path based on the starting place and the destination of the unmanned aerial vehicle; obstacle avoidance planning and power grid inspection are carried out in the flight process on the final flight path; and the flight state of the unmanned aerial vehicle is monitored in real time, and flight data are recorded, adjusted and optimized. According to the invention, from data acquisition, map generation, path planning and obstacle avoidance planning, and finally power grid inspection and feedback optimization, a complete path planning and obstacle avoidance inspection process is realized through the above contents, and the flight path of the unmanned aerial vehicle in power operation and maintenance is systematically and intelligently planned. The unmanned aerial vehicle can quickly and accurately complete the inspection task, invalid flight is avoided, the inspection efficiency and safety are improved, and reliable operation of electric power facilities is ensured.

The propaganda display device belongs to the technical field of propaganda display, not only can passively display propaganda materials, but also can display learning conditions through the status bar arranged on the edge of the propaganda column, so that the learning conditions displayed in the status bar can be obtained, learning objects can select learning time and content, and the learning efficiency is improved. The display rack can send a learning site to the display rack, after receiving learning related information, the display rack can send a propaganda unmanned aerial vehicle to convey related learning materials and a projector with propaganda content in place for learning, and after learning is completed, the display rack can report the learning situation back to the display rack; and then the corresponding learning condition is updated through the status bar, so that the functions of supervising and conveying learning materials are added.

The invention discloses a preparation method of a silicon nitride composite structural part, and relates to the technical field of thermal protection parts of overspeed aircrafts. According to the method, the functional gradient principle is adopted, ZrO2 is doped into one layer to achieve the high temperature resistance of the material, the high-temperature resistance of the material is further improved by adopting a porous technology, the physical strength of the whole component is compensated for by adopting a high-toughness and high-strength technology for the second layer, and the ZrO2 is subjected to conversion from a monoclinic phase to a tetragonal phase and then to a cubic phase in the heating process. The phase change process can absorb a large amount of energy along with the change of the volume, so that the toughness of the material is improved, the outer temperature-resistant layer is prepared, the characteristic of the strength of the silicon nitride material is exerted, and the inner force-bearing layer is prepared.

The landing structure of the unmanned air-ground aircraft comprises an installation support, two supporting devices, an installation hole, a limiting groove and a streamline fairing, the two supporting devices are symmetrically arranged and arranged on the two sides of the bottom end of the installation support, and the installation hole is formed in the installation hole. The supporting device comprises a first supporting plate, a second supporting plate, a servo motor, a mounting part and two supporting legs, the two supporting legs are symmetrically arranged, one end of each supporting leg is fixedly connected to the first supporting plate, and the other end of each supporting leg is rotationally connected to the interior of the mounting part. The supporting device can be freely folded and unfolded, the streamline fairing is installed, the folded supporting device is effectively shielded, therefore, wind resistance during flight is reduced, the flight speed of the aircraft can be increased, and meanwhile the risk that the supporting plate is hung by branches or other foreign matter in the flight process is avoided through the design of the fairing.

The invention relates to the field of aircrafts, in particular to a portable single-person low-altitude vector jet aircraft with a folding wing structure, the portable single-person low-altitude vector jet aircraft comprises a rack part, a power part and a load part, the power part is arranged below the rack part, and the load part is arranged below the power part; according to the portable single-person low-altitude vector jet aircraft with the folding wing structure, through the design of the telescopic framework of a multi-connecting-rod structure, the aircraft can be easily folded when not used, the occupied space is small, carrying and storage are convenient, and the problems that a traditional single-person aircraft is large in size and difficult to carry are solved; the applicability and convenience of the aircraft are improved; meanwhile, the structural strength of the wings in the unfolded state is ensured through the multi-point supporting design of the telescopic framework, the stability and safety of the aircraft are improved, the air resistance of the aircraft is reduced through the design of the wing skin, the protective cover, the conical cover, the wind tunnel and the fairing, the aerodynamic performance is effectively improved, and the aircraft is more efficient in the flight process.

The light high-performance crawler-type platform suitable for the amphibious unmanned aerial vehicle is composed of the two racks, the control box and the two crawler-type walking mechanisms, and the structure is simple and compact. Through the design of a carbon fiber integrated rack and the optimization of a crawler-type walking structure, the land walking function and the flight function are efficiently coupled, and the lightweight design of the mechanism is achieved. The crawler belt adopts a middle convex meshing and clearance type bulge design, so that the road holding force and the obstacle crossing ability are improved, meanwhile, redundant structures are reduced, and the overall weight is reduced; the design of the inclined hollow machine arm gives consideration to light weight and stability, and an axial tensioning mechanism effectively avoids the falling risk. The platform has high stability, strong environment adaptability and operation flexibility, and is suitable for tasks of environment monitoring, disaster rescue and the like under complex terrains.

This utility model discloses an adjustable two-dimensional tail nozzle, belonging to the field of two-dimensional tail nozzle technology; it includes a connected engine and an adapter casing. A servo is provided on one side of the adapter casing. The output side of the adapter casing consists of a rectangular opening formed by two oppositely arranged fixed plates and two oppositely arranged adjusting plates. A power arm is provided at the output end of the servo. The right end of the power arm is connected to two parallel first connecting rods by a pin shaft. The other ends of the two first connecting rods are respectively connected to two second connecting rods. It can be applied to small afterburning turbojet engines to improve the flight speed of UAVs. Its structure is simple. The synchronous opening and closing movement of the adjusting plates is achieved through a single servo drive source, reducing the control difficulty, realizing engine thrust adjustment, reducing the number of structures, and making it lightweight, highly reliable, and low in cost. By setting a support rod on the outside of the adjusting plate, the adjusting plate can be limited. The structure is simple and the use effect is good.

The invention discloses a rotor unmanned aerial vehicle with a retractable unmanned aerial vehicle structure, and relates to the technical field of unmanned aerial vehicles, the rotor unmanned aerial vehicle comprises a fuselage, a bent frame is fixedly mounted on the outer surface of the fuselage, and a protective frame is fixedly mounted at the top of the bent frame; the retractable undercarriage is used for stably supporting the unmanned aerial vehicle; and a balance driving member. According to the rotor unmanned aerial vehicle with the retractable unmanned aerial vehicle structure, when the unmanned aerial vehicle lands, the supporting blocks make contact with the ground, and when the unmanned aerial vehicle lands, the supporting blocks are affected by the weight of the unmanned aerial vehicle and extrude the ground, so that when the obliquely-arranged supporting blocks make contact with the ground, the supporting blocks make contact with the ground; damping rods connected to the surfaces of positioning blocks are driven to rotate in clamping blocks through rotating rings according to the terrain influence, so that the contact angle between supporting blocks and the ground is adjusted when the unmanned aerial vehicle is parked, the supporting blocks arranged in multiple directions are attached to and matched with the ground at the moment, the unmanned aerial vehicle is parked stably, and the phenomenon that the unmanned aerial vehicle shakes during landing is avoided.

The invention relates to the technical field of measuring low-altitude meteorological parameters by using a laser radar, and discloses a low-altitude meteorological multi-parameter laser radar, which is characterized in that two light sources, namely an infrared light source and an ultraviolet light source, are controlled by a data processing and control system, and laser emission is carried out according to a certain time sequence; scattered light generated after the two light sources act with the atmosphere is received by the composite optical antenna, is processed by the data processing and control system, and is displayed by the display terminal. According to the optical composite optical antenna system, a conventional shielding secondary mirror is utilized through the design of a specific light splitting process, a structural form and a specific size while a conventional receiving sectional area is not influenced, so that the use efficiency is improved, simultaneous observation of a plurality of meteorological parameters can be realized, the overall size is small, and the antenna system is convenient to use. The system is convenient to deploy in low-altitude use scenes such as urban roofs, realizes rapid and accurate observation of low-altitude meteorological parameters, and guarantees the flight safety of low-altitude aircrafts.

This invention proposes a symmetrically arranged cross-wing unmanned aerial vehicle (UAV) system, relating to the field of UAVs. It includes a fuselage structure, a power module, and a flight control module. The fuselage structure comprises a cylindrical fuselage and four wings symmetrically arranged in a cross pattern around the cylindrical surface of the fuselage; the four wings are arranged in an X-shape or a cross shape. The power module includes motors and propellers. The motors are located at the wingtips, with their output shafts aligned with the fuselage axis and facing the tail of the fuselage. The propellers are connected to the motor output shafts. The flight control module is located inside the fuselage and is used to control the output speed of the four motors. This system combines the advantages of a quadcopter FPV and a fixed-wing UAV, generating lift from the wings while also cruising and sprinting in fixed-wing form. Furthermore, by changing the motor speeds, it can control the pitch, yaw, and roll attitude of the UAV, eliminating the need for separate control surfaces, thus simplifying the structure and reducing costs.

The utility model belongs to the technical field of surveying and mapping unmanned aerial vehicles, and particularly relates to a windproof mechanism for a surveying and mapping unmanned aerial vehicle, which comprises a surveying and mapping unmanned aerial vehicle main body arranged in a flat shape, four hollow shafts, four windproof cylinders, four driving parts, four supporting legs, two reset assemblies, a guide assembly, a folding and unfolding control assembly and a mounting box, the four hollow shafts are fixedly mounted on the surveying and mapping unmanned aerial vehicle body, the four windproof cylinders are radially and rotatably mounted at the ends, away from the surveying and mapping unmanned aerial vehicle body, of the corresponding hollow shafts, the four driving parts are arranged in the corresponding hollow shafts and the windproof cylinders, and the mounting box is fixedly mounted in the middle of a shell of the surveying and mapping unmanned aerial vehicle body. The wind-resistant unmanned aerial vehicle is reasonable in design and good in wind-resistant performance, meanwhile, the flying speed can be greatly increased, the supporting legs can be conveniently folded and unfolded, effective protection can be provided for the paddles, and certain buffering can be provided during landing.

The invention provides an unmanned aerial vehicle collision system and a collision control method. The collision system comprises a mobile computer, a data chain ground terminal, a remote controller and an unmanned aerial vehicle flight device, the mobile computer is configured to display the unmanned aerial vehicle situation and the photoelectric image, and is used for sending an instruction to the unmanned aerial vehicle flight device; the remote controller is configured to perform flight remote control on the unmanned aerial vehicle flight device; an airborne computer on the unmanned aerial vehicle flight device is configured to operate a combined navigation algorithm, give position, attitude and course information of the unmanned aerial vehicle flight device, and realize navigation, guidance and control of the unmanned aerial vehicle flight device; a photoelectric module on the unmanned aerial vehicle flight device is configured to detect and identify a target in real time; the mobile computer communicates with the unmanned aerial vehicle flight device to realize information interaction; according to the scheme provided by the invention, the flight device of the unmanned aerial vehicle can be controlled, the target is collided through remote control, the collision response speed is increased, and the collision cost is reduced.

The present invention relates to the field of air pollution monitoring technology, and the present invention discloses a high-altitude particle pollutant detection sampling device, which includes a fuselage shell, a hanging bracket, an air intake assembly and a sampling assembly, wherein the fuselage shell is cylindrical, an air intake assembly is arranged at one end, a sampling assembly is arranged at the other end, a flow measurement assembly is arranged inside the fuselage shell, a hanging bracket is arranged at the top, and the top of the hanging bracket is connected to the belly or wing of the high-altitude aircraft. The advantages of the present invention compared with the prior art are: it can separate the pollutants to be detected from the high-altitude gas through a comprehensive sampling method and bring them back to the ground, without the need for a large-capacity gas sampling container, and can be adapted to most fixed-wing high-altitude aircraft. Fixed-wing high-altitude aircraft have a faster flight speed, which can improve the sampling and collection efficiency of pollutants, and adopt a comprehensive sampling method for sample collection, which is convenient for subsequent sample processing and analysis.

This invention provides an adaptive sampling flight control method and system for pollutants from unmanned aerial vehicles (UAVs), relating to the field of UAV technology. The method includes the following steps: constructing a three-level heterogeneous grid system and establishing the correlation between grids through cross-level data topology mapping; collecting pollutant concentration data and dynamically activating and / or dormant grids of different precision; calculating a three-dimensional concentration gradient vector using a multi-mode gradient reconstruction mechanism, and combining gradient direction identification and dynamic altitude adjustment strategies to trace the core area of ​​pollutants or track the diffusion boundary of pollutants; selecting different interpolation algorithms according to the system load state and generating a pollution concentration field isosurface model based on the moving cube algorithm; constructing a weighted cost map, integrating real-time concentration change information and historical sampling data to generate a spatially weighted cost value, and dividing different priority areas; implementing hierarchical trajectory planning according to the cost value distribution, and configuring differentiated sampling density and flight speed in different priority areas.

The utility model discloses a coaxial high-speed unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. The coaxial high-speed unmanned aerial vehicle comprises a cylindrical fuselage, a battery main body and a motor main body driven by the battery main body are arranged in the cylindrical fuselage, a motor rotating ring is arranged at the output end of the motor main body, a paddle main body is arranged on the motor rotating ring, a microcomputer is arranged at the bottom of the cylindrical fuselage, and a navigation camera and a GPS navigator are arranged on the microcomputer. According to the coaxial high-speed unmanned aerial vehicle, on one hand, the unmanned aerial vehicle is small in size, easy to carry and convenient to throw in a large number, on the other hand, when the unmanned aerial vehicle is thrown, the cylindrical fuselage and the gravity center are designed at the bottom, the posture is conveniently and rapidly adjusted through gravity, and the stability augmentation function of the unmanned aerial vehicle is achieved in cooperation with the design of the motor body, the motor rotating ring and the paddle body; in cooperation with a microcomputer, a navigation camera and a GPS navigation design, a 2.4 G frequency band image transmission and data transmission system communicates with an operation end, and the unmanned aerial vehicle flies towards a target rapidly.

The utility model relates to the technical field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle high-definition video transmission device, which comprises a vehicle body integrally designed in a cuboid shape; the telescopic wings are respectively arranged at four corners of the aircraft body; the high-definition camera is fixedly arranged at the lower end of the machine body through a multidirectional clamping mechanism, the multidirectional clamping mechanism comprises side wing clamping plates, the side wing clamping plates are symmetrically and movably arranged at the lower end of the machine body through a distance adjusting mechanism, every two side wing clamping plates are arranged in a rectangular mode, and sliding blocks are fixedly installed on the side walls of the side wing clamping plates; according to the device, a ratchet locking mechanism of the side wing clamping plate and the distance adjusting mechanism eliminates transverse displacement and prevents a camera from shaking, elastic lifting of the L-shaped clamping plate is matched with a damper of the damping mechanism, more than 85% of vertical impact energy is absorbed, it is ensured that images do not shake, the image quality of high-definition video transmission equipment is clear, and the service life of the high-definition video transmission equipment is prolonged. The utility model has the characteristics of strong practicability and fast adaptation capability.

This invention provides a tube-launched rotor-wing loitering munition and its operating method, comprising a first-stage propulsion device, a deceleration parachute, a second-stage propulsion device, a multi-rotor UAV, a warhead, and a seeker. The beneficial effects of this invention are: The first-stage propulsion device provides initial velocity during launch, enabling rapid deployment. During flight, the first-stage propulsion device can be automatically jettisoned via a mechanism, reducing the weight of the loitering munition and increasing its operational time. The invention also includes a second-stage propulsion device, which further increases the flight speed of the loitering munition, extending its range and compensating for its insufficient operational distance, ensuring the munition quickly reaches a preset altitude and position. For launch-type rotor-wing loitering munitions, by rationally designing the main body structure and the arm extension and retraction structure, the retraction size is significantly reduced, meeting overload requirements and enabling tube-launching of the rotor-wing loitering munition.

The present invention discloses a hybrid wing layout aircraft, belonging to the field of aviation equipment technology, which includes: a fuselage, wings, control surfaces, and a power unit for providing flight power and control, characterized in that: the power unit includes a left tilting power mechanism arranged on the left side of the fuselage, a right tilting power mechanism symmetrically arranged on the right side, and an adjustment mechanism that enables the two tilting power mechanisms to tilt synchronously, the left tilting power mechanism and the right tilting power mechanism are used to provide power and flight control during vertical flight and horizontal flight, the adjustment mechanism is used for the conversion of vertical flight and horizontal flight modes, and the control surface is used for roll and pitch control during horizontal flight. The aircraft layout mode of the present invention, as well as the setting of synchronous tilting and left and right tilting power mechanisms, successfully solve the problem that the rotor wing of the hybrid layout aircraft is difficult to control under aerodynamic interference.

The utility model discloses a flapping wing type bionic aircraft, which relates to the technical field of aircrafts and comprises a mounting rack, a flapping wing driving mechanism is fixedly mounted in the mounting rack, the output end of the flapping wing driving mechanism is fixedly connected with wings, a pitching mechanism is movably mounted at the bottom of the mounting rack, and the pitching mechanism is fixedly connected with the flapping wing driving mechanism. The output end of the pitching mechanism is movably provided with a deflection mechanism, the bottom of the deflection mechanism is provided with a flapping wing adjusting mechanism, and the output end of the flapping wing adjusting mechanism is fixedly connected with the bottom of the wing. The flight stability and accuracy of the aircraft are improved, the flight speed of the aircraft is also improved, in addition, the flapping wing driving mechanism is simple in structure and light in weight, the requirement of the flapping wing driving mechanism for the light weight can be met, and the endurance time of the aircraft is prolonged.

The utility model discloses a kind of unmanned aerial vehicle for realizing vertical take-off and attitude control using small turbojet engine, small turbojet engine is installed at wing tip of wing, small turbojet engine is installed at the back of fuselage (or in front of fuselage) two sides;Small turbojet engine is made to produce upward thrust by vertical rotation 90 ° using turbine worm drive mechanism or motor with self-locking holding torque, and unmanned aerial vehicle vertical take-off is realized;Unmanned aerial vehicle has aileron installed at the trailing edge of left and right wing tips, and the differential deflection of aileron makes unmanned aerial vehicle tilt rotation around longitudinal axis, and the direction of thrust of small turbojet engine is deflected using turbine worm drive mechanism, to realize the flight state stabilization and flight attitude control of unmanned aerial vehicle, so that unmanned aerial vehicle has good maneuverability;Horizontal stabilizer and elevator are omitted, vertical stabilizer and rudder are omitted, so as to reduce flight resistance, which is conducive to improving the flight speed and effective load of unmanned aerial vehicle.

The utility model discloses a portable unmanned aerial vehicle mounting structure which comprises a machine head body and a machine body, the machine head body is detachably connected with the machine body, a bullet head cavity is formed in the machine head body, a bullet body cavity is formed in the machine body, and a bullet head is arranged in the bullet body cavity. The bullet head cavity and the bullet body cavity are communicated to form a cavity used for containing a guided missile. The device has the effect of reducing wind resistance.

The utility model discloses an unmanned plane wing, including wing and power mechanism, and power mechanism includes base, controller, motor seat, motor, propeller and fairing, and the base is connected with the wing, is equipped with the accommodation groove on the base, and the controller is embedded on the accommodation groove, and the base is connected with the motor seat, and the motor is connected on the motor seat, and the motor is electrically connected with the controller, and the propeller includes base, blade and link cover, and the base is connected with the link cover, and surrounds multiple accommodation cavities with the link cover together, and the blade is multiple, and multiple blades are embedded on multiple accommodation cavities one -to -one, and the base is connected with the motor, and the fairing is equipped with multiple notches, and the fairing is fixedly connected with the base, and multiple blades pass through multiple notches one -to -one. The utility model discloses through setting power mechanism on the wing, can effectively reduce the difficulty of the unmanned plane of using the utility model to rise, and improve flight speed, can better match the navigation use of long range or the unmanned plane of the volume of bigger.

The invention relates to the technical field of aircrafts, in particular to a low-speed take-off and landing fixed-wing aircraft which comprises a fuselage (1), a flight control system (2), an aero-engine (3), a jet engine tail nozzle (4), wings (5), aircraft energy (6) and an empennage (7). The low-speed take-off and landing fixed-wing aircraft can take off and land at a low speed, accidents are reduced, control is easier, and flight safety is improved; the unmanned aerial vehicle can take off and land on a shorter runway or space, and the requirement for a take-off and landing site is low; the control difficulty is lowered, the requirement for a driver is lowered, and popularization is facilitated; the flying speed is high, low-speed flying can also be achieved, and the requirements of various tasks are met.

The invention discloses a pressure smooth opening electromagnetic device of a multi-oil-way and multi-electricity aero-engine fuel system, which is used for realizing stable switching among multiple oil ways in the fuel system and accurate pressure control and effectively reducing electromagnetic force requirements. The device comprises a valve body base, a main valve assembly, an auxiliary valve assembly and an electromagnetic actuation pilot valve assembly, a main valve is of a conical surface structure, it is ensured that good sealing is formed between the main valve and a valve port, smooth flowing of fluid is achieved through a small runner hole, meanwhile, the structure of the main valve is optimally designed in combination with related fluid mechanics theories, and the valve body structure is optimized. And when the main valve actuates, the electromagnetic force demand is effectively reduced. In addition, the auxiliary valve is designed to be a one-way valve, the unidirectionality of fuel oil flowing and the stability of system pressure during multi-oil-way switching are guaranteed, and the reliability of the system is improved. According to the device, through cooperative work of all the assemblies, stable switching among multiple oil ways and accurate pressure control are achieved, and the stability and reliability of an aero-engine multi-oil-way fuel system are remarkably improved.

The utility model discloses a spacecraft with a solar sail pushing function, which belongs to the technical field of spacecrafts and comprises a bottom plate, an abutting plate is connected to the top of the bottom plate, a supporting rod is connected to the top of the abutting plate, an adjusting device is arranged at the top end of the supporting rod, and a workbench is mounted at the top of the adjusting device. An unfolding mechanism is arranged at the top of the workbench, a plurality of solar sail bodies are mounted at the top of the workbench through the unfolding mechanism, a mounting seat is mounted at the top of the unfolding mechanism, and self-cleaning assemblies are arranged on the two sides of the bottom of the mounting seat; according to the solar sail, the unfolding mechanism and the adjusting device are arranged, and the designed rotating rod, the movable rod and the driving motor are used in cooperation, so that unfolding and folding work of the solar sail body is achieved, the light inlet amount of the solar sail body is increased, the angle between the solar sail body and sunlight is changed by adjusting the angle of the solar sail body, and therefore the light pressure is changed; the flight speed of the spacecraft and the working efficiency are improved.