414results about How to "Flying fast" patented technology

The invention discloses an anti-collision fixed-point unmanned aerial vehicle for fire control, and belongs to the field of unmanned aerial vehicles. The anti-collision fixed-point unmanned aerial vehicle for fire control comprises an unmanned aerial vehicle body, a bomb-dropping gun and an anti-collision cover, wherein the bomb-dropping gun is arranged below the unmanned aerial vehicle body; a steering engine is mounted on the bomb-dropping gun and is used for controlling the bomb-dropping gun to launch a fire extinguishing bomb; a collimation mechanism is mounted on the parallelly arranged bomb-dropping gun, so that the bomb-dropping accuracy is improved; the anti-collision cover adopts a cage-shaped structure; the cage-shaped structure encircles the periphery of the unmanned aerial vehicle body to protect the unmanned aerial vehicle body from being collided; a waterproof cover is also arranged on a spiral paddle support to prevent the spraying of flames. According to the anti-collision fixed-point unmanned aerial vehicle, fixed-point fire extinguishment on high-rise buildings and narrow channels is carried out without geographical environment limitation, and the unmanned aerial vehicle is unlikely to collide and damage, high in flying speed, sensitive in actions and wide in application range.

The invention provides a fixed-wing multi-shaft aircraft, and belongs to the field of aircrafts. The fixed-wing multi-shaft aircraft comprises a fixed wing and a multi-shaft rotor wing rack which are connected with each other, and the multi-shaft rotor wing rack is provided with multiple rotor wing mechanisms; the rotor wing mechanisms comprise propellers and rotating shafts, the propellers are rotatably connected with drive devices, the drive devices are fixedly connected with the rotating shafts, and the rotating shafts are connected with rotating control mechanisms. The fixed-wing multi-shaft aircraft has the advantages of both a fixed-wing aircraft and a multi-shaft aircraft, can achieve a multi-shaft mode, a fixed-wing mode and a fixed-wing and multi-shaft mixed mode and also has the advantages of achieving vertical taking-off and landing and hovering and being high in flying speed and long in flying time.

The invention provides a rotated quadrotor, and belongs to the technical field of aircraft design. The rotated quadrotor comprises flying rotor wings, brushless direct current motors, a fuselage, a canopy, undercarriages, a power supply unit, a flight control system, fixing tubes, a rotated rocker arm, a connecting rod, a rotated steering engine, rotor wing arms, and round heads. According to the rotated quadrotor, rotating angles of the four flying rotor wings in the front-back direction are controlled to as to realize forward flying or backward flying; installation angles of the flying rotor wings are changed so as to realize forward flying of the four flying rotor wings, maintain level condition of the fuselage, ensure that the best aerodynamic performance of the quadrotor is maintained all the time, and the maximum lifting force of the fuselage is induced, increase flying speed of the quadrotor, prolong flight duration, and improve wind resistance, operation capability, and efficiency.

The invention provides a multi-rotor unmanned airplane with inclined wings and rotors. The structure of the unmanned airplane comprises a plurality of rotors, a pair of wings and two rotors, wherein the plurality of rotors are arranged on a connecting rod, the wings are symmetrically arranged on the left and right sides of a fuselage and can be inclined between the directions perpendicular to the fuselage and parallel to the fuselage, and the two rotors are installed on the wings and can be synchronously inclined with the wings. The invention further provides a control system and a control method of the multi-rotor unmanned airplane with the inclined wings and the rotors. The attitude of the unmanned airplane provided by the invention is fully completed by a rotor system which is symmetrically arranged on the connecting rod, the rotors arranged on the wings only provide thrust, the attitude is not influenced, thereby decoupling the attitude control and the speed control, the complexity and the control difficulty of a dynamic model are reduced, additional lifting force is provided by utilizing an aerodynamic effect of the wings, and the flight speed, the bearing capacity and the endurance efficiency of the multi-rotor unmanned airplane are improved.

The invention discloses a driving mechanism of a hybrid power helicopter. The driving mechanism of the hybrid power helicopter comprises a fuel tank, an engine, a clutch, a first locker, a planetary gear mechanism, an energy storage device, a generator / electric motor, a second locker, a second generator / electric motor, a torque coupler, a tail end gear box, a tail rotor subsystem, an swashplate and a rotor wing subsystem, wherein the clutch and the first locker are mounted between the engine and the planetary gear mechanism, and the second locker is mounted between the generator / electric motor and the planetary gear mechanism. Two power sources comprising a basic power source and an auxiliary power source are utilized, the two power sources are reasonably matched and selected when driving the helicopter, accordingly, the problems that the power source of a conventional helicopter is single, a drive system is complicated, a drive device is heavy, mechanical failure easily happens and the like are solved, and the safety and the maneuverability of the helicopter are improved.

The invention discloses a cruise aircraft, the cruise aircraft is variable in type, can be a four-propeller aircraft capable of vertical take-off and landing, vertical hover and flexible flight, also can be deformed as a fixed wing cruise aircraft capable of long-distance raid, and can transform between the four-propeller aircraft and the fixed wing cruise aircraft according to the needs; during take-off and landing or in narrow space condition, wing tips folds downward, and can play the role of a landing gear or achieve the purpose of reducing the dimension of the cruise aircraft; while in cruise flight, 2 engines can turn 90 degrees, the other two engines shutdown, at the same time, the wing tips can be expanded, the cruise aircraft transforms as a delta wing layout fixed wing cruise aircraft with a high flight speed and a larger flight radius; when the cruise aircraft is in a fixed wing form flight, only 2 blade propellers are used for driving, energy is saved, and the flight radius is larger.

The invention discloses an environment detecting method based on an unmanned aerial vehicle. When the unmanned aerial vehicle receives an environment detecting instruction, the unmanned aerial vehicle flies to a to-be-detected position; the unmanned aerial vehicle acquires the environment information of the to-be-detected position and sends the information to a server; and the server analyzes the environment information according to a preset algorithm. the invention also discloses an environment detecting system based on the unmanned aerial vehicle. Thus, high-efficiency environment detection is realized, and the purpose of assisting decision making is achieved.

The invention discloses a culvert-type vertical take-off and landing lifting body unmanned aerial vehicle and relates to the technical field of vertical take-off and landing unmanned aerial vehicles.The culvert-type vertical take-off and landing lifting body unmanned aerial vehicle comprises a fuselage (1), lifting force rotor wings (2), a take-off and landing culvert (3), tilting-rotating thrustculverts (7) and tilting-rotating thrust rotor wings (8). The take-off and landing culvert (3) is composed of a through hole penetrating through the upper surface and the lower surface of the fuselage (1), and the lifting force rotor wings (2) are arranged in the take-off and landing culvert (3). The tilting-rotating thrust culverts (7) are hinged to the rear end of the fuselage (1) through tilting-rotating control mechanisms (9), the tilting-rotating control mechanisms (9) are configured to be capable of enabling the included angle between the axis of each tilting-rotating thrust culvert (7)and the axis of the fuselage (1) to be variable, and the tilting-rotating thrust rotor wings (8) are arranged in the tilting-rotating thrust culverts (7). Under the conditions that the vertical take-off and landing capacity of the unmanned aerial vehicle is maintained and the overall weight of the unmanned aerial vehicle is not excessively increased, the flight speed of the unmanned aerial vehicle is increased, the flight stability of the unmanned aerial vehicle is improved, the rotor wing exposed problem is avoided through the culverts, and the flight safety and the take-off and landing hovering efficiency are improved.

An airplane able to change the shape of wing is composed of an airplane body and two wings consisting of fixed wing with one end fixed to airplane body, slide wing installed in the skeleton of said fixed wing and with a roller moving in a spiral slot on a cylindrical body, and the cylindrical body and shape memory alloy bar, which are fixed to each other and installed in the skeleton of said fixed wing. Said shape memory alloy bar is used as the drive source for changing wing shape.

The invention relates to aircraft wings, in particular to deformable wings and a vertical take-off and landing aircraft using the wings. The technical problems that the wingspan area of a vertical take-off and landing aircraft is large at present, and the vertical take-off and landing aircraft is prone to being affected by wind power in the state of vertical take-off and landing so that the posture is unstable are solved. The deformable wings serve as an integrated airframe of the vertical take-off and landing aircraft. Each deformable wing comprises a wing leading edge and a wing trailing edge. Spreading and contracting between each wing leading edge and the corresponding wing trailing edge are achieved through a sliding assembly. A folding skin is connected between each wing leading edge and the corresponding wing trailing edge. According to the designed deformable wings, the size of the chord length can be expanded, contracted and changed, and the wing area is changed; meanwhile, the advantages of a fixed wing aircraft and the advantages of a multi-rotor-wing aircraft are combined, so that the function that the same aircraft can fly by arbitrarily switching two flight modes is achieved.

The invention provides a multifunctional unmanned plane launch and recovery vehicle which consists of a carrier, a lifting bracket, a gaseous catapult, recovery devices and an unmanned plane transfer box. The bottom of the lifting bracket is connected with the carrier, the gaseous catapult is arranged at the top part of the middle of the lifting bracket through a hinge, the recovery devices are arranged at the two sides of the lifting bracket, and the unmanned plane transfer box is arranged in the middle part of an upper bracket of the carrier. The recovery vehicle successfully solves launch and recovery difficulties which cannot be solved by an unmanned plane. The multifunctional unmanned plane launch and recovery vehicle has the following advantages that: (1) launch, recovery, storage and carrying in vehicle are integrated together, continuous launch and recovery of multiple planes can be achieved, no damage of planes is caused during transport in marching, planes can be launched and recovered at any time, the multifunctional unmanned plane launch and recovery vehicle can be suitable for bad field environment and can be free of ground environment influence; and (2) the flying resistance is low as the unmanned plane has no undercarriage, the unmanned plane does not need to carry a parachute and an anti-drop air sac, the characteristics of large fuel capacity, long cruising time, wide application scope and the like are realized, and good popularization and application values are achieved.

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 invention discloses a tail-sitter four-rotor canard aircraft capable of vertically taking off and landing. The tail-sitter four-rotor canard aircraft capable of vertically taking off and landing comprises an aircraft body, wings, canards, vertical tails and power devices; a pair of canards is mounted at the head part of the aircraft body; the wings are on two sides of the tail part of the aircraft body; the vertical tails are respectively arranged above and under the tail part of the aircraft body; the power devices are respectively arranged at the tip parts of the wings and the tip parts of the vertical tails; the power devices are variable pitch propellers; and rotating shafts of the power devices are parallel to the axis of the aircraft body. The tips of the wings, the tips of the vertical tails and the tail end of the aircraft body of the four-rotor canard aircraft mutually form five supporting points; and in a stopping state, the five supporting points enable the aircraft to vertically land on the ground upward. The tail-sitter four-rotor canard aircraft capable of vertically taking off and landing has the advantages of rapid vertical takeoff and landing response speed as well as good controllabitity, stability and wind-resistant performance during vertical takeoff and landing. By using canard configuration, the tail-sitter four-rotor canard aircraft capable of vertically taking off and landing can horizontally fly for a long time at a high speed in the form of a fixed wing and can realize good controllabitity and maneuverability.

The invention provides an unmanned aerial vehicle monitoring system for monitoring floating objects in water. The system comprises a UAV (unmanned aerial vehicle) cruise module and a ground monitoring processing module. By using the UAV cruise module to carry out monitoring, most water areas can be reached, the implementation difficulty of monitoring is small, a UAV does not carry monitoring personnel, the UAV cruise module reaches an observation point in the air, the disadvantages of power safety reliability and the interference of water area velocity and water flow direction by using an observation ship are overcome, the possibility of accidents is little, the reliability and safety of monitoring are improved, the floating objects in a large water area can be monitored in a short time, the monitoring efficiency is improved, a lot of manpower and resources are saved, the energy consumption of monitoring personnel is reduced, a monitoring area and a water area floating object area can be accurately calculated, the density of the water area floating objects is accurately calculated, and the analysis decision and further measures are facilitated according to provided detailed monitoring data.

A system and method for efficiently maneuvering a multirotor drone having a control system, an electrical power source, a plurality of rotor assemblies each having a rotor boom, a rotor mast, at least one rotor blade, a rotor assembly adjustment apparatus, a plurality of electric motors, wherein each electric motor is connected to a rotor boom positioned in a substantially horizontal direction and drives a rotor mast positioned in a substantially vertical direction and connected to at least one rotor blade, with the position of said rotor boom automatically adjustable in a substantially horizontal direction by the adjustment apparatus and the control system.

The invention discloses a helicopter taking off and landing vertically and flying horizontally and application thereof. The helicopter comprises a fuselage, rotor mechanisms, wing mechanisms, an undercarriage device, a power mechanism, a control mechanism and a transmission mechanism. The fuselage comprises a nose, a fuselage middle part and a tail. The rotor mechanisms comprise double rotating rotor mechanisms. Rotary double-rotor mechanisms are longitudinally arranged on the fuselage. The multiple wing mechanisms are perpendicularly arranged on the two sides of the fuselage middle part. As both the double rotating rotor mechanisms and the rotary double-rotor mechanisms are designed, both vertical taking-off and landing and rapid horizontal flying are achieved; as the rotor mechanisms are installed on the nose and the tail of the fuselage of the helicopter respectively and can rotate front and back around the center axis of the fuselage, the range of the helicopter is 5-6 times larger than that of an existing helicopter, flight safety is ensured, production and operation cost is reduced, the design can be applied to various aircrafts, and the significant technical effects of a large range, a high flight speed, a high safety coefficient and control easiness of the helicopter can be achieved.

The invention relates to a bird impact test device and method, belongs to the field of bird impact test, and mainly aims at improving the birdshot emission speed via the bird impact test device. The bird impact test device comprises a pressure release mechanism with an air outlet end, a gun barrel which is internally provided with a birdshot installation portion and a cartridge brake unit with a fixed flange; the gun barrel includes a first end and a second end opposite to the first end, the first end is connected with the air outlet end, and the second end is connected with the fixed flange; the bird impact test device further comprises a first sealing device and a second sealing device, the first sealing device comprises a first sealing film, and the first sealing film is clamped between the first end and the air outlet end; the second sealing device comprises a second sealing film, and the second sealing film is clamped between the second end and the fixed flange; and the gun barrel is provided with a pressure reduction port between the first end and the second end, and the pressure reduction port is connected with a pressure reduction device to reduce the internal pressure of the gun barrel.

The invention relates to the technical field of an unmanned aerial vehicle and especially relates to a flying system for the unmanned aerial vehicle. The flying system for the unmanned aerial vehicle comprises a fixed wing flying device, a rotor wing flying device and a control system, wherein the rotating direction of the rotor wing flying device is changeable; the control system is respectively connected with the fixed wing flying device and the rotor wing flying device; the control system can control the on and off of the fixed wing flying device and the rotor wing flying device with changeable rotating direction according to the flying and landing conditions. The flying system is formed by combining the fixed wing flying device with the rotor wing flying device with changeable rotating direction, so that the flying system has the advantages of the fixed wing flying device and the rotor wing flying device, the rotor wing flying device can supply the power for the unmanned aerial vehicle to ascend and land as well as the power for the unmanned aerial vehicle to fly, the ascending and landing are convenient, the duration of flight is long and the flying speed is high.

The invention discloses an integrated general-purpose vertical take-off and landing aircraft based on lifting and floating force. A center fuselage is positioned in the middle of the front edge of a rear tandem wing; a left fuselage and a right fuselage are respectively positioned at wingtips at two ends of the tandem wing, and stretch out forwards; two engines are respectively mounted on the inner side of the left fuselage and the inner side of the right fuselage; tail booms which extend backwards are respectively arranged at the rear end of the left fuselage and the rear end of the right fuselage, and each tail boom and the longitudinal axis of a fuselage form an included angle of 15 degrees. According to the aircraft, a twin-vertical tail layout is adopted; an elevating rudder and steering rudders are respectively arranged on a horizontal tail and vertical tails; each undercarriage is in a front three-point manner; main undercarriages are respectively positioned at the lower part of the left fuselage and the lower part of the right fuselage; the front undercarriage is positioned at the front part of the center fuselage. The aircraft disclosed by the invention has the characteristics of extensive range of application, wide flying regions and high working efficiency; the aircraft is suitable for the fields of transportation, land surveying, resource exploration, environmental monitoring, scientific experiments, aviation trainings, safety patrolling, personnel rescue, express delivery, prevention and treatment for agriculture and forestry, culture and sports, administrative affairs, and tour and sightseeing.

The present invention provides a horizontal rear wing structure of a remote controlled flight assuring fast and stable turning. The horizontal rear wing structure 1000 includes a servomotor facing the upper side of the flight body D, a rotating member 220 mounted on the servomotor and a connecting part 300 mounted on the top side of the rotating member, the connecting part being combined with the horizontal rear wing. Accordingly, the horizontal rear wing 400 rotates with respect to the plane of the flight body.

The invention discloses a combined coaxial unmanned helicopter. The combined coaxial unmanned helicopter is provided with a helicopter shell, a helicopter body supporting structure, an engine, an oil tank, a helicopter main rotor, a helicopter main speed reducer, wings and a tail wing and further comprises a power distribution and clutch system and a propelling propeller. The propelling propeller is mounted on the rear portion of a helicopter body. The combined coaxial unmanned helicopter can fly at different flight stages according to different flight speeds, power of the engine is distributed to the main rotor and the propelling propeller through the power distribution and clutch system, and vertical take-off and landing, hovering, low-speed forward flying, medium-speed flying and high-speed flying are achieved. The combined coaxial unmanned helicopter has the advantages that compared with a conventional helicopter, the flying speed can be remarkably increased; one set of engine is used for supplying power to two sets of flying systems, and the weight is low; the two coaxial rotor wings are adopted, airflow is symmetrical, the pneumatic effect is good, the structure is compact, the size is small, the self-rotation mode is achieved at the high speed, and resistance force is smaller.

The invention discloses a fixed wing aircraft provided with multiple rotor wings and capable of realizing vertical take-off and landing. The fixed wing aircraft comprises a fuselage, aircraft wings and a tail wing, as well as power rack units arranged on the aircraft wings and the tail wing, wherein the power rack units comprise front rotor wings, rear rotor wings and tail rotor wings. According to the invention, the switching between the helicopter mode take-off and landing and fixed wing flight mode can be realized, the safety performance of the take-off and landing of the aircraft is improved, and the take-off and landing mode of the traditional fixed wing aircraft is changed.

The invention relates to a wing of an aircraft, in particular to a wing deformation structure of a water and air amphibious aircraft, aiming at solving the problems that the wing, adopting a vertical fin discontinuous deformation structure, of the existing antisubmarine aircraft is poor in stealth performance and aerodynamic performance, has influence on the flight speed and is not beneficial to reduction of radar return signals, and the wing, adopting a structure without a vertical fin, of the existing antisubmarine aircraft is poor in controllability and maneuvering characteristic. The wing deformation structure of the water and air amphibious aircraft comprises a rigidity-variable wing spar, two bending torsion deformation components and two wing ribs; two pneumatic muscle actuators of each bending torsion deformation component are arranged crosswise; the two bending torsion deformation components are respectively arranged at two sides of the rigidity-variable wing spar; two ends of each pneumatic muscle actuator are respectively connected with the two wing ribs; the rigidity-variable wing spar comprises a flexible bearing pneumatic muscle actuator and a wing spar main body; the flexible bearing pneumatic muscle actuator is inserted into a tubular elastic beam; two ends of the tubular elastic beam are respectively connected with the two wing ribs. The wing deformation structure is used for the water and air amphibious aircraft.

The invention discloses a telescopic wing which consists of a wing I (7), a wing II (8), a wing III (9), a pulley I (2), a pulley II (11), a steel rope I (3), a steel rope II (10), a hydraulic rod seat (4), a hydraulic rod (5) and a hydraulic cylinder (6). The action of the wing is to generate lifting force so as to support airborne flight of an aircraft; the lifting force generated by the same wing is in a close relationship with the speed and height of the aircraft; for the same wing, when the height is the same, the higher the speed of the aircraft is, the higher the lifting force is; when the speed is the same, the larger the height is, the lower the lifting force is. According to the telescopic wing, when the aircraft carries out a cruising flight at a high altitude with thin air, the wing completely stretches out, only low fuel consumption is needed by the aircraft due to the ultra-wide wing, a low navigational speed is maintained, and the aim of prolonging the hang time can be achieved; moreover, the wing is completely shortened during sailing or course reversal, so that the flight speed is improved, and the sailing or course reversal time is shortened.

An STOL (short take off and landing) unmanned aerial vehicle with an unpowered-driven rotor wing comprises an aerial vehicle body, wings, a horizontal tail, vertical fins, an engine, a propeller, a rotor wing, a rotor wing prerotation device, undercarriages and a propeller hub, wherein the propeller is used for providing a thrust for flying forwards. When the unmanned aerial vehicle flies, airstream passes through a rotor wing disc from bottom to top to drive the rotor swing to rotate freely so as to generate a lift force; meanwhile, the rotor wing prerotation device is used for prerotating the rotor wing before takeoff; therefore, the short take off, even jumping take off, of the unmanned aerial vehicle can be realized. The STOL unmanned aerial vehicle with an unpowered-driven rotor wing has the advantages of high safety, low cost in the full service life, good flying performance and the like and has a bright application prospect.

The invention relates to a device and method used for offshore fertilization and pesticide application through an unmanned ship and a drone, and relates to the field of cultivation in water areas through assistance of an unmanned ship. The device consists of a cultivation carrier, an unmanned ship and a drone. A material filling device and a drone recycling device are arranged on an unmanned ship body. Through the cultivation carrier, materials are applied to a cultivation region, the drone detects condition information of the cultivation carrier and the unmanned ship helps the drone to supply materials for the cultivation carrier. Thus, improvement of efficiency for applying materials to the cultivation region is achieved; by applying the unmanned ship technology to the offshore cultivation industry, risks in offshore operation of fishermen are reduced; and efficiency of offshore operation is improved.

The invention discloses an UAV (unmanned aerial vehicle) which comprises a main body, a stretching unit, a driving unit and a steering unit, wherein the main body comprises a vehicle body, a support plate located below the vehicle body and wheels located below the support plate; the stretching unit comprises side wings hinged to two sides of the main body and a stretching motor for driving the side wings to rotate; the driving unit comprises a plurality of rotors fixed on the vehicle body, a plurality of first driving motors for driving the rotors to rotate respectively and a plurality of second driving motors for driving the rotors to rotate in different directions; the steering unit comprises an air deflector fixed at the end part of the vehicle body and a rotating motor for driving the air deflector to rotate. The UAV can hover vertically as well as take off and land vertically like a helicopter or a four-propeller aircraft and has super-high maneuverability.

The invention relates to manufacture of airplanes and flying use, taking off and landing modes of the airplanes. Excellent performance of a modern jet plane capable of flying supersonically and convenient taking off and landing of a helicopter are perfectly integrated on a jet helicopter. Wings and a motor of the jet helicopter are movably arranged and can be rotatably adjusted, a hydraulic control unit rotates the wings (3) and the motor (2) simultaneously when the airplane takes off or lands; and the change of the jet direction of the motor can change the taking off and landing mode of the airplane. Another mode is to arrange the motor on an airplane body and operate, control and rotate the motor by a hydraulic unit. Both modes can make the airplane take off and land vertically. The technique applied can design and produce various jet helicopters to serve national defense and human society.

The invention discloses a tail-sitter type three-rotor canard aircraft capable of vertically taking off and landing. The tail-sitter type three-rotor canard aircraft capable of vertically taking off and landing comprises an aircraft body, wings, a canard wing, a vertical tail and power devices; the canard wing is mounted at the head part of the aircraft body; the wings are positioned on two sides of the tail part of the aircraft body; the vertical tail is arranged under the tail part of the aircraft body; the power devices are respectively arranged at the wing tip parts of the wings and the wing tip part of the vertical tail; and the power devices are variable pitch propellers. Elevons are mounted at the rear edges of the wings; a rudder is mounted at the rear edge of the vertical tail; and an elevating rudder is mounted at the rear edge of the canard wing. The wing tips of the wings, the wing tip of the vertical tail and the tail end of the aircraft body of the tail-sitter type three-rotor canard aircraft capable of vertically taking off and landing mutually form four supporting points; in a stopping state, the four supporting points enable the aircraft to vertically land on the ground upwards; the vertical takeoff and landing response speed of the aircraft is high and the aircraft has good stability during vertically taking off and landing. Through adoption of canard configuraiton, the tail-sitter type three-rotor canard aircraft capable of vertically taking off and landing can horizontally fly at a high speed in the form of a fixed wing and has the advantages of long flying time, good controllability and good motility.