901 results about "Tailplane" patented technology

The invention discloses an unmanned aerial vehicle suitable for microwave reconnaissance interference equipment and an equipment antenna arrangement method, and belongs to the field of unmanned aerial vehicles. The unmanned aerial vehicle comprises a fuselage, wings and an empennage. The fuselage comprises a fuselage head, a fuselage body and a fuselage tail. The wings adopt upper single wings and are mounted at the top of the fuselage; the empennage is installed at the tail of the fuselage. The head of the fuselage adopts a nose cover made of wave-transparent materials, a plurality of forward interference antennas are mounted in the nose cover, lateral interference antennas and reconnaissance antenna arrays are mounted on fuselage skins on two sides of a fuselage main body, a plurality of backward interference antennas are mounted in an engine cover made of wave-transparent materials at the tail of the fuselage, and propellers at the tail end of the unmanned aerial vehicle are made of wave-transparent materials. Through the conformal design of the unmanned aerial vehicle and the antenna, the influence of the antenna on the aerodynamic performance of the unmanned aerial vehicle is reduced to the maximum extent, the aerodynamic layout of the unmanned aerial vehicle is optimized by combining the antenna arrangement, and the task antenna is not shielded.

The invention discloses a bionic robot with walking, jumping and taking-off functions and a movement method, and belongs to the technical field of robots. The robot comprises a control system, a flapping wing mechanism and two leg mechanisms. Each leg mechanism comprises a driving device I, an execution connecting rod mechanism and a buffer foot part, the buffer foot part is connected with the execution connecting rod mechanism, and the execution connecting rod mechanism is driven by the driving device I; the flapping wing mechanism comprises a driving device II, a transmission mechanism, wings and an empennage; the execution link mechanism is connected with the transmission mechanism, the wings and the empennage are respectively connected with the transmission mechanism, the transmission mechanism is driven by the driving device II, the control system is used for controlling the driving device I and the driving device II, and the motion modes comprise walking, jumping and flying. The multi-mode bird-simulating robot has a multi-mode bird-simulating motion function, can autonomously realize mode switching from land motion to air flight, and remarkably improves the motion performance of the robot.

The utility model discloses a cylindrical launch folding wing unmanned aerial vehicle which comprises an unmanned aerial vehicle body, the unmanned aerial vehicle body comprises a square fuselage and a conical nose cover, a concave platform is arranged below the middle rear section of the fuselage, foldable wings are arranged in the concave platform, foldable empennages are arranged on the two side faces, close to the tail, of the fuselage, and the tail of the fuselage is connected with the tail of the fuselage. A foldable propeller is arranged at the tail of the fuselage, two blades of the propeller can be folded and retracted into an upper arc-shaped groove and a lower arc-shaped groove, close to the tail, of the fuselage respectively, a pod, a parachute cabin and a GPS antenna cabin are integrated in the nose cover, and a load cabin, a battery cabin and an equipment cabin are sequentially arranged at the front section, the middle section and the rear section of the fuselage. According to the cylindrical launching folding wing unmanned aerial vehicle, the design of the conical nose cover, the square fuselage, the lower single wing and the V-shaped empennage is adopted, launching is carried out through the square launching cylinder during launching, a plurality of cabin sections are designed in the square fuselage, each cabin section is fully utilized under the condition that the gravity center of the unmanned aerial vehicle is proper, and the assembly efficiency is greatly improved.

The invention belongs to the technical field of airplane structure design, and discloses a horizontal tail wing beam connecting structure, an airplane and an assembling method, and the horizontal tail wing beam connecting structure comprises a central rib plate, an upper T-shaped connector, a lower T-shaped connector, a left connecting plate, a right connecting plate and an outer side connecting plate. The upper T-shaped joint comprises a lower edge strip, a first left edge strip and a first right edge strip, the lower T-shaped joint comprises an upper edge strip, a second left edge strip and a second right edge strip, the central rib plate is arranged between the left beam and the right beam, and the left connecting plate, the right connecting plate and the outer side connecting plate are combined for use, so that the bearing capacity of a left beam web plate and a right beam web plate is improved; the first left edge strip and the first right edge strip can increase the contact area between the upper T-shaped connector and the left wing and the contact area between the upper T-shaped connector and the right wing, the second left edge strip and the second right edge strip can increase the contact area between the lower T-shaped connector and the left wing and the contact area between the lower T-shaped connector and the right wing, the connecting strength of the left beam and the right beam in the vertical direction is improved, and the lower edge strip, the upper edge strip and the central rib plate are matched with one another. And the connection strength of the left beam and the right beam in the horizontal direction is improved.

The invention belongs to the technical field of flight mechanics, and particularly relates to a V-shaped empennage control surface course control extension control method which comprises the steps that a left control surface deflection angle reaches an upper limit, a right control surface deflection angle continues to deflect leftwards, and a right empennage generates right lower lift increment perpendicular to the incoming flow direction; the right empennage can simultaneously generate a vertically downward force and a head-up torque relative to the gravity center of the whole aircraft; a downward head lowering moment is generated through the longitudinal periodic pitch change of the rotor wings and the tilt angle of the rotor wings, so that the pitching moment is balanced; the vertical force balance of the whole aircraft is achieved by adjusting the attack angle of the aircraft body.

The invention belongs to the technical field of aerodynamic wind tunnel tests, and discloses a test device and method for a dynamic derivative wind tunnel test, and the device comprises an aircraft model which is formed by assembling a nose, a middle fuselage, a rear fuselage, a balance, wings and an empennage; the oscillation mechanism is provided with an adapter, and the adapter is connected with the balance; and one end of the wind tunnel strut is connected with the wind tunnel attitude control system and the other end is connected with the oscillation mechanism. The problem that an existing dynamic derivative wind tunnel test model and a test device are low in efficiency is solved, heaving, sidesway, yawing, pitching and rolling oscillation of the model are achieved by replacing the adapters, and the test efficiency of a dynamic derivative wind tunnel test can be effectively improved.

The intelligent bionic ornithopter with the body and the self-adaptive attack angle adjusting joints comprises an ornithopter body, wings and an empennage, the wings and the empennage are arranged on the ornithopter body, driving motors are symmetrically arranged on the flapping portions of the wings, and each driving motor is provided with a limiting joint; the limiting joint comprises an outer ring, an inner ring and an elastic cushion block, the outer ring is composed of a plane end and first protruding parts, the plane end and the driving motor are connected and rotate synchronously, the first protruding parts are located on the two sides of the plane end and provided with penetrating holes, the inner ring is a cylinder, and the inner ring is arranged between the first protruding parts and swings with the middle of the plane end as the center. The inner ring and the penetrating hole are matched and jointly sleeved and fixedly connected with the edge of the wing, a second protruding part is arranged on the inner ring, and elastic cushion blocks are arranged at the upper end and the lower end of the second protruding part. The invention aims to provide the bionic ornithopter which can fully simulate flapping wing flapping actions of flying organisms and can adaptively adjust the attack angle in the flapping process so as to improve the flapping lift force and reduce the resistance.

The invention provides a wing type biological hybrid flapping wing aircraft with deformable wings. The wing type biological hybrid flapping wing aircraft comprises a flapping mechanism, a wing deformation mechanism, bird feather type wings, an aircraft body, an empennage deformation mechanism and a bird feather type empennage, the flapping mechanism and the empennage deformation mechanism are mounted on the fuselage; the flapping mechanism drives the wing deformation mechanism to do wing flapping motion; the bird feather type wings are arranged on the wing deformation mechanism; the empennage deformation mechanism comprises an empennage joint and a plurality of steering engines, the steering engines drive the empennage joint to do four-degree-of-freedom motion, and the bird feather type empennage is installed on the empennage joint. The multi-degree-of-freedom cooperative connecting rod transmission mechanism is adopted, high-fidelity reproduction of bird flapping wing motion is efficiently achieved, and independent and accurate regulation and control of the torsion angle, the torsion rate and the torsion direction of the empennage are achieved based on hierarchical steering engine control and the decoupling characteristic of the double-layer motion frame.

The invention discloses a novel bird-imitating empennage multi-degree-of-freedom platform, and relates to the technical field of flying robots, the novel bird-imitating empennage multi-degree-of-freedom platform comprises a first driving structure, a support, a second driving structure, an empennage driving structure and an empennage assembly, the second driving structure and the empennage driving structure are both arranged on the support, the first driving structure can drive the empennage assembly to rotate in the heading direction, and the second driving structure can drive the empennage assembly to rotate in the pitching direction and the rolling direction. And the empennage driving structure can control the area change of the empennage assembly. According to the novel bird-imitating empennage multi-degree-of-freedom platform, control over the heading direction, the rolling direction and the pitching direction can be achieved, and the area of the empennage assembly can be changed.

The invention relates to a mobile device communication method and device, a mobile device, a readable storage medium and a program product. The mobile device comprises an empennage which is provided with an antenna array and is adjustable in pitching angle; the method comprises the following steps: determining a target pitch angle of an empennage required by the mobile device for satellite communication; according to the moving information of the moving device in the moving process, the acting moment borne by the empennage in the moving process is determined; adjusting the pitch angle of the empennage to a target pitch angle according to the acting moment; and under the condition that the empennage is at the target pitch angle, adjusting the phase difference between communication signals of each antenna unit in the antenna array so as to perform satellite communication for the mobile device through the antenna array. The method can improve the communication efficiency of the mobile device.

The invention discloses a mechanical linkage posture stabilizing pull-type submersible. The pull-type submersible comprises a cabin, an empennage assembly, an inertia assembly and at least one pair of side wings. The side wings are rotatably arranged on the side walls of the cabin body through second rods; the inertia assembly comprises a balance weight part, a main shaft and a gear structure, the balance weight part rotatably sleeves the main shaft, the tail end of the main shaft is connected with the empennage assembly, the gear structure is rotatably arranged on the inner side wall of the cabin body, and the balance weight part is connected with the gear structure; the counter weight part deviates from the central axis of the cabin body, relative rotation between the counter weight part and the cabin body can drive the paired side wings to rotate in the opposite directions through the gear structure, and movement of the counter weight part and the main shaft relative to the cabin body can drive the empennage assembly to be opened and closed. The pull-type submersible is provided with the inertia assembly, the inertia assembly achieves passive posture stabilization of the pull-type submersible through relative movement of the balance weight piece and the cabin body, and the pull-type submersible can be widely applied to the technical field of ocean exploration.

The invention belongs to the field of vertical take-off and landing aircrafts, and relates to a distributed contra-rotating rotor hybrid tilting rotorcraft. Comprising a front tilting electric contra-rotating rotor nacelle, a front cabin body, a wing end tilting electric contra-rotating rotor nacelle, a V-shaped empennage, a V-shaped empennage aileron, a vertical empennage, a retractable undercarriage, a green hybrid power energy system and an empennage tilting electric contra-rotating rotor nacelle, the front tilting electric contra-rotating rotor nacelle is hinged with the other end of the front cabin body; an empennage tilting electric contra-rotating rotor nacelle is arranged at the end part of the V-shaped empennage; wing end tilting electric contra-rotating rotor wing nacelles are arranged at the ends of the wings; and rotor wing units are arranged in the rotor wing nacelles, the six rotor wing units all adopt a coaxial reverse upper and lower two-paddle structure, and the rotating directions of the rotor wings in the six rotor wing units are that the adjacent rotating directions and the opposite rotating directions are opposite.

The invention provides an ornithopter with multi-degree-of-freedom empennage collaborative movement and a control method.The ornithopter comprises a rack, empennage bodies and an empennage driving mechanism, each empennage body comprises an empennage support, a plurality of tail feather bodies, a traction rope guide wheel and a tail feather elastic rope, and one end of each tail feather body is sequentially hinged to one end of the empennage support; the number of the traction rope guide wheels is two, the traction rope guide wheels are arranged in the middle of the empennage support side by side, the tail feather elastic rope is sequentially connected to the multiple tail feather bodies, and the two tail feather bodies on the outermost side are each provided with a connecting part extending towards the other side of the hinged end. The empennage driving mechanism comprises an empennage connecting pipe assembly, a traction steering engine, a winding roll, a traction rope, an empennage torsion steering engine, an empennage deflection steering engine and an empennage pitching steering engine. According to the empennage structure, independent control or combined control of torsion, pitching, deflection and opening and closing actions can be achieved, and the problems that an existing ornithopter empennage mechanism is insufficient in motion freedom degree and lacks an efficient wing-empennage cooperative motion system are solved.

The invention relates to the technical field of unmanned aerial vehicles, in particular to a passive tilting wing unmanned aerial vehicle which comprises a vehicle body, wings, a locking mechanism, a vertical empennage, a thrust power assembly, a posture regulation and control power assembly and a controller, and the thrust power assembly, the posture regulation and control power assembly and the locking mechanism are all electrically connected with the controller. The locking mechanism is responsible for locking angles of the wings in a vertical take-off and landing state and a cruising flight state, the thrust power assembly is arranged on the wings, the wings are rotationally connected with the fuselage, and the thrust power assembly is responsible for generating lift force for vertical take-off and landing and thrust force for cruising flight. The device can also be used for providing underwater thrust during water surface navigation; the passive tilting wing unmanned aerial vehicle can solve the technical problems that an existing tilting wing aircraft is heavy in tilting mechanism, poor in loading capacity, complex in aerodynamic characteristic in the tilting process, large in robustness control difficulty, poor in stability and the like.

An aircraft comprising a fuselage with a nose and a tail arranged on opposite parts to each other along a first longitudinal axis is described; a pair of half-wings arranged on respective mutually opposite sides of the fuselage; a first and a second rotor carried by respective half-wings, respectively rotatable around a second and third axis inclinable with respect to said fuselage, and independently operable from each other; the aircraft is switchable between a first hovering flight or take-off / landing configuration wherein the fourth and fifth axis are arranged orthogonal to said first axis; and a second forward flight configuration wherein the fourth and fifth axis are arranged parallel or inclined with respect to said first axis; the aircraft further comprising a tail portion comprising a first aerodynamic surface, and a third and a fourth rotor rotatable around a fixed fourth and a fifth axis; and support means of the third and fourth rotor connected to a corresponding said half-wing and to a corresponding said fin.

The present disclosure relates to an autonomous, electric, vertical takeoff and landing (VTOL) aircraft that is low-noise, safe, and efficient to operate for cargo transportation over relatively long ranges. A VTOL aircraft includes a fuselage, a plurality of arms, a tail, and a plurality of propulsion systems mounted on the arms and the tail. The plurality of arms have parts that are rotatable and the tail has a part that is rotatable for transitioning the VTOL aircraft between a forward-flight configuration and a hover configuration.

The utility model relates to the technical field of storage and transportation equipment of empennages of unmanned aerial vehicles, in particular to a loading structure of an empennage of an unmanned aerial vehicle, which comprises two frame bodies arranged at an interval, and the interval between the two frame bodies forms an accommodating space of an empennage body; each frame body comprises an upper cross beam and a lower cross beam which are vertically arranged at an interval, and an oblique beam is jointly welded at the front ends of the upper cross beam and the lower cross beam; a plurality of supporting plates are welded between the lower cross beams of the two frame bodies; a plurality of empennage fixing plates are mounted between the oblique beams of the two frame bodies through screws; and a trailing edge mounting plate and a trailing edge middle supporting plate are mounted between the upper cross beams of the two frame bodies through screws. The loading structure provided by the utility model is simple in structure, can load the empennage body and the tail edge of the wing at the same time, and effectively improves the loading efficiency. The loading structure is used for loading the empennage body and the tail edge of the wing, so that the whole can be conveniently put into a container for transportation.

The invention belongs to the technical field of electric heating deicing, and particularly relates to a surface heating electric heating film and a preparation method thereof. Comprising an outer surface insulating layer, a heating layer, a power supply electrode and an inner surface insulating layer, the heating layer is prepared from a carbon-based conductor composite polymeric material in a printing or coating mode, and the carbon-based conductor composite polymeric material is formed by mixing polyimide resin and carbon fibers (or one or more of graphene, carbon nanotubes and the like). The surface heating electric heating film provided by the invention has the characteristics of simple and reliable structure, light weight and surface heating performance, can be applied to ice prevention and removal operation of parts such as aircraft wings, empennages, propellers and the like, and has relatively high practical application value.

The invention provides an aircraft overall optimization design method and device and electronic equipment, and relates to the technical field of aircraft overall design. The method comprises the following steps: calculating the weight of each part of an aircraft based on aircraft design parameters, and calculating the maximum takeoff weight and the gravity center of the whole aircraft by integrating the weight and the gravity center of each part; based on airplane design parameters and the gravity center of the whole machine, parametric modeling is conducted on all the components, pneumatic calculation is conducted, and a lift-drag analysis result is output; establishing an engine performance model according to the engine type and the engine performance parameters, and generating a power curve and an oil consumption curve based on the model; calculating a plurality of aircraft performance indexes; and performing multi-objective optimization by taking the shape parameters of the wing empennage as design variables and taking a plurality of aircraft performance indexes as optimization objectives, and generating a Pareto optimal solution set containing an optimal value combination of the shape parameters of the wing empennage. The defects of subject conflict and long research and development period caused by the adoption of a serial design process in the existing aircraft design are overcome.

The vertical take-off and landing composite layout unmanned aerial vehicle comprises a fuselage and wings symmetrically arranged on the two sides of the fuselage, longitudinal rods symmetrical about the fuselage are arranged below the two wings, a front rotor wing and a rear rotor wing are installed at the front end and the rear end of each longitudinal rod correspondingly, and the tails of the two longitudinal rods are fixedly connected with a trapezoidal empennage; solar panels are integrated on the surfaces of the wings and the empennage; through cooperative control of the front rotor wing and the rear rotor wing, in combination with the propulsive force of the tail propeller and the optimized design of the tail wing of the trapezoidal structure, beneficial pneumatic coupling lift force is generated in the cruising and vertical take-off and landing processes, and due to the design, conversion between a vertical take-off and landing mode and a fixed wing cruising mode can be achieved without an additional variant mechanism; therefore, the flight efficiency is obviously improved. In addition, solar panels are laid on the surfaces of the empennage and the wings, solar radiation can be received to the maximum degree in the flight process, and the endurance time of the unmanned aerial vehicle is effectively prolonged.

The utility model belongs to the technical field of unmanned aerial vehicle packaging protection, and relates to a packaging box for a fixed-wing unmanned aerial vehicle, which comprises a box body, a box cover and a limiting assembly, the box cover is arranged above the box body, and a mounting cavity for placing parts of the unmanned aerial vehicle is formed between the box cover and the box body; the limiting assembly is arranged in the box body, and a fuselage clamping groove, a wing clamping groove and an empennage clamping groove are formed in the limiting assembly; according to the storage and transportation box, the fuselage, the wings and the empennage are clamped through the fuselage clamping grooves, the wing clamping grooves and the empennage clamping grooves respectively, and the positions of the fuselage, the wings and the empennage in the box body are fixed, so that the fuselage, the wings, the empennage and other unmanned aerial vehicle parts are kept relatively static in the storage and transportation process; the unmanned aerial vehicle parts are prevented from being damaged due to mutual collision, the protection effect of the unmanned aerial vehicle parts in the storage and transportation process is improved, and the surface integrity of the unmanned aerial vehicle parts is ensured.

The invention discloses a large seaplane integrated with a distributed electric propulsion technology and a propulsion method, and relates to the technical field of seaplane. Comprising a fuselage, a left wing and a right wing are arranged on the two sides of the fuselage respectively, and a V-shaped hull is arranged at the lower end of the fuselage; and a T-shaped empennage is arranged at the tail part of the fuselage. Through the synergistic effect of the design of the V-shaped ship body and the distributed propulsion system, the whole ship body makes contact with the water surface to provide sufficient buoyancy at the low speed, only the main sliding face makes contact with the ship body to form an air layer at the high speed, and the air film drag reduction effect of a propeller at the bottom of the ship body is matched, so that the water resistance is reduced by 35%-50%, and the draft is reduced by 40%-60% along with speed increase; the problems that a traditional seaplane is large in water resistance and difficult to leave water are effectively solved, meanwhile, the left buoy and the right buoy are in linkage with the attitude control system, wave disturbance can be counteracted in real time, the transverse inclination angle is controlled within 1 degree, the wave resistance is improved to be capable of coping with waves with the height of 1.5 m, and the defects that a traditional seaplane is poor in wave resistance and has strict requirements for taking-off and landing water areas are overcome.

The invention provides a novel composite tilting and folding rotor integrated mechanism and an aircraft, and belongs to the technical field of tilting rotor aircrafts. The mechanism and the aircraft are characterized in that the whole aircraft comprises a fuselage, an empennage, an undercarriage, two wings and two tilting rotor devices. The wings are located on the two sides of the fuselage, rotor wing tilting mechanisms at the tail ends of the wings are driven by hydraulic cylinders to achieve overall rotation, and modes can be switched in the take-off stage and the cruise stage. The folding function of the paddle is controlled by adopting a linear telescopic connecting rod mechanism driven by a hydraulic rod to realize two states of retraction and unfolding; a piezoelectric ceramic material and an energy storage device are embedded in the tilting mechanism, and current is generated by utilizing the piezoelectric effect when the unmanned aerial vehicle flutters, so that electric energy is recycled and supplied to the folding device; meanwhile, a PID control algorithm is adopted, so that the aircraft is good in stability and high in response speed during hovering and vertical take-off and landing; the reliability of the aircraft can be improved, the aerodynamic performance can be improved, and high flexibility and wide application prospects are achieved.

The application aims to provide a single-motor driven multi-mode ornithopter simulating the flight posture of insects and birds, comprising a fuselage, a foldable wing mechanism, a flapping wing and ground walking mechanism, and a steering tail wing mechanism; the flapping wing and ground walking mechanism is a spatial five-link mechanism; in the flight state, the motor outputs power, the five-link mechanism drives the wing to complete the flapping action; in the ground walking state, the electromagnet connection hole is not electrified, the connecting rod driving wheel and the electromagnet right-angle connecting shaft are disconnected, the wing is in the folded state, and the rotation output of the motor is the rotation movement of the driving connecting rod driving wheel; the application integrates the connecting rod and the wheel, realizes the function of single-motor driving two modes, simplifies the mechanism complexity, reduces the manufacturing difficulty, lightens the ornithopter weight, and has good obstacle crossing ability and can cross narrow space.

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned eVTOL capable of being quickly mounted, dismounted and transported, which comprises a fuselage main body structure, a wing structure is arranged at the top of the fuselage main body structure, motor support arms are detachably connected to two sides of the bottom of the wing structure, and an empennage structure is arranged on the rear side of the fuselage main body structure. The fuselage main body structure comprises a framework, a skin is fixedly connected to the surface of the framework, cabin doors are detachably connected to the front side, the right side and the top of the fuselage main body structure, and the surfaces of the cabin doors are detachably connected with the skin. The wing has the advantages of being fast to disassemble, assemble and transport, according to the scheme, the whole wing is split in a three-section mode, the central wing and the fuselage main body are integrated and disassembled disorderly, the left outer wing and the right outer wing can be disassembled in the transportation process, space is saved, and transportation is convenient; separation of the outer wing and the central wing may be restricted by a latch.

The invention provides a patrol flight unmanned aerial vehicle with W-shaped folding wings. The patrol flight unmanned aerial vehicle comprises a fuselage, inner-section wings, inner-section wing limiting structures, inner-side folding and unfolding mechanisms, outer-section wings, ailerons, outer-side folding and unfolding mechanisms, empennages, empennage folding and unfolding mechanisms and empennage protection structures. The fuselage is designed by adopting a flat lifting body configuration, the inner and outer sections of wings are designed by adopting low-speed friendly plane shapes such as rectangles and trapezoids, and the empennage is designed by adopting a V-shaped empennage / inverted V-shaped empennage. The inner section wing and the outer section wing of the unmanned aerial vehicle are integrally in a W shape in the unfolding process, and a folding wing layout with the larger aspect ratio and the higher aerodynamic efficiency can be derived based on the W-shaped layout. According to the layout, the extension length of the wings is slightly restrained by the length of the fuselage, the contradiction between the aerodynamic characteristic design of the wings and the storage space of the launch canister is well balanced and solved under the condition that the length of the fuselage is fixed, and the layout wings are large in aspect ratio, high in aerodynamic efficiency and simple in structural design.

The invention belongs to the field of aviation aircraft design, and discloses a short-distance vertical take-off and landing unmanned aerial vehicle with distributed duct rotor wing combinations and a control mode of the short-distance vertical take-off and landing unmanned aerial vehicle. The unmanned aerial vehicle adopts a wing body fusion layout, and an empennage adopts a T-tail layout; the wings on the two sides of the fuselage are sequentially divided into inner wings and outer wings from inside to outside; on-wing fusion design is adopted, distributed ducted power modules in bilateral symmetry are arranged on the rear portion of the upper surface of a wing, and each distributed ducted power module comprises parallel ducted fans with the same number; a rotor support rod is mounted between the inner wing and the outer wing and adopts an anti-symmetric rod type appearance, a pull-type rotor is mounted at the front end, and a push-type rotor is mounted at the rear end; steering engines are installed in inner cavities of the rotor wing supporting rods. The control modes comprise a cruise mode, a vertical take-off and landing mode and a short-distance take-off and landing mode. Short-distance take-off and landing and vertical take-off and landing can be achieved, the multi-target conflict problem that in the plateau environment, the take-off and landing site is limited, the loading performance is insufficient, and the wind resistance is weak is solved, and the method has the engineering practical value.

The invention discloses a tilt rotor aircraft depending on aerodynamic force, and relates to the technical field of aircrafts. The four-axis unmanned aerial vehicle comprises a fuselage, wing assemblies, four-axis unmanned aerial vehicle modules and empennage assemblies. The wing assembly comprises a left wing, a right wing and a wing cross beam which are all provided with ailerons; the four-axis unmanned aerial vehicle module is I-shaped, is hinged to a wing cross beam through a bearing, and can tilt bidirectionally; the empennage assembly comprises a tail support, a horizontal electric variable pitch propeller, a horizontal empennage with a control surface and a vertical empennage. The four-axis unmanned aerial vehicle module serves as a tilting unit, and the structure is simplified; attitude control is realized by virtue of aerodynamic difference, and the efficiency is improved; the tail horizontal electric variable-pitch propeller realizes rapid pitching adjustment; vertical take-off and landing, low-altitude maneuvering and high-speed cruising capabilities are integrated, the application scene is wide, and safe forced landing can be achieved when faults occur.

An electric vertical take-off and landing aircraft comprises a fuselage and a tilt wing. The tilt wing is tiltable relative to the fuselage in a range of tilt wing angles. Control surfaces are arranged at the tilt wings. The aircraft comprises a horizontal stabilizer with an elevator, in particular a stabilator, a vertical stabilizer with a rudder, in particular a fully movable stabilizer, at least one electric engine for powering main propellers arranged at the tilt wing and at least one software control device. The control device is configured to control at least the control surfaces , the main propellers and the tilt wing angle during hover and transition between hover and cruise flight.

A vertical take-off and landing aircraft includes: a fuselage and 2N tilting rotors. Both sides of the fuselage are provided with a wing symmetrically, a tail of the fuselage is provided with an empennage, and ruddervators are provided at the empennage. 2N tilting rotors are symmetrically provided at both sides of the fuselage, and a part of the 2N tilting rotors are provided on the empennage. N is a natural number greater than or equal to 2; in a vertical take-off and landing state, projections of propellers of the 2N tilting rotors on a horizontal plane are centrally symmetrical about point B, point B and a center of gravity point G of the vertical take-off and landing aircraft are both provided in a symmetry plane of the fuselage.