64 results about "V-tail" patented technology

An aircraft tail section has a first tail component and a second tail component, the first tail component being positioned further forward than the second tail component with respect to a nose of the aircraft. Each tail component has two surfaces, each of the two surfaces of at least one of the first and second tail components comprises a solar panel configured to collect solar energy. Each tail component is rotatable with respect to a centerline of the aircraft such that an offset angle of between zero degrees and 180 degrees is formed between corresponding surfaces of the first and second tail components. Preferably, the tail components are rotated into (i) a takeoff and landing configuration that is substantially horizontal, and (ii) a crosswise configuration during flight such that collection of solar energy is maximized.

The invention provides a power-driven tilt three-rotor unmanned aerial vehicle. The power-driven tilt three-rotator unmanned aerial vehicle has flight characteristics of both a helicopter and a fixed-wing aircraft and can take off and land in a vertical and short-distance way. The integral structure of the power-driven tilt three-rotor unmanned aerial vehicle is composed of all-moving canard wings, straight low wings and a fixed V tail. Two motors and rotors of the unmanned aerial vehicle are fixed at the wing tips of the canard wings and can independently tilt by certain angles along with the canard wings, and another motor and rotor of the unmanned aerial vehicle are installed in the V tail and can tilt by certain angles around a rotating shaft. When the rotating shafts of the thee rotors of the unmanned aerial vehicle tilt to a position near a Z axis, the unmanned aerial vehicle can fly like the helicopter; and when the thee rotors tilt to a position near an X axis, the unmanned aerial vehicle can fly like the fixed-wing aircraft. Through simultaneous control of the thrust and directions of the thee rotors, the reaction torque of the rotors is overcome and the posture of the unmanned aerial vehicle is controlled. The unmanned aerial vehicle provided by the invention can take off and land in a limited place or runway to execute special tasks and is improved in flight speed, duration of flight and payload.

The invention is directed to an actuation system in an aircraft comprising a fuselage and a hinged tail section with at least one interlock component that engages a tail support, wherein the engagement of the tail support to the tail section enables the actuation system to operate. The actuation system pulls in, latches, and locks the tail section during closing of the tail section, and the actuation system unlocks, unlatches, and releases the tail section during opening of the tail section.

A method for preventing the loops from not containing the steel tail features that the load head signal of down stream rolling mill is used as the loop lifting command, the load tail signal of upstream rolling mill is used as the loop lowering command, and the load signal of the first rolling mill is directly used as the control signal of the loop lifters for the next three rolling mills.

Aircraft, such as tri-body aircraft, and associated methods of manufacture. In one embodiment, a tri-body aircraft has a fuselage with a forward portion extending at least partially forward of an aft-mounted main wing and first and second aft portions extending at least partially aft of the main wing. The forward fuselage portion and the first and second aft fuselage portions can include passenger cabins that are connected, allowing passengers to travel between the cabins during flight. In another embodiment, the aircraft includes a propulsion system having a first engine nacelle positioned at least proximate to the first aft fuselage portion, a second engine nacelle positioned at least proximate to the second aft fuselage portion, and a third engine nacelle positioned atop an inverted V-tail extending upwardly from the first and second engine nacelles.

The invention relates to a positioning drive mechanism for an aircraft full-movement V tail. The positioning drive mechanism comprises a rudder shaft, an upper bearing sleeve, an upper joint bearing, a cylindrical positioning sleeve, a connection key, a semi rocker arm, a cone positioning sleeve, a lower bearing sleeve, a lower joint bearing, a shaft end cover, an upper bearing base, a lower bearing base, a servo actuator and a servo actuator bracket, wherein the upper bearing base and the lower bearing base are connected with an aircraft body frame to form a box-shaped structure so as to increase bending resistance and torsion resistance of the support structure, the upper joint bearing and the lower joint bearing provide rotation support for the rudder shaft, the semi rocker arm is connected with the rudder shaft through the connection key so as to change a load output by the servo actuator into a torque for driving the rudder shaft to deflect, the cone surfaces of the lower bearing sleeve and the lower bearing base are matched to perform centering, and the cylindrical surface matching position of the lower bearing sleeve and the lower bearing base is provided with threaded half holes to auxiliarily load and unload the full-movement V tail. According to the present invention, reliable positioning drive and convenient loading and unloading of the rudder surface of the aircraft with characteristics of large size, inclined angle and dual pivot point cantilever support are concurrently achieved.

The invention discloses a novel trans-domain multiphibious carrier, which includes a fuselage, a tail, a V-tail, a landing gear, first to second wings, first to second buoys, first to fourth hydrofoils, first to fourth angle adjustment modules, first to second deflection motors, first to second power motors, first to second built-in propellers, and first to second auxiliary flight modules. The invention adopts unique shark-like shape design, has excellent aerodynamic and hydrodynamic performance, and can realize rapid motion under water and in the air. The use of hydrofoils enables the vehicleto move quickly and flexibly on the water surface, and the use of tilting ducts and tilting propellers enables the vehicle to move vertically and flexibly. The carrier of the invention has the characteristics of a tilting aircraft, a hydrofoil boat and a submarine.

The invention relates to a horizontal taking-off and landing two stage to orbit (TSTO) reuse aerospace plane layout. A first-stage aircraft and a second-stage aircraft are included, and the second-stage aircraft and the first-stage aircraft are in up-down horizontal parallel layout; the second-stage aircraft is in wing body combination body layout with a wedge-shaped head, a fusion edge strip, a small-span-chord-ratio sweepback thin wing and a central vertical fin; and the first-stage aircraft is in wing body combination body layout of a cathedral sweepback wing with the waverider characteristic, a downwards-folding wing tip and a V tail. The horizontal taking-off and landing TSTO reuse aerospace plane layout meets the TSTO flight principle based on the turbine based combined cycle (TBCC),the design demands of the whole speed domain, the whole airspace lift-drag matching, push-resistance matching, operation-stability matching, volume-weight matching and the like are reached, and the closure of the TSTO technical scheme in the conceptual design stage is achieved.

The invention provides a bionic undercarriage system for a flapping wing air vehicle and a takeoff and landing control method. The bionic undercarriage system comprises a visual navigation unit, a motion coordination processor, a gripper unit and a full-motion V-tail actuator mechanism, wherein the visual navigation unit comprises a left camera, a right camera and an image processor; the left camera and the right camera are symmetrically installed in front of the abdomen of the flapping wing air vehicle; the left camera and the right camera are connected to the image processor; and the motion coordination processor is installed in the fuselage of the flapping wing air vehicle and is respectively connected with the image processor, a left gripper steering engine, a right gripper steering engine and the actuator mechanism. The bionic undercarriage system has the advantages that after the bionic undercarriage system is installed, the flapping wing air vehicle has takeoff and landing capabilities like birds, the efficient maneuverability of the flapping wing air vehicle is improved, the application range of the flapping wing air vehicle is expanded, and the capabilities of the flapping wing air vehicle are enhanced.

The invention discloses a selective catalytic reduction (SCR) tail-gas after-treatment system fault diagnosis instrument, which comprises a controller network (CAN) communication module, a microcontrol unit, a storage device, a display screen, a keyboard and a power supply. The CAN communication module is electrically connected with an SCR tail-gas after-treatment system and an engine. The microcontrol unit is electrically connected with the CAN communication module and the display screen. The storage device is electrically connected with the microcontrol unit, and the keyboard is electrically connected with the microcontrol unit. The power supply is electrically connected with the microcontrol unit. Due to the adoption of the SCR tail-gas after-treatment system fault diagnosis instrument, the fault of the SCR tail-gas after-treatment system can be accurately judged, the fault finding time can be shortened, and convenience in use and carrying also can be realized.

The invention relates to a V-tail unmanned aerial vehicle with an oil tank embedded into a blended wing body. The unmanned aerial vehicle can be used to execute flight missions such as scientific experiments, remote sensing, aerial photographing and the like. The unmanned aerial vehicle is characterized in that: 1) the duration of flight is long and flight missions with high requirements can be conducted conveniently; 2) the use is simple and the operation is convenient; 3) the stability is good and devices such as autopilots, aerial photographing cameras, video cameras and the like can be carried; and 4) the requirement on taking-off and landing conditions is low. According to one aspect of the invention, the small unmanned aerial vehicle comprises a body (1), wings (3), an empennage (7), a left front oil tank (16), a left rear oil tank (15), a right front oil tank (13) and a right rear oil tank (14), wherein the wings (3) are connected on the body (1); and the left front oil tank (16) is arranged at the left front of the internal part of the body (1), the left rear oil tank (15) is arranged at the left rear of the internal part of the body (1), the right front oil tank (13) is arranged at the right front of the internal part of the body (1) and the right rear oil tank (14) is arranged at the right rear of the internal part of the body (1). According to the further aspect of the invention, the left front oil tank, the right front oil tank, the left rear oil tank and the right rear oil tank are respectively provided with shapes adaptive to the wing profile of the body and balanced oil consumption sequences.

The invention provides a method for qualitatively and quantitatively analyzing long straight side chain cyclane and alkylbenzene of hydrocracking tail oil, and belongs to the technical field of qualitative and quantitative analysis of detailed physical properties of the hydrocracking tail oil. The GC-MS is adopted for qualitatively analyzing compositions in raw materials and quantitatively analyzing the detailed compositions of the long straight side chain cyclane and alkylbenzene. The analytical method comprises the following steps: preparing samples; dissolving a sample HVGO5 by normal hexane; performing the qualitative analysis; and adopting an SIM method to draw an external standard curve to quantitatively analyze the detailed compositions of the long straight side chain cyclane and alkylbenzene. By comparing with different analytic methods, the method suitable for qualitatively analyzing the long straight side chain cyclane and alkylbenzene of the hydrocracking tail oil is established; moreover, the method for considering the influence of a response factor is adopted in the quantitative analysis, so that the problem of the quantitative calculation for materials without master standards is solved.

The invention relates to a fish head and tail cutting device. The fish head and tail cutting device comprises a frame, a fish tail fixing plate, a fish head fixing plate and a supporting plate, and the fish tail fixing plate, the fish head fixing plate and the supporting plate are sequentially arranged on the frame from top to bottom. The fish tail fixing plate is provided with a plurality of first through hole, the fish head fixing plate is provided with a plurality of second through holes in one-to-one correspondence to the first through holes, the first through holes and the second through holes are internally provided with air bags communicated with an inflation and deflation device, two opposite fish body fixing plates are arranged between the fish tail fixing plate and the fish head fixing plate and driven by a first air cylinder. The fish head and tail cutting device further comprises a fish tail cutter and a fish head cutter, and the fish tail cutter and the fish head cutter are arranged horizontally and driven by a second air cylinder and a third air cylinder respectively. The fish head and tail cutting device which substitutes for manual operation is high in processing efficiency.

The simplified inverted V-tail aircraft comprise of fixed inverted V-tail stabilizers, wing mounted elevons, with no moving control surfaces attached to the fixed inverted V-tail stabilizers. Elevons act as elevators as well as aileron elements and rudders and the design is simplified, making construction far less costly. No control cables or other control devices are required to be routed to the inverted V-tail. Moreover, the number of control surfaces is reduced and limited to the wing portion of the aircraft. The inverted V-tail may thus be made in one piece, for example, using composites, thus simplifying construction considerably.

The invention discloses a redundancy architecture method for a flight control system for a large-scale medium-high-altitude reconnaissance and attack integrated unmanned aerial vehicle. The flight control system comprises three parts, namely a flight sensor, a redundancy flight control computer and an execution mechanism. According to the redundancy architecture method for the flight control system, corresponding redundancy design is carried out on each part; the flight control computer part adopts a three-redundancy hardware architecture based on FlexRay and Can buses; and the execution mechanism part comprises an aileron steering engine, a V-tail steering engine, a front wheel steering engine, an air door steering engine, an accelerator steering engine and a propeller speed regulation steering engine. The method has the advantages that the corresponding redundancy design is carried out on all the components of the flight control system, the three-redundancy flight control computer and the distributed architecture design based on the FlexRay and Can buses enable the system to eliminate the Byzantine General's fault, and therefore the reliability is improved, meanwhile, the expansibility is high, the structure is simple and flexible, and the maintenance cost is low, and the like; and the system can simultaneously meet the requirements of high reliability, low cost and high costperformance of the unmanned aerial vehicle.

The invention relates to an automatic skiving machine for the head and tail of a shoe last, which mainly solves the problem that in the prior art, when the head and tail allowances of a last is skived, only a manual operation method can be adopted, thereby resulting in low production efficiency and poor skiving effect, so that the quality of products is influenced. The automatic skiving machine comprises a rack, the rack is provided with a positioning device, a head dresser and a tail dresser, a sliding frame formed in such a way that a hydraulic cylinder on the head dresser is connected with the sliding frame carries out a linear reciprocating motion along a sliding rail and drives a first ring tool to cooperate with the head of a shoe last, and a sliding plate formed in such as way that a hydraulic cylinder on the tail dresser is connected with the sliding plate can slide upwards and downwards along the surface of the tail end of the last so as to drive a second ring tool to cooperate with the tail end of the shoe last. Because the head and tail of a shoe last are subjected to dressing by using the fully automatic skiving machine, the production efficiency is high, and the head and tail of the shoe last are dressed smoothly and completely, and the product quality is high.

The invention discloses an aerodynamic layout of a high altitude long flight time tandem wing aircraft adopting a tail wing with high back wing support and belongs to the field of aerodynamic layout designs of aircrafts. According to the aerodynamic layout disclosed by the invention, the aircraft comprises a cylindrical section body, front wings and a rear wing with a large aspect ratio, V-shaped tail wings and a vertical fin, wherein the front wings are lower single wings and are symmetrically mounted on the front half section of the body; totally two V-shaped tail wings are symmetrically mounted on the rear half section of the body; the rear wing is mounted at the tip of the V-shaped tail wings in a V tail supporting manner; the vertical fin is mounted below the tail of the body; and an engine is mounted above the tail of the body. Large elongation can be avoided by using the tandem wing layout under the condition that the same wing area is guaranteed, the requirements on the structural strength and rigidity of the wings are further reduced, the weight of the aircraft is lightened, and the effective load is increased; and with the adoption of a reasonable aerodynamic surface fit manner, the aircraft has excellent flight stability and controllability under the condition that excellent aerodynamic characteristics are guaranteed.

The invention provides a rocket engine integration wave rider aircraft. The aircraft comprises wave-riding wings (1), a load bin (2), an engine bin (3), a tail bin (5), V tails (4) and an engine tailspraying pipe (6). The load bin (2), the engine bin (3) and the tail bin (5) are sequentially connected in a transition manner to form an aircraft body. The wave-riding wings (1) are located below theaircraft body. The V tails (4) are symmetrically installed above the tail portion of the engine bin (3) and the tail bin (5). The engine tail spraying pipe (6) extends out from the end face of the rear portion of the tail bin (5). The wave-rider aircraft can solve and avoid the technical problems that the shape of a combination body of an existing boosting gliding hypersonic flight vehicle and aroll booster is poor in stability characteristic, high dynamic pressure stage separation risk of the non-axis symmetry shape is high, and the aerodynamic resistance of a driving section is large, andthe overall performance indexes such as the higher lift-drag ratio and the higher filling volume utilization rate are achieved.

A tail-wheel-free combined left-turning driven disk plow is a drive tillage implement, consisting of a drive tillage disk and a moldboard plow, and having the advantages of low oil consumption, low traction resistance, high production efficiency and high oil penetrating performance. The structure of the disk plow comprises a suspension bracket assembly, a central transmission assembly, a main beam, a side transmission box assembly, a disk tillage component assembly, a right side plate, a tail plow assembly, and on the like. With the adoption of the implement, the complex tail wheel device is eliminated and the machining cost and the raw material consumption are reduced; the lateral force is mainly balanced by a plow side plate of the moldboard plow arranged on the tail part, so the balancing property is high, the disk plow is suitable for paddy field dry tillage and dry land tillage, and capable of being developed and used in large dry farming areas, so that the novel tillage implement which saves energy, reduces emission, enhances gain and reduces cost is provided to the agricultural industry.

The invention discloses a built-in V tail vane surface driving mechanism. The built-in V tail vane surface driving mechanism comprises a machine body and a vane surface. Steering engines for providing driving power, first tumblers for being connected with the steering engines, a second tumbler for driving the vane surface, a third tumbler for being in transmission driving connection with the second tumbler, and connecting rods for being in transmission connection with the first tumbler and the third tumbler are arranged in the machine body. The first tumblers are steering engine pieces for connecting the steering engines with the connecting rods, the second tumbler is a driving stirring piece directly connected with the vane surface in a matched mode and used for driving the vane surface, and the third tumbler is a shaft seat transmission stirring piece and is in driving connection with the driving stirring piece through an arranged stirring piece connecting shaft. The built-in V tail vane surface driving mechanism is convenient to assemble, more reliable in driving and more attractive in appearance, and the internal space of the machine body can be more effectively utilized through modular installation of an overall framework.

The invention relates to a simplified model design method suitable for mechanism research of a complex hypersonic aircraft. The design of the complex hypersonic aircraft is simplified according to thefollowing simplified design criteria to obtain a simplified model for mechanism research; and the complex hypersonic aircraft is a two-stage parallel aircraft. The simplified model comprises a first-stage simplified model and a second-stage simplified model which meet the original parallel relation, the simplified design criterion is that the two-stage simplified model removes the appearance endof an original second-stage standard model, and other characteristics are unchanged; and the appearance of the first-stage simplified model is kept consistent with that of an original first-stage standard model in front of the position of a second-stage standard model head, and a V tail is reserved.

The invention discloses a fish-tail-imitating propulsion device suitable for a small waterplane area catamaran, and is mainly used for the field of boats and ships. The fish-tail-imitating propulsion device comprises a steering engine for supplying the dynamic effect, fish-tail-imitating hydrofoils, springs, connecting rods, rocking rods and pin nails. According to the fish-tail-imitating propulsion device disclosed by the invention, the connecting rods are driven by the steering engine to move, the rocking rods are driven by the connecting rods to move, and the fish-tail-imitating hydrofoils are driven by the rocking rods to move; because the pin nails for connecting the rocking rods and the fish-tail-imitating hydrofoils are eccentrically fixed relative to the fish-tail-imitating hydrofoils, the fish-tail-imitating hydrofoils can swing around the pin nails under the driving of the rocking rods, so that propulsion force consistent with fish tails can be generated.

The invention belongs to the field of the biological test instruments and relates to a device for preventing climbing on tail in an animal tail suspension test. The device is capable of preventing an animal from climbing on the tail in an animal tail suspension test. The device is composed of a main suspension arm, a main beam, an upper connecting shaft, a threaded rod, a tension meter, a lifting ring, a suspension arm, a spring plate, semilunar tail climbing preventing plates, a circular ring hook and the like. The height of the tension meter is adjusted by use of a screw on the threaded rod so that the root part of the tail of the animal is slightly lower than the lower parts of the semilunar tail climbing preventing plates. The circular ring hook is fixed to the 1 / 3 part, close to the tail end, of the tail of a mouse by use of an adhesive tape; the semilunar tail climbing preventing plates are divided and stabilized on both sides; the circular ring hook fixed on the tail of the mouse is suspended on a lifting hook. Two semilunar tail climbing preventing plates are connected by use of four connecting fasteners to form a circular structure in the center of which a hole is formed; the tail of the mouse passes through the central round hole and the root part of the tail of the mouse is basically flush with the lower part of the central round hole. The size of the central round hole is smaller than that of the head of the mouse so that the head of the mouse cannot pass through the central round hole and only can contact the root part of the tail of the mouse at top, and therefore, climbing on the tail is prevented.

The invention provides a bolt connecting pair with a function of preventing a nut from rotating towards the loosening direction. According to the technical scheme, the bolt connecting pair at least comprises a bolt connecting pair body, wherein the bolt connecting pair body at least comprises a tail section bolt (1), a nut (2), a one-way or two-way rotation-stopping nut tail (5) with a sleeve, a one-way or two-way rotation-stopping bolt tail (7), a two-tail common rotation-stopping accessor (8) and a locking mechanism (9); and the nut (2) is matched with the tail section bolt (1). Alternatively, the bolt connecting pair at least comprises a bolt connecting pair body which at least comprises a tail section bolt (1), a one-way or two-way rotation-stopping nut (6) with a tail, a one-way or two-way rotation-stopping bolt tail (7), a two-tail common rotation-stopping accessor (8) and a locking mechanism (9). From the above, the bolt connecting pair has the advantages that the nut is prevented from rotating towards the loosening direction, so that the nut cannot be screwed off from the bolt.

The invention discloses an aerodynamic configuration of a dual-fuselage multipurpose carrier aircraft with a high aspect ratio support wing, belonging to the technical field of aerodynamic configuration design of the aircraft. Includes engine, main wing, engine attachment, fuselage, support wing, payload, payload attachment, v-tail, tail support and support wing tip attachment. A support wing configuration is combine with a two-fuselage configuration, the aspect ratio of the main wing is greater than 35, the engine has two, each engine has a fuselage directly beneath it, each fuselage has a supporting wing symmetrically arranged on the left and right sides, when the fuselage is in the horizontal position, the leading edge of the supporting wing and the trailing edge of the main wing in thehorizontal direction coincide length in the chord length direction is 0% of the chord length of the main wing at the position 40%. A support wing is arrange below that trailing edge of the main wingto carry out the support layout, the structural rigidity of the main wing is increased, the adverse interference between the support wing and the main wing is reduce, and different payloads can be mounted.

A triphibian cross-medium transverse tilting double-rotor aircraft comprises a fuselage, wings and tilting rotor mechanisms, the wings are symmetrically arranged on the left side and the right side of the fuselage, rotor mechanism mounting holes are formed in the middles of the wings, and the tilting rotor mechanisms are arranged in the rotor mechanism mounting holes; a ventral fin is arranged below the rear part of the fuselage, a V tail is arranged above the rear part of the fuselage, and a control surface is arranged on the V tail; an upper reverse winglet and a lower reverse winglet are respectively arranged at the tip of the wing, and an aileron is arranged at the rear edge of the wing; a water tank is arranged in the root of the wing, a vent hole is formed in the top of the water tank, a waterproof vent valve is arranged at the vent hole, a water through hole is formed in the lower part of the water tank, and a throttle valve is arranged at the water through hole; a water pumping opening in one end of the bidirectional water pump is communicated with the water through hole of the water tank through a water conveying pipeline; a water changing hole is formed in the bottom of the machine body, a water pumping opening in the other end of the two-way water pump communicates with the water changing hole through a water conveying pipeline. The aircraft disclosed by the invention has the capabilities of flying in the air, sailing on the water surface and sneaking underwater, and all modes can be freely switched.

The invention provides a bionic landing gear system and a landing control method applied to a flapping-wing aircraft. The bionic landing gear system includes: a visual navigation unit, a motion coordination processor, a mechanical claw unit and a full-motion V-tail actuating mechanism; the visual The navigation unit includes a left camera, a right camera and an image processor; the left camera and the right camera are installed symmetrically in front of the abdomen of the flapping wing aircraft; the left camera and the right camera are all connected to the image processor; The motion coordination processor is installed inside the body of the flapping-wing aircraft, and is respectively connected with the image processor, the left mechanical claw steering gear, the right mechanical claw steering gear and the actuator mechanism. The advantages are: after the bionic landing gear system is installed, the flapping-wing aircraft can have the take-off and landing capability like a bird, which improves the high-efficiency maneuverability of the flapping-wing aircraft and expands its application range and capability.

The invention discloses a tail-gas treating process in the preparation process of calcined clay. The tail-gas treating process comprises the following steps: cleaning and treating acid-removing gas by traditional tail-gas treating method. The tail-gas treating process is characterized by comprising the detailed steps of: (1) collecting and treating residual heat of tail gas and cooling the tail gas; (2) introducing the tail gas into a water pool, cleaning the tail gas, precipitating dust and solid particles in the tail gas to obtain slurry, wherein residual tail gas becomes wet gas; and (3) introducing wet gas of the tail gas into NaOH solution, enabling SO2, SO3 and CO2 in the tail gas to react with NaOH to obtain and discharge sodium salt and clean tail gas. The tail-gas treating process disclosed by the invention has the advantages that the problem of tail-gas treatment in the traditional manufacturing process of the calcined clay is solved, the residual energy in the tail gas is fully utilized, and the harmful gas components of the tail gas are purified, so that the environment is protected, the tail-gas treating cost of a company is saved, and more benefit for production of the company is saved. The tail-gas treating process has the advantages of simple process, high treating efficiency and low cost.

The invention relates to an overall aerodynamic layout of a double-engine unmanned aerial vehicle. The overall aerodynamic layout of the double-engine unmanned aerial vehicle is characterized in thatthe unmanned aerial vehicle comprises a vehicle body (1), a large-size radome (2), a wing (4), short cabins (3), propellers (5), a V tail (6) and a blocking hood (11); the section of the vehicle body(1) is in a ship shape, the span-chord ratio of the wing (4) is 15:25, and the vehicle body (1) and the wing (4) are in fused transition in shape; a flap (7), a flaperon (8) and an aileron (9) are arranged on the wing (4), and a lifting rudder (10) is arranged on the V tail (6); and engines are mounted on the inner section of the front edge of the wing through the short cabins (3), and the propellers (5) are mounted at the front ends of the short cabins. The unmanned aerial vehicle adopting the short-distance taking-off and landing layout can meet the overall, aerodynamic, structural and taking-off-and-landing-performance requirements and has the advantages of being wide in flying speed range, high in lift-to-drag ratio, short in taking-off and landing distance and the like, and the short-distance taking off and landing unmanned aerial vehicle layout can be used for aerodynamic layout design of scouting and attaching integrated unmanned aerial vehicles, attaching-type unmanned aerial vehicles, scouting-type unmanned aerial vehicles and special unmanned aerial vehicles.