49results about How to "Improve cruise efficiency" patented technology

The invention relates to a tilt rotor aircraft adopting parallel coaxial dual rotors, which comprises a fuselage, wings, an empennage, a pitch control scull system, a landing gear, a power and fuel system, a transmission system, a rotor system, a rotor nacelle and a tilt system, wherein the wings are arranged at the center section of the fuselage; the empennage and the pitch control scull system are arranged at the tail of the fuselage; the landing gear is positioned at the belly of the fuselage; the power and fuel system is arranged inside the center section of the fuselage and is connected with the rotor system and the pitch control scull system through the wings and the transmission system in the fuselage; the rotor system is arranged on the rotor nacelle at the tip of the wings; partial wing which is fixedly connected with the rotor nacelle and simultaneously can tilt is arranged at the inner side of the rotor nacelle; and the tilt system is arranged in the wings and is connected with the rotor nacelle and the partial wing which can tilt. The tilt rotor aircraft is mainly characterized by adopting the pitch control scull system, the parallel coaxial dual rotors and the partialwing which can tilt to realize flight status transformation and conventional taxiing and landing, thereby improving the forward speed and the propulsive efficiency.

A tilt rotor aircraft adopting a thrust tail rotor and a slipstream rudder for operation and propelling and a design of two parallel rotary wings and common pneumatic distribution comprises an airframe, wings, an empennage, a system of thrust tail rotor and slipstream rudder, an undercarriage, a power-fuel system, a transmission system, a rotary wing system, a rotary-wing nacelle and a tilt rotor system of the rotary-wing nacelle. The aircraft adopts the system of the thrust tail rotor and slipstream rudder to operate the VTOL and the pitching and drifting of the forward flight; the system comprising the thrust tail rotor, an elevator and a rudder is arranged on the empennage; a tilting wingtip appears as a small-area wing which is arranged on the outside of the rotary-wing nacelle and rotates together with the rotary-wing nacelle; the plane shape of the tilting wingtip appears as a trapezoid of leading edge sweepback and trailing edge sweepforward and the aspect ratio is 1.5 and the area of the tilting wingtip occupies about 15 to 20 percent of the whole wing area and the tilting wingtip is just integrated with the appearance of the rotary-wing nacelle and fixedly connected with a nacelle bevel gear box. The tilt rotor aircraft is a novel aircraft type with the development potential and prosperous prospect.

The invention provides an unmanned aerial vehicle cruising and monitoring system for forest fire. The weight of the unmanned aerial vehicle is reduced, flight time is prolonged, an unmanned aerial vehicle cruising range is enlarged, route planning is carried out for fire monitoring, and an unmanned aerial vehicle flight control system is combined with a geographic information system. The route planning not only guarantees monitoring quality and monitoring full coverage but also considers the hardware parameters and the flight safety of the cruising unmanned aerial vehicle, a rotary head carries a thermal infrared imager and a colorful high-definition camera, the thermal infrared characteristics of the image of the forest fire are fully utilized, and an automatic monitoring and identification method for forest fire information is designed. Even if the forest fire monitoring distance of the unmanned aerial vehicle is long, fire characteristics can be accurately captured. A colorful high-definition image is compressed and transmitted back to a ground command post, a high-definition fire video image can be quickly transmitted to the ground, a fire position can be accurately reported, so that convenience is brought to the ground command post in accurately judging a fire situation and organizing people to fight the fire, and precious fire-fighting time is saved.

The invention relates to a layout scheme of a tilt rotor transport aircraft. According to the layout scheme, the tilt rotor transport aircraft comprises a body, front wings, rear wings, front-rear-wing connecting end plates, a vertical tail wing, rotor wings, front wing auxiliary wings, rear wing auxiliary wings, a rotatable main shaft, engines, engine small-angle rotating mechanisms, a slip-flow rudder, a slip-flow rudder surface and a rudder; the body is connected with the front wings, the rear wings, the rotatable main shaft and the vertical tail wing; the front wings and the rear wings are arranged on the front end and the rear end of the body, and the front wing auxiliary wings and the rear wing auxiliary wings are respectively installed on the front wings and the rear wings; the vertical tail wing is installed on the tail end of the body, the rudder is installed on the vertical tail wing, and the rotatable main shaft is connected with the engine small-angle rotating mechanism in a rotating manner; the rotor wing is installed on an output shaft of the engine; the slip-flow rudder is installed on the rotatable main shaft, and the slip-flow rudder surface is installed on the slip-flow rudder. The invention relates to a control method of the tilt rotor transport aircraft. The control method comprises five steps. By adopting the layout and the control method of the tilt rotor transport aircraft, the pneumatic interference and mode transformation between the rotor wings and the wings of the aircraft can be solved, the transport capacity and the vertical take-off and landing capacity of the connected-wing layout can be reasonably combined, and a novel type of transport aircraft is formed.

The invention provides a natural laminar flow aerofoil profile with high lift. The natural laminar flow aerofoil profile is characterized in that the aerofoil profile is of a streamlined structure with a blunt-end leading edge and a weakly recurved trailing edge and the surface curve of the aerofoil profile is simply geometrically convex and is free of obvious curvature and inflection.

The invention discloses a jet-propelled flap lift augmentation joined wing system. The jet-propelled flap lift augmentation joined wing system comprises a turbofan engine, an airfoil, a hanger and a turbine shaft rectifying cone, wherein the airfoil is provided with a rear-edge flap, the turbine shaft rectifying cone extends backwards for a given length and is provided with a plurality of scale-type convergence dispersion spray pipes, the left side and the right side of an outer duct spray opening are respectively provided with an airflow convergence dispersion apparatus consisting of an outer front edge and two outer convergence dispersion sheets, the left side and the right side of an inner duct spray opening are respectively provided with an airflow convergence dispersion apparatus consisting of an inner front edge and two inner convergence dispersion sheets, the airfoil is a joined wing. When the jet-propelled flap lift augmentation joined wing system takes off and lands perpendicularly, an upward lift resultant force can be generated; when the jet-propelled flap lift augmentation joined wing system flies in a level cruising manner, a thrust force and a lift force can be generated; an aircraft utilizing the jet-propelled flap lift augmentation joined wing system disclosed by the invention can vertically take off and land and fly at a high speed and can be stably switched between the vertical taking-off and landing and high-speed flight.

The invention discloses a manufacturing method of a light aerofoil with super-high aspect ratio and high lift-drag ratio and an aerofoil manufactured thereby. At present, some used optimized design methods for improving the strength and the rigidity of the aerofoil with the high aspect ratio have the limited improvement space; and if a method for increasing geometrical characteristic parameters of the sections of the plasmodium is adopted, the structure weight of the aerofoil needs to be increased and the effect is poor. By the manufacturing method adopted by the invention, these problems are solved. According to the overall configuration of an aircraft, the aerofoil is divided into a plurality of sections; tensile wires are arranged according to a certain mode section by section. The research result shows that the original bending function of the aerofoil is replaced by the tension of the tensile wires and the impaction of the aerofoil, and under the premise that the structure weight is basically not increased, the rigidity and the strength of the aerofoil with the high aspect ratio are greatly improved, and the pneumatic elastic deformation is reduced to be within 10 percent of the traditional aerofoil. The manufacturing method is very important for the practical application of the aerofoil with super-high aspect ratio, the cruising efficiency of the aircraft can be greatly improved, and the fuel consumption and the cost are reduced.

The invention relates to a distributed intelligent search and rescue system using an unmanned aerial vehicle on sea. The search and rescue system comprises the unmanned aerial vehicles and a search and rescue vessel. The unmanned aerial vehicles are disposed on the search and rescue vessel. Each of the unmanned aerial vehicles comprises the following modules: a positioning navigation module, an infrared sensing module, an infrared camera module, an image signal processing module, a wireless communication module, an information collecting module, a control unit, a flight unit and a power supply. The search and rescue vessel comprises the following modules: a video coding module, a display device, an alarm device, a wireless communication module, a digital-to-analog conversion module, a positioning and cruising module, a controller and a power supply device. The control unit of the unmanned aerial vehicle is a sub-module of the controller of the search and rescue vessel. As a total control center, the controller can control multiple control units, that is, the number of the unmanned aerial vehicles exceeds two, thereby realizing distributed search, and having better search effect. The invention has the advantages of automatic positioning, high cruising efficiency, wide distribution range and timely rescue.

The present invention discloses a high-aspect-ratio wing frame architecture design method and relates to the technical field of aircrafts. The design method comprises a rigid wing optimization step and an elastic wing optimization step. The rigid wing optimization step comprises generating an initial population of the wing architecture, performing lift-drag ratio calculation to obtain a local optimal solution, then carrying out optimizing calculation, performing lift-drag ratio calculation on the local optimal solution and comparing with the local optimal solution obtained after the initial population is subjected to the lift-drag ratio calculation, and finally judging the globally optimal solution; and the elastic wing optimization step comprises calculating the aerodynamic load borne by an elastic wing during an flight, then calculating the elastic deformation of the wing, solving the true form of the wing structure under elastic balance at the flight state through multiple iterative computations to obtain the flight load after the elastic deformation and acquire the twist angle of a wing profile architecture, and thus completing the design of the wing frame architecture. The wings designed through the high-aspect-ratio wing frame architecture design method have good geometrical aerodynamic twist angle distribution, the lift distribution is better, the smaller induced resistance can be produced, the best lift-drag ratio is obtained, and thus the cruising efficiency is improved.

The invention discloses a trapezoid layout tandem tilt wing aircraft and a tilting mechanism thereof. Tandem wing layout, trapezoidal power system arrangement, multiple control surfaces and electric power system differential combination control are adopted, so the aircraft integrates vertical takeoff and landing functions and high-speed hover performance advantages, and also has the long-enduranceand long-range characteristics of a fixed wing aircraft and the hovering and vertical takeoff and landing characteristics of a helicopter. The vertical takeoff and landing and the air fixed wing modecruising are completed through the tilting wing layout, so the requirements for a taking off and landing place are reduced, and the cruising efficiency is improved; the trapezoid dynamic system layout can improve the efficiency of propellers; the roots of wings and a fuselage are fused, and the tilting sections of the wings and the fuselage section fused wing roots are connected and rotate relative to each other, so the mounting and positioning precision of the wings is improved; and the multi-control surface layout of the wings makes the control surfaces on the wings generate the rudder effect by using rotor wake during the vertical takeoff and landing, and attitude control participating in the vertical take-off and landing state reduces the control surfaces of a vertical fin, so the structural efficiency is improved.

The invention belongs to the technical field of flying automobiles, in particular to a flying automobile with folding wings for vertical take-off and landing, which comprises a body, a folding wing, atail wing, a power system, a transmission mechanism and a landing gear. The power system is composed of a rotor duct system, a tail propeller and a pitch mechanism. The rotor duct system comprises four sets of coaxial dual rotor ducts. The invention solves the technical problems of long take-off and landing distance of flying vehicles, high requirements on take-off and landing sites, low liftingefficiency, high fuel consumption and insufficient stability of ducted rotor flying vehicles in the prior art. Higher lift acquisition rate, lower fuel consumption, higher reliability, higher safety,and lower cost.

The invention discloses a robot cruise control method and device, a control device and a storage medium, which are used for improving the cruising efficiency of the robot and the reliability of execution of cruise mission. The robot cruise control method comprises the following steps: controlling a robot to move to a target patrol point according to a planned path; determining whether the target patrol point is reachable during the process of controlling the robot to move to the target patrol point; and if judging that the target patrol point is unreachable, controlling the robot to skip the target patrol point.

The invention provides a natural laminar-flow supercritical wing section applied to a sweepback wing of an intermediate range civil airplane. The natural laminar-flow supercritical wing section has the following pressure distribution form: a bump appears in a front edge area of an upper surface, i.e., an area with a chordwise range of 0 to 5 percent C, a pressure coefficient height of the bump is 0.05, a bump area accounts for 0.3 percent of a whole pressure distribution area, which is used for inhibiting the unstable disturbance development of a three-dimensional cross-flow CF wave; and a favorable pressure gradient is kept in an area from the back of the bump to a shock wave position, which is used for inhibiting the unstable disturbance development from a two-dimensional flow to a TS wave. The natural laminar-flow supercritical wing section has the advantages that the development of the two-dimensional TS wave disturbance and the three-dimensional cross-flow CF wave disturbance can be simultaneously inhibited, the transition of boundary laminar flow occurring in the front edge area when the wing section is arranged on the sweepback wing can be avoided, so that a relatively large-scale natural laminar flow can still be maintained on the surface of the sweepback wing, the resistance of a whole airplane can be reduced, the cruise efficiency is increased, and the consumption of fuel oil and carbon dioxide discharging can be reduced.

The invention relates to a method and a system for planning paths of marine unmanned ships. The method comprises the following steps: generating a raster map of a sea area to be cruised; generating random cruising paths of multiple unmanned ships in the raster map; obtaining history cruising data of each unmanned ship; predicting an estimated arrival time of each unmanned ship when passing each raster in the cruising path; judging whether the cruising path of each unmanned ship and the cruising paths of other unmanned ships have repeated raster, if judging that difference between estimated arrival time of multiple unmanned ships which pass the same raster is greater than a first threshold if the cruising path of each unmanned ship and the cruising paths of other unmanned ships have repeated raster; and adjusting the cruising path of one unmanned ship if the difference between estimated arrival time of two unmanned ships which pass the same raster is less than or equal to the first threshold so as to enable the cruising path of the unmanned ship avoid the raster. Through the method and the system for planning the paths of the marine unmanned ships, the collaborative path planning for multiple unmanned ships is achieved; the comprehensive cruising of the sea area is achieved; meanwhile, the situation that the paths are coincident is avoided.

The invention provides a box type solar unmanned aerial vehicle which comprises an unmanned aerial vehicle body, box type wings, composite type vertical fins, a ducted fan assembly, rotor assemblies,an undercarriage and solar panels. The unmanned aerial vehicle adopts a box type wing layout, the laying area of the solar panels is increased, and meanwhile, the cruising aerodynamic efficiency of the solar unmanned aerial vehicle is improved; the mode that a ducted fan and tilting rotors are combined is adopted, so that it is guaranteed that the solar unmanned aerial vehicle has the vertical take-off and landing performance and the cruising performance; and the mode of the composite type vertical fins is adopted, so that the stability and controllability of the solar unmanned aerial vehicleare guaranteed, and meanwhile, the influence on the wing aerodynamic efficiency of the solar unmanned aerial vehicle by tilting rotor wake flows in the cruising process is reduced.

The invention provides a laminar flow aerofoil profile FNLF1 with maximum relative thickness of 0.17 and with an emphasis on stall characteristic by using a computer fluid dynamics method and an aerofoil profile parameterization method and taking a cruising point, a climbing point and a stalling point into consideration in state design on the basis of the internally public NLF0416 aerofoil profile. The leading edge radius of the laminar flow aerofoil profile FNLF1 is 2.11% of C, the maximum thickness of the laminar flow aerofoil profile FNLF1 is 17% of C, the maximum thickness position of the laminar flow aerofoil profile FNLF1 is 5.37% of C, the maximum camber of the laminar flow aerofoil profile FNLF1 is 1.88% of C, the maximum camber position of the laminar flow aerofoil profile FNLF1 is 76.29% of C and the trailing edge thickness of the laminar flow aerofoil profile FNLF1 is 0.43% of C, wherein C is the chord length of the aerofoil profile. In the case that the climbing and cruising performances of the laminar flow aerofoil profile FNLF1 are kept at or slightly superior to those of the NLF0416, the stalling angle of attack of the laminar flow aerofoil profile FNLF1 is delayed and the stall characteristic of the laminar flow aerofoil profile FNLF1 is slowed; and in case that the cruising state is the laminar flow main control, the length of an upper wing surface laminar flow area reaches 48% and the length of an lower wing surface laminar flow area reaches 53%.

The invention relates to a fire-fighting reconnaissance robot path generating method and device, computer equipment and a storage medium. The method comprises the steps that the front path is detectedthrough an ultrasonic radar on the front side of a chassis, information of a barrier in front of the fire-fighting reconnaissance robot is obtained, if the information of the barrier in front of thefire-fighting reconnaissance robot meets a steering triggering model, the steering state of the fire-fighting reconnaissance robot is triggered, in the steering state, left barrier information detected by an ultrasonic radar on the left side of the chassis and right barrier information detected by an ultrasonic radar on the right side of the chassis are received, the turning direction of the fire-fighting reconnaissance robot is determined according to the left barrier information and the right barrier information, and a turning path of the fire-fighting reconnaissance robot is generated according to the turning direction. By adopting the method, the robot can effectively avoid the barriers on the advancing path, and the cruising efficiency of the fire-fighting reconnaissance robot in thefire scene environment is improved.

The invention provides an illegal emergency lane occupation detection method and system based on an unmanned aerial vehicle; firstly, the unmanned aerial vehicle cruises according to a pre-configured target route, and does not need to be controlled by professionally trained personnel; secondly, when the target vehicle occupies the emergency lane, illegal video images can be sent to the control equipment, and the traffic police do not need to observe at any time, so that the efficiency of the traffic police can be improved, for example, one traffic police can process the video images fed back by multiple unmanned aerial vehicles at the same time and confirm the illegal emergency lane occupation behavior; thirdly, the different camera shooting parameters are adopted during cruising and license plate information recognition, it can be ensured that the unmanned aerial vehicle has a large shooting view during cruising, the cruising efficiency is improved, and when it is found that the target vehicle exists, the information of the target vehicle can be clearer by adjusting the camera parameters, and evidence obtaining is facilitated.

The invention relates to a gravity-center-adjustable composite propulsion unmanned aerial vehicle and the control method thereof, two power machine arms of the unmanned aerial vehicle are hinged to a comprehensive bearing vehicle body in parallel through four cross beams, and rotary joints rotate to drive the machine arms to move forwards and backwards, so that gravity center adjustment of the unmanned aerial vehicle is achieved; the unmanned aerial vehicle adopts a lift rotor wing and a propulsion rotor wing for composite propulsion; the left propulsion rotor and the right propulsion rotor oppositely rotate to counteract the reverse torsion moment, differential rotation provides course control moment when the unmanned aerial vehicle cruises, the self-adaptive lift rotor flies at a positive attack angle, and the attack angle of the unmanned aerial vehicle is adjusted through gravity center adjustment and lift rotor attitude control, so that the flight attack angle of the lift rotor is adjusted. The unmanned aerial vehicle automatically adjusts the attack angle at different airspeeds.

The invention belongs to a technology of airplane design and relates to an overall arrangement of a large air freighter. The overall arrangement of the large air freighter comprises a fuselage (1), a cockpit (2), wings (3), a retractable nose-wheel landing gear (4), an upturning cargo bay front door (5), an upturning cargo bay rear door (6), and two propulsion devices which are arranged at the rear part of the wings and at the two sides of the fuselage, wherein each propulsion device consists of an engine mounting plate (7) and a power mechanism, wherein each engine mounting plate (7) is provided with a power mechanism mounting hole, and each power mechanism is arranged in the corresponding power mechanism mounting hole; each power mechanism consists of a pitching guide ring (8), a yaw guide ring (9), a propfan engine (10), a pitching rotating shaft (11), a yaw rotating shaft (12) and a support rod (17). By adoption of the overall arrangement of the large air freighter, the cruise efficiency, the structural efficiency and the loading efficiency of the air freighter can be improved, the oil consumption rate is reduced, the empty weight coefficient is reduced, and the fuel load and the flying range are improved.

The invention belongs to the technical field of aviation aircraft design, and discloses a flying wing layout wide-speed-range aerodynamic operation stability characteristic structure, a wing body and flying wing layout integrated aircraft body, double wings of the aircraft body adopt double sweepback layout, the wings are divided into inner wing sections and outer wing sections, the inner wing sections are wing sections fused with the aircraft body, and the sweepback angles of the front edges of the inner wing sections are large; the sweepback angle of the front edge of the outer wing section is small; the outer wing section is further divided into an outer wing section fixing section and an outer wing section foldable section, the outer wing section fixing section is fixedly connected with the inner wing section, the outer wing section foldable section is in shaft driving connection with the outer wing section fixing section through an outer wing section rotating shaft, and the outer wing section foldable section rotates relative to the outer wing section rotating shaft so as to be folded upwards. When the structure is applied, different aerodynamic and operation stability performance requirements of low-speed take-off and landing, high subsonic speed cruise and supersonic speed cruise design points can be considered.

The invention provides a rudder control type vertical take-off and landing unmanned aerial vehicle and a take-off and landing control method thereof. Symmetric horizontal tails, upper vertical tails,lower vertical tails and take-off and landing supporting rods are arranged at the slender tail of a rudder control type vertical take-off and landing unmanned aerial vehicle body; a pair of fixed mainpower propellers, a pair of auxiliary power propellers and corresponding independent motors are installed on the root portion and the wing tip of the rear edge of the main wing respectively. The rudder control type fixed wing vertical take-off and landing technology is adopted, the unmanned aerial vehicle can take off vertically and cruise horizontally through the fixed wings, the take-off and landing device is simple in structure, the flight mode conversion mode is convenient, and complex tilting mechanisms of existing other forms of vertical take-off and landing aircrafts or power devices which are not fully utilized are removed. The operation is flexible, and the flight mode conversion cost is low. By utilizing the wake flow and the full-motion horizontal tail of the main propulsion ducted propeller, the horizontal tail is deflected after the aircraft vertically rises to a certain height, so that the aircraft is smoothly transited to a horizontal cruise state.

The invention discloses a ball-borne suspended launching system based on a combined unmanned aerial vehicle, the ball-borne suspended launching system comprises the combined unmanned aerial vehicle provided with a flight control system; a high-altitude balloon connected with the combined unmanned aerial vehicle through a rope; and a rope cutter fixed to the back of the combined unmanned aerial vehicle, wherein the rope is connected to the rope cutter; the combined unmanned aerial vehicle rises to a preset height through buoyancy of the high-altitude balloon and then enters a cruising state. When the balloon and the combined unmanned aerial vehicle lift off to a preset height, the rope cutter is remotely controlled to cut off the rope to separate the balloon from the unmanned aerial vehicle, so that the throwing of the combined unmanned aerial vehicle is completed, and the energy consumed by the common combined unmanned aerial vehicle during ground skating or catapult-assisted take-offis saved.

The invention discloses a variant wing vertical takeoff and landing unmanned aerial vehicle. The variant wing vertical takeoff and landing unmanned aerial vehicle comprises an unmanned aerial vehiclebody and a plurality of power assemblies installed on the unmanned aerial vehicle body; the unmanned aerial vehicle off and landing can be optimized. le body includes wings, the power assemblies are used for generating thrust or pull in the longitudinal direction of the unmanned aerial vehicle body, and the power assemblies are arranged in the transverse direction of the unmanned aerial vehicle body; in the transverse direction of the unmanned aerial vehicle body, the unmanned aerial vehicle body is formed by connecting a plurality of subsections in series, and any two adjacent subsections canbe overturned oppositely, and the directions of an overturned shaft is that one end is towards the front end of the unmanned aerial vehicle body, the other end is towards the rear end of the unmannedaerial vehicle body; and the number of power assemblies is at least three, and the power assemblies are distributed in different subsections. According to the unmanned aerial vehicle, the problem ofmaneuverability of unmanned aerial vehicle taking off and landing can be solved, and stability and control performance of the unmanned aerial vehicle in the process of taking off and landing.

The invention discloses a vertical / short-distance take-off and landing aircraft with distributed power coupling lift augmentation airfoils, and belongs to the field of aviation aircrafts. The aircraft comprises lift fans, an aircraft body, wings, high lift airfoils, distributed ducted fans and a motion mechanism, wherein the fuselage and the wings are in a flying wing layout with a fused wing body; the lift fan is embedded in the middle of the nose, is in a coaxial contra-rotating form and is used for generating a vertical upward lifting force; the distributed ducted fans are symmetrically distributed at the tail of the fuselage, and the side walls of the two ends of each distributed ducted fan are hinged to side plates fixed to the fuselage through rotating shafts correspondingly. The high-lift airfoil comprises an upper straight wing and a lower straight wing which are arranged in parallel and located at the upper end and the lower end of the outer side of an outlet of the distributed ducted fan respectively, and the two ends of each straight wing are connected with the side plates through movement mechanisms respectively and can tilt relative to the fuselage along the movement mechanisms. Hovering, vertical / short-distance taking-off and landing and cruising level flight of the aircraft in the air can be achieved, and due to the fact that lift force is provided in a lift augmentation airfoil mode, the aircraft can fly more safely and stably in a transition mode.

The invention discloses a trapezoid layout tandem tilt wing aircraft and a tilting mechanism thereof. Tandem wing layout, trapezoidal power system arrangement, multiple control surfaces and electric power system differential combination control are adopted, so the aircraft integrates vertical takeoff and landing functions and high-speed hover performance advantages, and also has the long-enduranceand long-range characteristics of a fixed wing aircraft and the hovering and vertical takeoff and landing characteristics of a helicopter. The vertical takeoff and landing and the air fixed wing modecruising are completed through the tilting wing layout, so the requirements for a taking off and landing place are reduced, and the cruising efficiency is improved; the trapezoid dynamic system layout can improve the efficiency of propellers; the roots of wings and a fuselage are fused, and the tilting sections of the wings and the fuselage section fused wing roots are connected and rotate relative to each other, so the mounting and positioning precision of the wings is improved; and the multi-control surface layout of the wings makes the control surfaces on the wings generate the rudder effect by using rotor wake during the vertical takeoff and landing, and attitude control participating in the vertical take-off and landing state reduces the control surfaces of a vertical fin, so the structural efficiency is improved.

The invention relates to a tilt rotor aircraft adopting parallel coaxial dual rotors, which comprises a fuselage, wings, an empennage, a pitch control scull system, a landing gear, a power and fuel system, a transmission system, a rotor system, a rotor nacelle and a tilt system, wherein the wings are arranged at the center section of the fuselage; the empennage and the pitch control scull system are arranged at the tail of the fuselage; the landing gear is positioned at the belly of the fuselage; the power and fuel system is arranged inside the center section of the fuselage and is connected with the rotor system and the pitch control scull system through the wings and the transmission system in the fuselage; the rotor system is arranged on the rotor nacelle at the tip of the wings; partial wing which is fixedly connected with the rotor nacelle and simultaneously can tilt is arranged at the inner side of the rotor nacelle; and the tilt system is arranged in the wings and is connected with the rotor nacelle and the partial wing which can tilt. The tilt rotor aircraft is mainly characterized by adopting the pitch control scull system, the parallel coaxial dual rotors and the partialwing which can tilt to realize flight status transformation and conventional taxiing and landing, thereby improving the forward speed and the propulsive efficiency.