43results about How to "Increase the voyage" patented technology

The invention provides a multi-cavity scramjet engine combustion chamber and a control method thereof. The combustion chamber is simple in structure, capable of adapting to different equivalence ratio ranges and different flight heights, low in resistance, high in combustion performance, low in thermal load of the wall face of the combustion chamber, convenient to maintain and capable of facilitating aircraft-engine integrated design. The combustion chamber comprises an isolation section, a first concave cavity group, a second concave cavity group, a third concave cavity group, an injection module and a combustion chamber expansion section, each concave cavity group is provided with two concave cavities which are oppositely arranged up and down; the isolation section is a first square tube and is connected with the first concave cavity group; the first concave cavity group is connected with the second group of concave cavities through a second square tube; the second group of concave cavities is connected with a third concave cavity group through a third square pipe; a combustion chamber expansion section is connected behind the third concave cavity group; the injection unit comprises a front injection device and a rear injection device; front injection devices are oppositely arranged on the upper wall surface and the lower wall surface of the second square pipe; rear injection devices are oppositely arranged on the upper and lower wall surfaces of the third square pipe.

According to the modularized traffic tool with multiple take-off modes, through the innovative split modularized design, the form of the traffic tool can be flexibly changed between an automobile and an aircraft, the flight state and the land running state are switched, and more novel passenger and freight application scenes can be expanded through cooperation of the independent carrying cabin modules. By utilizing the tiltable ducted fan mechanism and by virtue of boosting of the autonomous traveling chassis, the composite wing flight module can realize vertical take-off and landing, and wing lift force can be provided for short-distance taxiing take-off and landing to reduce energy consumption, so that the purposes of large voyage and high load are finally realized. The foldable fixed wing, the horizontal tail and the telescopic tail wing structure ensure that the traffic tool is small in size when running and parking on the land, so that the requirements of existing urban and rural roads and traffic safety laws and regulations can be met, and actual popularization is more facilitated.

The invention relates to a variable-pitch lift wing for a vertical take-off and landing level flight cruise aircraft, and belongs to the technical field of vertical take-off and landing aircraft wings, the variable-pitch lift wing comprises an aircraft body, a left wing and a right wing are symmetrically arranged on the left side and the right side of the middle of the aircraft body, and the left wing and the right wing are designed according to the shape of a conventional lift wing; the left wing and the right wing are connected in the mode that a variable-pitch shaft penetrates through the aircraft body, a left positioning bearing and a right positioning bearing are fixedly arranged on the two sides, in the aircraft body, of the variable-pitch shaft respectively, a sector gear is arranged in the middle of the variable-pitch shaft, a worm is arranged at the tooth end of the sector gear, and a worm gear is arranged at the tooth end of the worm. A positive and negative rotation servo motor is arranged at one end of the worm to provide power, the servo motor is fixed in the machine body, the worm is used for driving the sector gear to rotate, and the sector gear rotates to drive the left wing and the right wing to rotate synchronously through the variable pitch shaft. The incidence angle of the wing can be changed through forward and reverse rotation of the servo motor.

The invention provides a nano smooth surface treatment method and system suitable for aircraft drag reduction. The nano smooth surface treatment method comprises the steps that sand blasting treatment is conducted on an operation part of the surface; the operation part is divided into strips; determining a scanning path according to the strip; determining the laser power, the scanning rate and the defocusing amount according to the strip and the target roughness, and formulating a laser strategy; polishing according to a laser strategy; and cleaning the polished surface. According to the method, a nano finish treatment method is adopted, the aerodynamic resistance of the high-speed flying aircraft is reduced under the condition that the structure is not changed, the technological operation is simple and feasible, the surface friction resistance of the high-speed aircraft is reduced by 40% or above under the condition that no attack angle exists, and the effects of increasing the voyage and reducing aerodynamic heat are achieved.

The invention discloses a distributed power fixed-point take-off and landing portable solar unmanned aerial vehicle, and belongs to the technical field of overall comprehensive design of unmanned aerial vehicles. Comprising a front wing, a rear wing and a folding assembly, the front wing and the rear wing are arranged in a tandem wing mode, the folding assembly is connected between the front wing and the rear wing, the front edge of the front wing and the front edge of the rear wing are each provided with a plurality of rotors in the spanwise direction, and the four rotors located in the spanwise middle of the front wing and the spanwise middle of the rear wing are located at the four vertexes of a quadrangle respectively to form the four-rotor power system of the unmanned aerial vehicle. The other rotor wings form a fixed wing power system of the unmanned aerial vehicle; the front wing and the rear wing are connected into a tandem wing with a space height difference through the folding assembly, and the front wing and the rear wing can be in a stacked state through deformation. The problems that a single-type propeller of a tailstock type configuration machine consumes much energy, the efficiency of the cruising stage is low, and the endurance is short are solved.

The invention discloses a tilting type electric vertical take-off and landing aircraft with foldable airfoils and an operation method. Comprising a fuselage, a fixed section wing arranged on the fuselage, a folding section wing connected to the fixed section wing through a wing folding assembly, a vertical fin arranged at the tail of the fuselage, a fixed section horizontal tail arranged on the vertical fin and a folding section horizontal tail connected to the fixed section horizontal tail through a horizontal tail folding assembly. The conversion of the aircraft among a folding mode, a helicopter mode and a fixed-wing aircraft mode can be realized under the action of the wing folding assembly and the horizontal tail folding assembly, a front-end rotor wing is arranged on the fixed-section wing, a middle-end rotor wing is arranged on the folding-section wing, and a rear-end rotor wing is arranged on the folding-section horizontal tail. When the aircraft is parked on the ground, the folding section wings and the folding section horizontal tail can be folded, so that the parking space needed by the aircraft is reduced, the requirement for special infrastructures is lowered, the cost is saved, the aircraft can be more easily integrated into the current limited space of a city, and the operation flexibility is enhanced.

The invention discloses an underwater glider, and belongs to the field of underwater robots. According to an existing underwater glider, the trim angle of the existing underwater glider needs to be adjusted through a configured posture adjusting device to obtain forward thrust, so that the carrying capacity of the underwater glider is weakened, and meanwhile posture adjustment is subjected to the nonlinear coupling effect of hull dynamics and fluid dynamics; the change of the attitude of the underwater glider has strong unpredictability and hysteresis, and a great challenge is brought to accurate control of the gliding speed of the underwater glider and the like. The underwater glider comprises a main boat body, a floating and sinking adjusting mechanism and two wing plates, the two wing plates are symmetrically arranged on the two sides of the main boat body, the floating and sinking adjusting mechanism is installed in the main boat body and used for controlling floating or sinking of the underwater glider, the underwater glider further comprises two wing plate posture adjusting units symmetrically installed in the main boat body, and each wing plate posture adjusting unit is connected with one wing plate. And the attack angle and / or the sweepback angle of the wing plate can be adjusted when the underwater glider dives, so that the multi-attitude movement of the underwater glider is realized.

The present invention relates to a ground-following wireless charging system for an electric-propulsion aircraft, comprising a ground subsystem, wherein the ground subsystem comprises a plurality of ground-following charging devices, wherein the ground-following charging devices comprise: a main control module, which is used for the running control of the device, for the state management of charging and power supply, for the state analysis of aircraft following, and for the control of sending and receiving information, and the modules connected to the main control module comprise: a first wireless communication module, an aircraft following module, a charging management module, and a mobile control module. According to the present invention, when the electric-propulsion aircraft has not taken off the ground, the ground-following charging device automatically follows the electric-propulsion aircraft, charges and supplies power to the electric-propulsion aircraft in time, thereby avoiding or reducing the consumption of electric energy in the onboard energy storage device by the electric-propulsion aircraft during the ground stage, and the onboard energy storage device can be put into operation after the electric-propulsion aircraft takes off the ground, thereby effectively extending the range and flight time of the electric-propulsion aircraft.

This disclosure relates to a fuselage shell of a drone and the drone itself. The fuselage shell includes a housing for enclosing a space for accommodating internal components of the drone. The housing includes a bottom wall and a front end wall, a transition wall, and a main body wall sequentially disposed on the bottom wall from front to back along the drone's longitudinal direction. The orthographic projection area of ​​the front end wall along the longitudinal direction is a first projection area. The orthographic projection area of ​​the area enclosed by a first connecting line at the junction of the transition wall and the main body wall and the bottom wall along the longitudinal direction is a second projection area. The first projection area is completely located within the second projection area. The transition wall is a continuous, smooth curved surface extending rearward from the front end wall. This technical solution optimizes the shape of the housing, making it more rounded, suitable for guiding airflow during flight, reducing fuselage drag, and increasing the drone's range.

The invention discloses an aircraft connecting assembly and an aircraft, and relates to the technical field of aircrafts, the aircraft connecting assembly comprises a fixing shell, the fixing shell is connected with a pair of connecting rods, one side of each connecting rod is slidably connected with an inserting block, the bottom end of each connecting rod is provided with an inserting groove, and one connecting rod is internally and rotatably connected with a wind shielding cloth roll; the aircraft connecting assembly comprises a fixing shell, two pairs of connecting rods are slidably connected to the fixing shell, the connecting rods are slidably connected to a fixing frame through sliding grooves, a supporting rod is slidably connected to the fixing shell, a sliding block is slidably connected to the supporting rod, and a pull rod is rotatably connected between the sliding block and the fixing frame. The sliding block pushes the fixing frame through the pull rod, so that the two pairs of connecting rods rotate oppositely and are aligned and closed together, the two pairs of connecting rods are pulled to be slowly retracted into the two fixing shells through rotation of the lead screw, fixation is firm, looseness is not likely to happen, the wind blocking cloth roll is pulled out and unfolded during landing, and therefore wind resistance is increased and the sliding distance is reduced during landing of the unmanned aerial vehicle.

The invention discloses a flexible webbed wing structure capable of improving dynamic characteristics, which comprises a body, an isosceles trapezoid of the cross section of the body is called as a cross section trapezoid, and the bottom edge of the cross section trapezoid is longer than the top edge of the cross section trapezoid; the included angle of the two side edges of the section trapezoid is called as the taper angle, the height of the section trapezoid is called as the height of the flexible webbed wing, the surface hardness of the body is 60 HB, the taper angle is 4.7-5.2 degrees, the top edge is 2 mm, the bottom edge is 5 mm, and the height of the flexible webbed wing is 110 mm. The body is made of SBR rubber. Optimized object parameters of the dynamic characteristics of the flexible webbed wing are determined, a geometric model of the flexible webbed wing and a fluid-solid coupling 2.5 D model of the flexible webbed wing are established, numerical simulation is carried out on the dynamic characteristics of the flexible webbed wing by using an ANSYS Workbench simulation platform, and finally a relative optimal result of each optimized object parameter is obtained. The flexible webbed wing prepared according to the invention can improve the energy conversion efficiency of the wave glider and increase the voyage and speed of the wave glider; the maneuverability and controllability of the wave glider can be enhanced, the environmental adaptability of the wave glider is enhanced, the comprehensive performance of the wave glider is improved, the performance of the flexible web wing of the wave glider is remarkably improved, the application range of the flexible web wing of the wave glider is remarkably widened, and powerful technical support is provided for development of ocean science and technology and effective utilization of ocean resources.

The invention relates to a corrugated wall surface airfoil profile and a design method thereof, which are applied to an unmanned aerial vehicle, and are characterized in that a corrugated wall surface is arranged in a chordwise region of the upper surface of the airfoil profile, and the corrugated wall surface is used for inducing a boundary layer of the upper surface of the airfoil profile to transition in advance and inhibiting generation of laminar flow separation bubbles; the corrugated wall surface is of a sine function corrugated structure, and the sine curve of the corrugated wall surface meets the following formula. According to the invention, the sine wave pattern-shaped wall surface structure with specific geometric parameters is arranged in the chordwise middle rear area of the upper surface of the wing profile, so that local pressure distribution of the surface of the wing profile is changed, a boundary layer is induced to transit in advance, generation of laminar separation bubbles is inhibited, wall surface friction resistance and differential pressure resistance are reduced, and the stability of the wing profile is improved. The problem that the low-altitude low-speed unmanned aerial vehicle wing type drag reduction effect is limited is solved.

The application discloses a wing surface continuous deformation mechanism based on a slide bar-flexible truss-skin, which comprises a rigid wing box (40% of the terminal chord length), a flexible upper skin, four independent flexible trusses, a slide bar and a rigid trailing edge. The trusses are connected with the upper skin together, and the whole driving system serves as the lower skin of the wing. The slide bar slides back and forth at the leading edge of the wing, the deformation mechanism is stretched or bent, and the curved surface of the wing is changed. The upper surface skin of the wing is made of a skin prepared from a material capable of bearing large deformation. The motor drives the slide bar to generate a driving force, when the driving force is applied to the leading edge direction, the trailing edge deflects downward, and when the driving force is applied to the trailing edge direction, the trailing edge deflects upward, so that the deformation is completed.

The utility model belongs to the technical field of shape design and control of aircrafts, and relates to an electric tilt-rotor aircraft. Comprising a fuselage, two wings located on the two sides of the fuselage, an empennage, a plurality of supporting rods arranged below the wings and rotors arranged at the two ends of the supporting rods. The rotor wings comprise a plurality of tilting rotor wings and a plurality of fixed rotor wings; the number of the supporting rods is even, and the supporting rods are divided into two sets with the same number and are symmetrically arranged on the two sides of the machine body. A tilting rotor wing is arranged at the front end of each supporting rod; a fixed rotor wing is arranged at the rear end of each supporting rod; the tilting rotor wings are connected with the front ends of the supporting rods through tilting mechanisms, and the tilting mechanisms are used for adjusting the orientation of the tilting rotor wings. The electric tilting rotor aircraft provided by the utility model can realize the functions of vertical take-off and landing, tilting transition and cruise flight.

The invention discloses a yacht oil-electricity hybrid power system which comprises a yacht propelling module, a motor, a diesel engine, a power generation module, a battery module and an electric control module. The diesel engine is used for combusting diesel oil to generate heat energy, converting the heat energy into mechanical energy and transmitting the mechanical energy to the motor; the motor is connected with the yacht propelling module and drives the yacht propelling module to operate, meanwhile, part of mechanical energy is recycled and converted into electric energy to be stored in the battery module, and the battery module and the power generation module are both connected with the motor through the electric control module for power supply and used for storing the electric energy. The power generation module is further connected with the battery module and stores electric energy to the battery module.

The invention discloses a variable rotor duct system and a tilt rotor aircraft, and relates to the technical field of aircrafts, the variable rotor duct system comprises a transmission shaft, a rotor assembly and a duct assembly; the transmission shaft is in transmission connection with an aircraft body; the rotor assemblies are connected to the transmission shaft; the duct assembly comprises a deformation shell and a first driving mechanism, the first driving mechanism is connected to the transmission shaft, and the deformation shell is arranged outside the rotor wing assembly in a surrounding mode in the circumferential direction; the first driving mechanism is in transmission connection with the deformation shell, the first driving mechanism can drive the deformation shell to circumferentially expand in the direction away from the transmission shaft so as to form a duct configuration, and the first driving mechanism can further drive the deformation shell to circumferentially contract in the direction close to the transmission shaft so as to form a fairing configuration. According to the variable rotor duct system and the tilt rotor aircraft provided by the invention, the rotor duct system gives consideration to high hovering efficiency and low forward flight resistance, and the overall aerodynamic efficiency and engineering application value of the tilt rotor aircraft are improved.

The invention discloses an intelligent power generation and energy storage system which comprises a solar cell panel, an inverse control all-in-one machine, an energy storage battery, a direct-current generator, a combiner box and a load. The inverse control all-in-one machine is used for controlling power generation of the flexible solar cell panel and the direct-current generator, and inverting direct current provided by the solar cell panel, the direct-current generator and the energy storage battery into alternating current to be provided for a load for use; the solar cell panel and the direct-current generator are used for providing a direct-current power supply; and the energy storage battery is used for storing a direct-current power supply provided by the solar cell panel and the direct-current generator. The combiner box is used for centralized management of electric energy, and a load takes electricity for use through the combiner box. According to the product provided by the invention, renewable energy sources of the solar cell panel and high-capacity energy storage of the energy storage battery with the BMS are utilized, so that a load such as a yacht and the like can meet the requirement for shore power during sailing within a period of time, meanwhile, consumption of a large amount of diesel oil resources caused by a traditional oil engine power supply mode is reduced, the voyage is prolonged, and power utilization is safe.

The application discloses a kind of modular display platform and display system based on ocean exploration unmanned ship, including surface boat, the bottom end of surface boat is fixedly installed with umbilical cable, the bottom end of umbilical cable is fixedly installed with hydrodynamic glider, the bottom end of hydrodynamic glider is fixedly installed with winch, the inside of winch is wound and is connected with the temperature-salinity-depth detection cable extending to outside, the middle of the top of surface boat is fixedly installed with weather station, Beidou terminal, AIS receiver and near field communicator, the device of the application uses artificial intelligence autonomous navigation control, new energy, satellite communication, ocean big data technology, uses small low-power unmanned surveying ship, saves a lot of funds, reduces personnel injury risk, and combines solar energy, wind energy, energy storage battery new energy technology, expands voyage, lengthens operation time, is not restricted by insufficient logistical support capability, can obtain good economic benefit and military effectiveness.

The present invention discloses a segmented modular underwater robot, comprising a propulsion section, a pitch adjustment section, a buoyancy adjustment section, a fixed battery pack section and an observation section connected in sequence; the propulsion section comprises a propulsion frame, a propeller, a motor drive unit, an elevator and a rudder; the pitch adjustment section comprises a pitch compartment shell and a mobile battery pack arranged inside the same, a pitch support assembly and a driving device; the buoyancy adjustment section comprises a buoyancy shell, an outer oil bladder and a piston-type inner oil bladder, the outer oil bladder is arranged around the outer wall of the shell, the inner oil bladder is arranged in the inner cavity of the shell and the outer wall is sealed and slidably connected with the inner cavity wall of the shell; the outer oil bladder is connected with the inner oil bladder through an adjustment system and adjusts the oil amount in the outer oil bladder and the inner oil bladder; the fixed battery pack section comprises a fixed battery pack section shell and a fixed battery pack and a support pipe arranged inside the fixed battery pack section. The present invention can solve the technical problems of the existing underwater robots with short range, short self-sustaining time and lack of autonomous heave capability.

The three-duct tilting electric vertical take-off and landing aircraft comprises an aircraft body, the aircraft body adopts a streamline design, and an integrated electric ducted fan fused with the aircraft body is arranged at the rear part of the aircraft body; a duct sealing device is arranged at an inlet and an outlet of the integrated electric ducted fan; left and right wings are arranged on two sides of the fuselage, and left and right tilting electric ducted fans are respectively mounted in the middles of the left and right wings; the three electric ducted fans are arranged in a triangular space; a horizontal tail and a vertical tail are arranged at the tail part of the fuselage, and the horizontal tail and the vertical tail are arranged by adopting an integrated cross-shaped empennage; wing control surfaces are arranged on the rear edges of the left and right wings, a horizontal tail control surface is arranged on the rear edge of the horizontal tail, and a vertical tail control surface is arranged on the rear edge of the vertical tail. The aircraft adopts a combined layout of double tilting ducts and a single fixed fusion duct, so that high stability of vertical take-off and landing, moment self-balance in a transition stage and high aerodynamic efficiency in a cruise stage are realized.

The invention provides a flight method of an aircraft and an aircraft system. Flight of the aircraft comprises a take-off phase from the ground to the air, a cruise phase flying in the air and a landing phase from the air to the ground. The flight method comprises the following steps: at a take-off stage of the aircraft, providing at least a part of power / lift force for flight by the take-off auxiliary device; and in the cruising stage of the aircraft, only a power system of the aircraft provides flight power. Through the take-off auxiliary device, at least part of power / lift force can be provided for the aircraft in the take-off stage of the aircraft, and therefore energy consumption of a power system of the aircraft can be reduced.

The utility model provides a foldable trailing edge flying wing unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the foldable trailing edge flying wing unmanned aerial vehicle comprises a main wing, the main wing comprises a main wing inner section and a main wing outer section, the wingtip of the main wing outer section is connected with a small wing, and the trailing edge of the main wing outer section is connected with a connecting wing and an empennage; the winglet is connected with the connecting wing through a driving rotating shaft, the connecting wing is connected with the empennage through a driven hinge, and the empennage is connected with the main wing inner section through a driven hinge; and the front parts of the connecting wing and the empennage are connected with the main wing outer section through a locking structure. When the multi-wing unmanned aerial vehicle is used for executing complex maneuvering actions such as emergency avoidance, large-attack-angle climbing and small-radius turning, the winglet, the connecting wing and the empennage are folded under the driving of the wingtip driving rotating shaft, so that a connecting wing layout is formed. The wing surfaces are converted into a three-dimensional structure from the same plane, so that an additional stabilizing plane is added for the flying wing unmanned aerial vehicle, and meanwhile, additional torque is provided for the unmanned aerial vehicle to execute complex maneuvering actions.

The present invention discloses an automatic hanging and removing wiring device for unmanned aerial vehicles with electric field detection capability, comprising a shell, a clamping plate rotatably connected inside the shell, an elastic telescopic rod installed inside the shell, an elastic clamping block installed inside the clamping plate, a connecting rod rotatably connected to the back end of the clamping plate, and a pull rod rotatably connected to the end of the connecting rod. The present invention provides a pull ring, an electric field detector, a controller and an extension mechanism. When the high-voltage cable is affected by wind direction or air humidity, resulting in an increase in the electromagnetic field strength around the cable, the electric field detector can change the electromagnetic field strength to avoid the unmanned aerial vehicle being too close to the high-voltage cable when disassembling the wiring device, thereby preventing the unmanned aerial vehicle from being affected by the electromagnetic field. By timely adjusting the distance between the pull ring and the shell, it can be ensured that the unmanned aerial vehicle maintains a safe distance when disassembling the wiring device, avoiding the influence of the electromagnetic field on the electronic equipment inside the unmanned aerial vehicle, thereby protecting the unmanned aerial vehicle from damage.

The invention relates to the technical field of aviation aircraft design, and discloses a variable camber wing based on a bistable composite material structure driving multi-section rotation, which comprises a wing leading edge structure, a multi-section rotation rigid skin, an internal truss structure connected with the multi-section rotation rigid skin, a bistable composite material driving structure and a transmission mechanism, the bistable composite material driving structure is arranged between the rigid skin hinge and the transmission mechanism; and the transmission mechanism is arranged between the truss structure in the rigid skin and the sliding chute of the wing leading edge structure. The control precision and reliability are improved through relative change of the three rigid wings, and the problems that in the prior art, the structure is complex, the weight is large, the actuation efficiency is low, and the bearing capacity is low are solved.

The invention belongs to the technical field of underwater vehicle control, and particularly relates to a vertical plane navigation attitude control method for a variable-mass underwater vehicle, which can effectively maintain a depth control attitude, reduce energy consumption and improve a voyage, and is beneficial to exerting the optimal maneuvering performance and maneuvering performance of the underwater vehicle. Aiming at the problems of increased navigation resistance, increased energy consumption, increased depth control error and shortened voyage caused by changes of a navigation pitch angle and a rudder angle due to factors such as fuel consumption, cross-sea-area seawater temperature, salinity change and large-range depth change of an underwater vehicle, the invention can effectively maintain a depth control attitude, reduce energy consumption and improve voyage, and has the advantages of simple structure, low cost and high efficiency. And the optimal maneuvering performance and maneuvering performance of the underwater vehicle can be developed. By combining a buoyancy balance control strategy with navigation control, a depth control attitude is kept, so that the energy consumption of vertical plane navigation control is remarkably reduced, the control precision is remarkably improved, and the optimal maneuverability and maneuverability of the underwater vehicle are favorably exerted.

The present invention provides a robot system and a control method for water diversion tunnel detection, which relate to the field of heterogeneous robots and include a surface robot and an underwater robot. The underwater robot is connected to the surface robot via a cable, the underwater robot includes an underwater communication component, the surface robot includes a tracking component and a surface communication component, and the underwater communication component establishes hydroacoustic communication and network communication with the surface communication component. In view of the problems that it is difficult to achieve remote control and wired transmission is inconvenient to establish water diversion tunnel survey at present, a heterogeneous robot system in which the surface robot and the underwater robot work in coordination is established, the linear trajectory movement of the surface robot is used to cooperate to obtain the position in the tunnel, and relative position positioning and data transmission are achieved through hydroacoustic communication and network communication, thereby ensuring the correspondence between the detection data in the water diversion tunnel and the detection position, and effectively realizing the survey in the water diversion tunnel.

The present application relates to the field of aircraft flight mechanics and flight control, and particularly relates to a distributed overdrive tilting wing aircraft control strategy analysis method, comprising the following steps: step one: determining a rudder distribution scheme; the rudder distribution scheme is determined based on a minimum control energy fusion method; the control of multiple aerodynamic rudders is always linked without considering the flight conditions of the aircraft; in order to fully exert the efficiency of the linkage of multiple aerodynamic rudders, the weighted minimum control energy principle is used to distribute the control input, so as to use the rudders with high authority and high efficiency as much as possible under the same control input, and as little as possible to use the rudders with low authority and low efficiency, and finally make all the rudder angles as small as possible; step two: determining a flap aileron bias scheme; step three: calculating the lift propeller speed.

The application relates to the technical field of aircraft design, and discloses a cooperative control method and system for multi-mode flight of an aircraft and the aircraft. The method comprises the following steps: S1. a cruising efficiency optimization step: in a cruising flight mode, current Mach number, an angle of attack and real-time pressure distribution data from a pressure sensor array arranged at the rear of the upper surface of a main wing of the aircraft are acquired; based on the Mach number and the angle of attack, a target pressure distribution feature under the current working condition is solved in real time through a pre-stored optimization model; the working parameters of a boundary layer management propulsion module integrated in the main wing are dynamically adjusted so that the real-time pressure distribution data approaches the target pressure distribution feature; and S2. a mode conversion cooperation step: in response to a command for conversion to a vertical take-off and landing mode, a preset cooperative conversion sequence is executed. The system-level unification of cruising aerodynamic efficiency and vertical take-off and landing flexibility significantly improves the mode conversion stability and the comprehensive efficiency of the whole task profile.

The invention relates to a vertical take-off and landing aircraft adopting special fixed wings, which belongs to the technical field of vertical take-off and landing airplanes, and comprises an aircraft body, and a set of coaxial reverse propeller power device is arranged at the front end of the aircraft body. A front upper rudder wing and a front lower rudder wing are symmetrically arranged on the front portion of the aircraft body up and down, a left wing and a right wing are symmetrically arranged on the left side and the right side of the middle of the aircraft body, a left empennage and a right empennage are arranged on the left side and the right side of the rear portion of the aircraft body, and an upper empennage and a lower empennage are arranged on the upper side and the lower side of the rear portion of the aircraft body. A left anti-lift wing is arranged in the middle of the upper portion of the left wing, a right anti-lift wing is arranged in the middle of the upper portion of the right wing, and during vertical take-off and landing, lateral thrust f2 generated when the left anti-lift wing and the right anti-lift wing synchronously open by a certain angle can counteract lateral thrust f1 generated by the left wing and the right wing, so that the aircraft can keep balanced during vertical take-off and landing.