Tilting wing multi-rotor aircraft system based on self-adaptive pneumatic optimization

Abstract

The invention discloses a tilting wing multi-rotor aircraft system based on self-adaptive pneumatic optimization, and relates to the technical field of aircrafts. A plurality of protruding wing roots are arranged on the outer wall of the aircraft body, tilting shafts are installed in the protruding wing roots through bearings, tilting rotor wings are installed at the other ends of the tilting shafts, and telescopic mechanisms are installed in the protruding wing roots. Through cooperative work of the telescopic rear wings, the magnetic coding sliding blocks, the sliding rails, the tilting rotor wings and other components, precise sliding and position feedback of the telescopic rear wings in the protruding wing roots are achieved, the telescopic rear wings meet the requirements for light weight and high strength, and in the flight mode conversion process, the telescopic rear wings can be fixed to the rear wings. The aerodynamic configuration of the wings is optimized through dynamic adjustment of the telescopic rear wings, energy loss is reduced, and autonomous switching between the vertical take-off and landing mode and the efficient level flight mode of the aircraft is achieved through the tilting rotor wings.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically to a tilting wing multirotor aircraft system based on adaptive aerodynamic optimization. Background Technology

[0002] Aircraft refer to all kinds of devices that can fly controllably within the atmosphere or outer space. Their core characteristic is that they overcome gravity by generating thrust or lift through a power system to achieve flight. Depending on the flight principle and application scenario, they can be divided into fixed-wing aircraft (which rely on the relative motion between the wings and the air to generate lift), rotorcraft (which provide lift through rotating wing surfaces), hybrid configuration aircraft (such as tiltrotor aircraft, which have both vertical take-off and landing and high-speed cruise capabilities), and special aircraft (such as drones and airships).

[0003] Traditional tiltrotor aircraft have an energy utilization rate of less than 45% during level flight. The rotor has to bear both lift and thrust, resulting in high energy consumption. Furthermore, during mode transitions, the discontinuity of lift can easily cause a loss of more than 3 meters in altitude, affecting flight stability. Summary of the Invention

[0004] The purpose of this invention is to provide a tiltrotor multi-rotor aircraft system based on adaptive aerodynamic optimization, so as to solve the problems of low energy utilization and poor flight stability of traditional tiltrotor aircraft in the prior art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a tilting wing multirotor aircraft system based on adaptive aerodynamic optimization, including an aircraft fuselage;

[0006] The outer wall of the aircraft fuselage is provided with multiple protruding wing roots. Each of the multiple protruding wing roots has a tilting shaft installed inside via bearings. Each of the other ends of the multiple tilting shafts is equipped with a tilt rotor wing. Each of the multiple protruding wing roots has a telescopic mechanism installed inside. Each of the multiple tilt rotor wings has a ventilation window at its bottom end. A wind-blocking mechanism is embedded at the bottom end of the aircraft fuselage.

[0007] The telescopic mechanism includes a telescopic rear wing, a magnetic coding slider, and a slide rail. There are two magnetic coding sliders and two slide rails. The two magnetic coding sliders are respectively installed on the outer walls of both sides of the telescopic rear wing. The two slide rails are respectively slidably installed on the opposite sides of the two magnetic coding sliders, and the opposite sides of the two slide rails are respectively installed on the inner walls of both sides protruding from the wing root.

[0008] The control system is located inside the aircraft fuselage.

[0009] Furthermore, the aircraft fuselage is equipped with a fully movable tail fin at the rear, and a rotation drive assembly is installed at the top of each of the multiple tiltrotor wings. The output end of each of the multiple rotation drive assemblies is equipped with a rotor body, and an inlet and outlet are provided at one end of each of the multiple tiltrotor wings and the protruding wing root.

[0010] Furthermore, each of the protruding wing roots has an inlet / outlet at one end, and a fuselage opening is provided at the bottom center of the aircraft fuselage.

[0011] Furthermore, the wind-blocking mechanism includes a support plate, an adjustment drive assembly, a connecting seat, a wind-blocking plate, and a hinge. The support plate is installed on the bottom inner wall of the aircraft fuselage. Two adjustment drive assemblies, connecting seats, and hinges are provided. The two adjustment drive assemblies are respectively installed on the upper part of the outer walls on both sides of the support plate via movable shafts. The two connecting seats are respectively installed on the output ends of the two adjustment drive assemblies via movable shafts. The wind-blocking plate is installed at the bottom end of the two connecting seats. The two hinges are both installed on the top upper side of the wind-blocking plate, and the other side of the bottom end of the two hinges is installed on the bottom inner wall of the aircraft fuselage.

[0012] Furthermore, the aircraft fuselage is equipped with a digital servo motor, which is connected to the tilt axis via a transmission assembly. A BeiDou-3 positioning module is installed at the top of the aircraft fuselage, and multispectral vision sensors are installed at the bottom of multiple tilt rotor wings and protruding wing roots.

[0013] Furthermore, an optical encoder is provided on the slide rail, the bottom surface of the telescopic rear wing is higher than the top surface of the tilting shaft, and the tilting shaft is made of titanium alloy material with a low coefficient of friction.

[0014] Furthermore, the rotary drive assembly is connected to the rotor body via a planetary reducer, and the rotary drive assembly is electrically connected to the control system. The all-moving tail fin is connected to the tail of the aircraft fuselage via a high-rigidity rotating shaft.

[0015] Furthermore, the adjustment drive assembly is electrically connected to the control system, and the shape of the wind baffle matches the shape of the machine body opening.

[0016] Furthermore, the digital servo motor, the BeiDou-3 positioning module, and the multispectral vision sensor are all electrically connected to the control system.

[0017] Compared with the prior art, the beneficial effects of the present invention are:

[0018] (1) This invention achieves precise sliding and position feedback of the telescopic rear wing within the protruding wing root through the coordinated work of components such as the telescopic rear wing, magnetic coding slider, slide rail and tiltrotor wing. The telescopic rear wing takes into account both lightweight and high strength requirements. During the flight mode conversion process, the dynamic adjustment of the telescopic rear wing optimizes the aerodynamic shape of the wing and reduces energy loss. The tiltrotor wing enables the autonomous conversion between the aircraft's vertical take-off and landing and efficient level flight modes.

[0019] (2) The present invention uses the coordinated work of the support plate, the adjustment drive component, the connecting seat, the wind deflector and the hinge to adjust the angle of the wind deflector that can be extended and retracted by the drive component to match the aerodynamic requirements of different flight stages. When the wind deflector is opened, its contact area with the air increases, which significantly increases air resistance and helps the aircraft decelerate efficiently. When the wind deflector is retracted, the contact area decreases sharply and the resistance is basically eliminated, allowing the aircraft to accelerate quickly and improve flight flexibility and efficiency.

[0020] (3) Through the coordinated operation of components such as the control system, digital servo, Beidou-3 positioning module and multispectral vision sensor, the control system integrates the data of digital servo, Beidou-3 positioning module and multispectral vision sensor. By processing tilt axis angle, flight position and environmental information in real time, it realizes intelligent switching of flight mode and path optimization, ensures dynamic adjustment of aerodynamic parameters and precise control of actuators, and significantly enhances the autonomy and safety of the aircraft. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0022] Figure 1 A schematic diagram of the overall structure of the level flight mode is provided for embodiments of the present invention;

[0023] Figure 2 A schematic diagram of the overall structure for vertical take-off and landing is provided for embodiments of the present invention;

[0024] Figure 3 A schematic diagram showing the connection between the tilt shaft, the protruding wing root, and the tilt wing is provided for embodiments of the present invention.

[0025] Figure 4 A structural cross-sectional view of a tilting wing is provided for an embodiment of the present invention;

[0026] Figure 5 A schematic diagram of the telescopic mechanism is provided for an embodiment of the present invention;

[0027] Figure 6 A structural flowchart of the control system is provided for embodiments of the present invention;

[0028] Figure 7 A bottom view of the overall structure for vertical take-off and landing is provided for embodiments of the present invention;

[0029] Figure 8 A schematic diagram of the wind-blocking mechanism is provided for an embodiment of the present invention.

[0030] Explanation of reference numerals in the attached figures:

[0031] 1. Aircraft fuselage; 2. Protruding wing root; 3. Tilting shaft; 4. Tilting rotor wing; 5. Telescopic mechanism; 51. Telescopic rear wing; 52. Magnetic coded slider; 53. Slide rail; 6. Wind-blocking mechanism; 61. Support plate; 62. Adjustment drive assembly; 63. Connecting seat; 64. Wind-blocking plate; 65. Hinge; 7. Control system; 8. All-moving tail fin; 9. Rotation drive assembly; 10. Rotor body; 11. Inlet / outlet; 12. Digital servo; 13. Beidou-3 positioning module; 14. Multispectral vision sensor; 15. Vent window; 16. Fuselage opening. Detailed Implementation

[0032] To enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings.

[0033] As attached Figure 1 To be continued Figure 8 As shown:

[0034] Example 1:

[0035] The present invention provides a tilting wing multirotor aircraft system based on adaptive aerodynamic optimization, including an aircraft fuselage 1;

[0036] The outer wall of the aircraft fuselage 1 has multiple protruding wing roots 2. Each of these protruding wing roots 2 has a tilting shaft 3 mounted on it via bearings. The tilting shaft 3 is made of TC4 titanium alloy and coated with a PTFE self-lubricating coating. The corrosion resistance of the titanium alloy combined with the chemical stability of PTFE allows the tilting shaft 3 to withstand harsh environments such as high temperature, high humidity, or salt spray, ensuring long-term reliability. The other end of each tilting shaft 3 is equipped with a tiltrotor wing 4. The tiltrotor wing 4 is a key structure for the aircraft to achieve multi-mode flight, and it can adjust its configuration according to flight requirements. The tilting mechanism alters the aerodynamic characteristics of the aircraft. Multiple protruding wing roots 2 are equipped with telescopic mechanisms 5, and multiple tilting rotor wings 4 are equipped with ventilation windows 15 at their bottom ends. The ventilation windows 15 are controlled by the control system 7. During vertical takeoff, the ventilation windows 15 open to prevent horizontal winds from affecting the stability of the aircraft and causing it to sway left and right. The ventilation windows 15 can also be used on the protruding wing roots 2. A wind-blocking mechanism 6 is embedded at the bottom end of the aircraft fuselage 1. The wind-blocking mechanism 6 can adjust the aerodynamic drag as needed during the flight of the aircraft to optimize the aerodynamic performance of the aircraft.

[0037] The telescopic mechanism 5 includes a telescopic rear wing 51, a magnetic coding slider 52, and a slide rail 53. There are two magnetic coding sliders 52 and two slide rails 53. The two magnetic coding sliders 52 are respectively installed on the outer walls of the two sides of the telescopic rear wing 51. The two slide rails 53 are respectively slidably installed on the opposite sides of the two magnetic coding sliders 52, and the opposite sides of the two slide rails 53 are respectively installed on the inner walls of the two sides of the protruding wing root 2.

[0038] The control system 7 is located inside the aircraft fuselage 1. The control system 7 is the "brain" of the entire aircraft, responsible for receiving various sensor signals and precisely controlling the various components of the aircraft according to the preset program and control algorithm.

[0039] The fuselage 1 of the aircraft is equipped with a fully movable tail 8 at the tail. The fully movable tail 8 can swing in all directions under the control of the control system 7, thereby adjusting the pitch, yaw and other attitudes of the aircraft and improving the controllability and stability of the aircraft. The top of the multiple tiltrotor wings 4 is equipped with a rotary drive assembly 9, and the output end of the multiple rotary drive assemblies 9 is equipped with a rotor body 10.

[0040] Multiple protruding wing roots 2 have inlets and outlets 11 at one end, and a fuselage passage 16 is opened at the bottom center of the aircraft fuselage 1.

[0041] An optical encoder is installed on the slide rail 53. The optical encoder can accurately detect the position of the magnetic encoder slider 52, thereby realizing precise control of the extension and retraction of the telescopic wing 51. The design of the telescopic wing 51 protruding from the wing root 2 is highly flexible. The telescopic wing 51 can be set to extend from the rear side of the protruding wing root 2 to realize the extension and retraction adjustment along the front and rear directions of the UAV; or it can be set to extend from the side of the protruding wing root 2 to achieve inward and outward extension and retraction between the protruding wing root 2 and the aircraft fuselage 1. The specific extension and retraction method will be freely selected by the UAV manufacturer according to actual needs and application scenarios. The bottom surface of the telescopic wing 51 is higher than the top surface of the tilt axis 3 to avoid interference during tilting. The tilt axis 3 is made of titanium alloy material with low friction coefficient. The tilt axis 3 is a key component to realize the tilting function of the wing. It is made of titanium alloy material with low friction coefficient. This material can effectively reduce the friction during the rotation process, reduce energy loss, and improve the flexibility and efficiency of tilting.

[0042] The rotary drive assembly 9 is connected to the rotor body 10 via a planetary reducer. The planetary reducer can reduce the output speed of the rotary drive assembly 9 while increasing the output torque, so that the rotor body 10 can obtain a suitable speed and torque to achieve efficient flight. The rotary drive assembly 9 is electrically connected to the control system 7. The rotary drive assembly 9 is set as a motor. The control system 7 can precisely control the start, stop, speed adjustment and other operations of the rotary drive assembly 9. The all-moving tail fin 8 is connected to the tail of the fuselage 1 of the aircraft via a high-rigidity rotating shaft.

[0043] Working principle: During aircraft operation, the control system 7 activates the rotary drive assembly 9 according to the flight mode command, which drives the rotor body 10 to rotate through the planetary reducer to generate lift. At the same time, the tilt shaft 3 rotates under the drive of the digital servo 12, causing the tiltrotor wing 4 to tilt to a vertical or horizontal state, realizing the autonomous switching between vertical takeoff and landing and level flight modes. During vertical takeoff and landing, the ventilation window 15 on the tiltrotor wing 4 opens to allow wind to pass directly through, reducing the impact of crosswinds. During level flight, the magnetic coded slider 52 slides along the slide rail 53, driving the retractable wing 51 to extend or retract from inside the protruding wing root 2, optimizing the aerodynamics. The aircraft moves in shape, while the optical encoder on the slide rail 53 feeds back position data to the control system 7 in real time to ensure motion accuracy. Through the dynamic adjustment of the telescopic rear wing 51 and the coordinated control of the aerodynamic drag of the wind-blocking mechanism 6, the aircraft reduces energy loss during mode switching and achieves the optimal matching of aerodynamic-energy integrated efficiency, thereby maintaining flight stability and avoiding altitude loss caused by discontinuous lift during mode switching. Furthermore, UAV manufacturers can freely choose to use a tiltrotor wing 4 equipped with a ventilation window 15 or a telescopic rear wing 51 according to actual needs and application scenarios to achieve the optimal performance and flexibility of the aircraft.

[0044] Example 2:

[0045] This embodiment is basically the same as the previous embodiment, except that the wind-blocking mechanism 6 includes a support plate 61, an adjustment drive assembly 62, a connecting seat 63, a wind-blocking plate 64, and a hinge 65. The support plate 61 is installed on the bottom inner wall of the aircraft fuselage 1. The support plate 61 has a certain strength and rigidity to support other components. There are two of each of the adjustment drive assembly 62, the connecting seat 63, and the hinge 65. The two adjustment drive assemblies 62 are respectively installed on the upper part of the outer walls on both sides of the support plate 61 through a movable shaft. The adjustment drive assembly 62 is configured as an electric push rod, a hydraulic cylinder, or a pneumatic cylinder. The two connecting seats 63 are respectively installed on the output ends of the two adjustment drive assemblies 62 through a movable shaft. The wind-blocking plate 64 is installed at the bottom end of the two connecting seats 63. The two hinges 65 are both installed on the top upper side of the wind-blocking plate 64, and the other side of the bottom end of the two hinges 65 are both installed on the bottom inner wall of the aircraft fuselage 1.

[0046] The adjustment drive assembly 62 is electrically connected to the control system 7. The control system 7 can issue commands according to the flight status of the aircraft (such as flight speed, altitude, attitude, etc.) to control the action of the adjustment drive assembly 62. The shape of the wind deflector 64 matches the shape of the fuselage opening 16, so that the wind deflector 64 can completely cover or partially block the fuselage opening 16 to adjust the wind resistance.

[0047] Working Principle: During aircraft operation, when faced with specific aerodynamic performance requirements at different flight stages, the control system 7 comes into play. The control system 7 precisely sends control signals to the adjustment drive assembly 62. Upon receiving the signal, the adjustment drive assembly 62 extends and retracts, causing the connecting seat 63 to move. This causes the wind deflector 64 to deflect around the hinge 65, thereby adjusting the angle of the wind deflector 64 to match the aerodynamic requirements of different flight stages such as vertical takeoff and landing, hovering, and level flight. When the aircraft needs to decelerate, the control system 7 controls the adjustment drive assembly 62 to open the wind deflector 64. At this time, the contact area between the wind deflector 64 and the air increases, significantly increasing air resistance and helping the aircraft decelerate efficiently. When the aircraft needs to accelerate, the control system 7 again controls the adjustment drive assembly 62 to retract the wind deflector 64 into the fuselage opening 16. At this time, the contact area between the wind deflector 64 and the air decreases sharply, and the resistance is basically eliminated, allowing the aircraft to accelerate quickly. This effectively improves flight flexibility and efficiency. This flexible adjustment capability significantly improves the aircraft's energy utilization and flight stability.

[0048] Example 3:

[0049] This embodiment is basically the same as the previous embodiment, except that a digital servo 12 is installed inside the aircraft fuselage 1. The digital servo 12 is an actuator with high-precision position control capability. It integrates a microprocessor, which can quickly process input signals and accurately control the output angle. The digital servo 12 is connected to the tilt shaft 3 through a transmission assembly. The transmission assembly can transmit the rotational motion of the digital servo 12 to the tilt shaft 3, realizing the precise adjustment of the tilt angle of the tilt rotor wing 4. For example, the transmission assembly can be a gear transmission mechanism, which amplifies or reduces the small angle rotation of the digital servo 12 and transmits it to the tilt shaft through the meshing of gears with different numbers of teeth. 3. To meet the different tilt angle requirements of the tiltrotor wings 4, a Beidou-3 positioning module 13 is installed on the top of the aircraft fuselage 1. The Beidou-3 positioning module 13 has high-precision positioning capabilities and can provide accurate geographical location information globally. Installing it on the top of the fuselage can avoid signal blockage by other parts of the fuselage and ensure stable reception of positioning signals. Multispectral vision sensors 14 are installed at the bottom of multiple tiltrotor wings 4 and protruding wing roots 2. Multispectral vision sensors 14 can capture multi-band spectral information (covering visible light, infrared, ultraviolet, etc.) to achieve target recognition, environmental perception, mission efficiency improvement and anti-interference capability enhancement.

[0050] The digital servo motor 12, the BeiDou-3 positioning module 13, and the multispectral vision sensor 14 are all electrically connected to the control system 7. The digital servo motor 12 receives control signals from the control system 7 and precisely controls the rotation angle of the tilt axis 3 according to the signal commands, thereby achieving precise adjustment of the tilt angle of the tilt rotor wing 4. This allows the aircraft to quickly and accurately adjust its flight attitude in different flight phases, such as takeoff, cruise, hovering, and landing, to meet the requirements of precision operations. The BeiDou-3 positioning module 13 acquires the aircraft's geographical location information in real time and transmits this information to the control system 7. The control system 7 plans the flight path based on the positioning information to ensure that the aircraft operates according to the preset route, avoiding repeated operations or missed areas. The multispectral vision sensor 14 collects multispectral image information and transmits the image data to the control system 7. The control system 7 analyzes and processes the image data, and based on the analysis results, the control system 7 can control the aircraft's flight path and operating mode. The control algorithm for the synchronous tilt of the tilt rotor wing 4 is as follows:

[0051]

[0052] During the vertical takeoff and landing phase: the tiltrotor wing 4 is locked at 90°±0.5°, and the retractable rear wing 51 is fully retracted and electromagnetically locked;

[0053] Level flight transition phase: The tiltrotor wing 4 and rotor body 10 are tilted to θ = f(v,h) (15°≤θ≤75°), where θ is the tilt angle, v is the airspeed, and h is the flight altitude. The telescopic wing 51 is deployed at L = 0.3C·arctan(v / 20), where L is the extension amount and C is the characteristic chord length.

[0054] The extension length L and the airspeed v satisfy: L = C·(1-e Λ (-0.12v));

[0055] Tail fin adjustment: β=0.8θ+0.1∫θdt, where β is the tail fin deflection angle and θ is the aircraft pitch angle;

[0056] The wind choke plate 64 control adopts PID-fuzzy composite algorithm:

[0057] ΔH=K_p·e(t)+K_i·∫e(t)dt+K_d·F(e(t)), where ΔH is the core output of the adjustment of the wind baffle 64. High-precision control is achieved through PID-fuzzy composite algorithm. F(e(t)) is the key innovation of the invention. By dynamically adjusting the weight of the differential term, the adaptability problem of traditional PID in nonlinear systems is solved.

[0058] Working principle: During flight, the digital servo motor 12 precisely controls the rotation angle of the tilt axis 3 through the transmission components, thereby adjusting the attitude of the tiltrotor wing 4 to match the aerodynamic requirements of vertical takeoff and landing or level flight modes. At the same time, the Beidou-3 positioning module 13 acquires the three-dimensional position and velocity data of the aircraft in real time. The multispectral vision sensor 14, through the layout of the tiltrotor wing 4 and the bottom of the protruding wing root 2, performs multimodal perception of obstacles, terrain and weather conditions in the flight path. The control system 7 integrates the data from the above sensors (tilt axis 3 angle, flight position and environmental information), and dynamically optimizes the flight strategy after real-time processing: on the one hand, it ensures flight stability through trajectory correction, and on the other hand, it realizes intelligent switching of flight modes (such as vertical takeoff and landing and level flight conversion) and dynamic path optimization. This process significantly improves the autonomy, safety and navigation accuracy of the aircraft in complex environments through dynamic adjustment of aerodynamic parameters and precise control of the actuators.

[0059] The foregoing has only described certain exemplary embodiments of the present invention by way of illustration. Undoubtedly, those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the foregoing drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. A tiltable wing multi-copter aircraft system based on adaptive aerodynamic optimization, characterized by, Include: The aircraft fuselage (1); The outer wall of the aircraft fuselage (1) is provided with a plurality of convex wing roots (2), the inside of the plurality of convex wing roots (2) is provided with a plurality of tilt shafts (3) through bearings, the other end of the plurality of tilt shafts (3) is provided with a plurality of tilt rotor wings (4), the inside of the plurality of convex wing roots (2) is provided with a plurality of telescopic mechanisms (5), the bottom end of the plurality of tilt rotor wings (4) is provided with a plurality of air vents (15), and the bottom end of the aircraft fuselage (1) is embeddedly provided with a plurality of wind resistance mechanisms (6); The telescopic mechanism (5) comprises a telescopic rear wing (51), a magnetic coding slider (52) and a slide rail (53), the magnetic coding slider (52) and the slide rail (53) are provided with two, the two magnetic coding sliders (52) are respectively installed on the two side outer walls of the telescopic rear wing (51), the two slide rails (53) are respectively slidably installed on the opposite sides of the two magnetic coding sliders (52), and the opposite sides of the two slide rails (53) are respectively installed on the two side inner walls of the convex wing root (2); The control system (7) is arranged in the inside of the aircraft fuselage (1).

2. The tiltable wing multi-copter aircraft system based on adaptive aerodynamic optimization of claim 1, wherein, The aircraft fuselage (1) is provided with a plurality of movable tail wings (8) at the tail of the fuselage, a plurality of rotary drive assemblies (9) are arranged at the top end of the plurality of tilt rotor wings (4), and a plurality of rotor bodies (10) are arranged at the output end of the plurality of rotary drive assemblies (9).

3. The tiltable wing multi-copter aircraft system based on adaptive aerodynamic optimization of claim 1, wherein, One end of the plurality of convex wing roots (2) is provided with an inlet and outlet (11), and the bottom end of the aircraft fuselage (1) is provided with a fuselage opening (16) in the middle.

4. The tiltable wing multi-copter aircraft system based on adaptive aerodynamic optimization of claim 1, wherein, The wind resistance mechanism (6) comprises a support plate (61), an adjusting drive assembly (62), a connecting seat (63), a wind resistance piece (64) and a hinge (65), the support plate (61) is installed on the bottom inner wall of the aircraft fuselage (1), the adjusting drive assembly (62), the connecting seat (63) and the hinge (65) are provided with two, the two adjusting drive assemblies (62) are respectively installed on the upper parts of the two side outer walls of the support plate (61) through the movable shafts, the two connecting seats (63) are respectively installed on the output ends of the two adjusting drive assemblies (62) through the movable shafts, the wind resistance piece (64) is installed on the bottom end of the two connecting seats (63), the two hinges (65) are respectively installed on the top side of the top end of the wind resistance piece (64), and the bottom ends of the two hinges (65) are respectively installed on the bottom inner wall of the aircraft fuselage (1).

5. The tiltable wing multi-copter aircraft system based on adaptive aerodynamic optimization of claim 1, wherein, The inside of the aircraft fuselage (1) is provided with a digital steering engine (12), and the digital steering engine (12) is connected with the tilt shaft (3) through a transmission assembly, the top end of the aircraft fuselage (1) is provided with a Beidou third-generation positioning module (13), and the bottom end of the plurality of tilt rotor wings (4) and the plurality of convex wing roots (2) is provided with a plurality of multispectral visual sensors (14).

6. The tiltable wing multi-copter aircraft system based on adaptive aerodynamic optimization of claim 1, wherein, An optical encoder is arranged on the slide rail (53), the bottom end of the telescopic rear wing (51) is higher than the top end of the tilt shaft (3), and the tilt shaft (3) is made of titanium alloy material with low friction coefficient.

7. The tiltable wing multi-copter aircraft system based on adaptive aerodynamic optimization of claim 2, wherein, The rotating drive assembly (9) is connected with the rotor body (10) through a planetary reducer, and the rotating drive assembly (9) is electrically connected with the control system (7), and the full-moving tail wing (8) is connected with the tail of the fuselage of the aircraft (1) through a high-rigidity rotating shaft.

8. The tiltable wing multi-copter aircraft system based on adaptive aerodynamic optimization of claim 4, wherein, The adjusting drive assembly (62) is electrically connected with the control system (7), and the shape of the wind-blocking piece (64) is matched with the shape of the fuselage through-opening (16).

9. The tiltable wing multi-copter aircraft system based on adaptive aerodynamic optimization of claim 5, wherein, The digital steering engine (12), the Beidou third-generation positioning module (13) and the multi-spectrum visual sensor (14) are electrically connected with the control system (7).

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