Bionic aircraft

Abstract

The invention provides a bionic aircraft and relates to the technical field of aircrafts, the bionic aircraft comprises an aircraft body and main wing systems arranged on the two sides of the middle of the aircraft body, each main wing system comprises a first driver, a first rocker arm, a connecting rod, a connecting base and a plurality of bionic wing ribs, and the first drivers are fixedly connected to the aircraft body; one end of the first rocker arm is connected with an output shaft of the first driver, the other end of the first rocker arm is hinged to one end of the connecting rod, one end of the connecting seat is hinged to the other end of the connecting rod, the other end of the connecting seat is hinged to the fuselage, the bionic wing ribs are hinged to the connecting seat, and the first driver drives the first rocker arm to rotate. The first rocker arm drives the connecting base to rotate around the fuselage through the connecting rod, then at least part of the bionic wing ribs are driven to rotate relative to the connecting base so as to be unfolded to form radial arrangement, and the aerodynamic performance, the control flexibility and the impact resistance are considered while the folding storage portability is kept.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft, in particular to a bionic aircraft. BACKGROUND

[0002] In recent years, micro unmanned aerial vehicles have been widely used in reconnaissance and surveillance, emergency rescue, environmental monitoring, scientific research and testing, and other fields due to their small size, light weight, portability, and rapid deployment. However, traditional micro unmanned aerial vehicles still have obvious deficiencies in structural design. For example, their fixed wings occupy a large space during transportation and storage, which is not conducive to carrying and can easily damage key components such as wings during handling, thereby affecting flight performance and reliability.

[0003] To solve this problem, the related field proposes a folding wing design. By folding or retracting the wings, the volume of the unmanned aerial vehicle in the transportation state can be significantly reduced, improving portability. However, existing folding designs mostly rely on hinge mechanisms, causing the entire wing to be rigidly folded. Although this structure reduces the volume to some extent, the occupied space after folding is still relatively large, and rigid folding cannot easily meet the demand for wing flexibility of bionic aircraft, limiting flight efficiency and applicable scenarios.

[0004] Against this background, document CN118907465A proposes a cross-medium bionic unmanned aerial vehicle that can work in water and air respectively: when navigating in water, the flapping wings are folded and tightly attached to the fuselage to reduce drag; when flying in the air, the flapping wings are unfolded to provide lift, with certain bionic characteristics. In its design, each side of the flapping wing is composed of five skeletons and high-strength polyester film, with one end of the skeleton being a circular ring connected through a rotating shaft and a roller bearing. The first skeleton is connected to the steering engine and drives the remaining skeletons to unfold in sequence through a positioning pin and a bar hole structure, finally forming the required wing shape.

[0005] Although this technical solution has certain advantages in folding mode and bionic ability, it still has several deficiencies. First, the design of connecting multiple skeletons with a single rotating shaft makes it difficult to maintain a reasonable and stable wing shape after unfolding, resulting in low actual lift and limiting flight performance. Second, the first skeleton needs to drive multiple skeletons to unfold in sequence through the rotating shaft, which puts high requirements on the output torque and response speed of the steering engine, which can easily lead to increased power consumption and response lag, thereby reducing control accuracy and flight sensitivity. In addition, to achieve the sequential unfolding of different skeletons, the internal structure of the rotating shaft is complex, involving a large number of parts and high assembly precision requirements. This not only increases manufacturing difficulty and cost, but also increases the risk of structural failure during long-term operation, with insufficient reliability.

[0006] Therefore, it is urgent to provide a new micro unmanned aerial vehicle design scheme which can keep high lift, reduce power consumption and simplify structure while considering folding storage and biomimetic flight. SUMMARY

[0007] The present application aims at the above technical deficiencies, and provides a biomimetic aircraft.

[0008] To achieve the above object, the technical scheme adopted by the present application is as follows: The present application provides a biomimetic aircraft, which comprises a fuselage and a main wing system arranged on both sides of the middle part of the fuselage, each main wing system comprising a first driver, a first rocker arm, a connecting rod, a connecting seat and a plurality of biomimetic wing ribs, the first driver being fixedly connected to the fuselage, one end of the first rocker arm being connected to the output shaft of the first driver, the other end of the first rocker arm being hingedly connected to one end of the connecting rod, one end of the connecting seat being hingedly connected to the other end of the connecting rod, the other end of the connecting seat being hingedly connected to the fuselage, the plurality of biomimetic wing ribs being hingedly connected to the connecting seat, the first driver driving the first rocker arm to rotate, the first rocker arm driving the connecting seat to rotate around the fuselage through the connecting rod, and further driving at least part of the biomimetic wing ribs to rotate relative to the connecting seat to be unfolded to form a radial arrangement.

[0009] Further, each main wing system further comprises a non-elastic film, the non-elastic film covering the outer surface of the plurality of biomimetic wing ribs, for limiting the rotation angle of each biomimetic wing rib during unfolding.

[0010] Further, the connecting seat comprises upper and lower fixed plates arranged in parallel and at intervals, an installation shaft being fixedly connected to the fuselage, one end of the upper fixed plate and one end of the lower fixed plate being hingedly connected to two ends of the installation shaft respectively, the other end of the upper fixed plate being connected to the lower fixed plate through a connecting shaft, the other end of the lower fixed plate being hingedly connected to the connecting rod, a plurality of rotating shafts being arranged at intervals between the upper fixed plate and the lower fixed plate, and each biomimetic wing rib being hingedly connected to a different rotating shaft.

[0011] Further, each main wing system further comprises a main load-bearing beam fixedly connected to the end of the connecting seat away from the fuselage, the plurality of biomimetic wing ribs being located between the fuselage and the main load-bearing beam, and the main load-bearing beam being used for limiting the maximum unfolding angle of the plurality of biomimetic wing ribs.

[0012] Further, the lengths of the plurality of biomimetic wing ribs increase successively in the direction from the fuselage to the main load-bearing beam, so that the projection connecting line of the plurality of biomimetic wing ribs on the same horizontal plane after unfolding is an arc line.

[0013] Further, the outer surface of each biomimetic wing rib is a streamlined curved surface which is convex upward.

[0014] Further, the bionic aircraft further comprises a tail wing system, the tail wing system comprises horizontal tail wing systems arranged on both sides of the tail of the fuselage, each horizontal tail wing system comprises a second driver, a second rocker arm, a pull rod and a horizontal tail wing, the horizontal tail wing comprises a first wing part fixed on the side of the fuselage and a second wing part movably spliced on the first wing part along the length direction of the fuselage, the second driver is fixedly connected on the fuselage, one end of the second rocker arm is connected with the output shaft of the second driver, the other end of the second rocker arm is hingedly connected with one end of the pull rod, the other end of the pull rod is hingedly connected with the second wing part, the second driver drives the second rocker arm to rotate, the second rocker arm drives the second wing part to rotate through the pull rod, so as to adjust the attitude of the bionic aircraft.

[0015] Further, the second drivers of the two horizontal tail wing systems are non-synchronous rotation, and the two second wing parts are non-synchronous rotation, so as to adjust the attitude of the bionic aircraft.

[0016] Further, the tail wing system further comprises a vertical tail wing, the vertical tail wing is fixedly connected on the top surface of the tail of the fuselage.

[0017] Further, the bionic aircraft further comprises a power system arranged on the head of the fuselage, the power system comprises a third driver, a paddle and a streamlined shell, the third driver is fixedly connected on the fuselage, the output end of the third driver is connected with the paddle, for driving the paddle to rotate to generate flight power, the shell is sleeved outside the third driver, for protecting the third driver and improving the aerodynamic effect.

[0018] The beneficial effects of the present application include: The application provides a bionic aircraft, comprising a fuselage and main wing systems arranged on both sides of the middle part of the fuselage, each main wing system comprising a first driver, a first rocker arm, a connecting rod, a connecting seat and a plurality of bionic wing ribs, the first driver being fixedly connected to the fuselage, one end of the first rocker arm being connected to an output shaft of the first driver, the other end of the first rocker arm being hingedly connected to one end of the connecting rod, one end of the connecting seat being hingedly connected to the other end of the connecting rod, the other end of the connecting seat being hingedly connected to the fuselage, and the plurality of bionic wing ribs being hingedly connected to the connecting seat, respectively, the first driver driving the first rocker arm to rotate, the first rocker arm driving the connecting seat to rotate around the fuselage through the connecting rod, and further driving at least part of the bionic wing ribs to rotate relative to the connecting seat to be arranged in a radial manner. The connecting rod of the main wing system and the radial arrangement of the bionic wing ribs achieve balance in structure and kinematics, so that the transport volume can be greatly reduced and the main wing system can be quickly and reliably unfolded, the peak moment borne by the first driver and the fuselage is reduced, the energy consumption is reduced and the service life of the first driver is prolonged, the bionic wing ribs arranged in a non-coaxial manner improve the airfoil retention and aerodynamic efficiency, effectively improve the lift and reduce the moment, and suppress the buffeting of the aircraft during high-speed flight, the adjustable angle setting caused by the independent driving of the main wing systems on both sides enhances the adaptability and maneuverability of the aircraft under different working conditions, the self-unloading feature without locking enables the main wing to release energy in a controllable manner when impacted, and the probability of structural damage is significantly reduced and the reliability and recoverability of the whole machine are improved. Overall, the scheme takes into account the aerodynamic performance, control flexibility and impact resistance while maintaining the folding, storage and portability, and provides a systematic solution to the problems of easy damage of the wings of traditional unmanned aircraft, difficulty in maintaining the airfoil and large driving load. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 FIG. 1 is a structural schematic diagram of a bionic aircraft provided by the application; Figure 2 FIG. 2 is another structural schematic diagram of a bionic aircraft provided by the application; Figure 3 FIG. 3 is a third structural schematic diagram of a bionic aircraft provided by the application; Figure 4 FIG. 4 is a structural schematic diagram of a main wing system of a bionic aircraft provided by the application; Figure 5 FIG. 5 is another structural schematic diagram of a main wing system of a bionic aircraft provided by the application; Figure 6 FIG. 6 is a structural schematic diagram of a tail wing system of a bionic aircraft provided by the application; Figure 7 FIG. 7 is a structural schematic diagram of a power system of a bionic aircraft provided by the application.

[0020] Icons: 1. Main wing system; 101. First actuator; 102. First mounting base; 103. First rocker arm; 104. Connecting rod; 105. Connecting base; 1051. Upper fixing plate; 1052. Lower fixing plate; 106. Bionic wing rib; 107. Main load-bearing beam; 108. Limiting block; 109. Limiting plate; 110. Mounting shaft; 111. Rotating shaft; 2. Tail system; 201. Second actuator; 202. Second rocker arm; 203. Pull rod; 2041. First wing; 2042. Second wing; 205. Rudder angle; 206. Vertical tail; 3. Power system; 301. Housing; 302. Third actuator; 303. Third mounting base; 4. Fuselage. Detailed Implementation

[0021] This application provides a biomimetic flight vehicle, such as Figures 1 to 5 As shown, the system includes a fuselage 4 and main wing systems 1 arranged on both sides of the middle of the fuselage 4. Each main wing system 1 includes a first actuator 101, a first rocker arm 103, a connecting rod 104, a connecting seat 105, and several bionic wing ribs 106. The first actuator 101 is fixed to the fuselage 4 via a first mounting seat 102. The output shaft of the first actuator 101 is fixedly connected to one end of the first rocker arm 103. The other end of the first rocker arm 103 is hinged to one end of the connecting rod 104. The other end of the connecting rod 104 is hinged to one end of the connecting seat 105. The other end of the connecting seat 105 is hinged to the fuselage 4. The first rocker arm 103, the connecting rod 104, the connecting seat 105, and the line connecting the rotation center of the first rocker arm 103 and the rotation center of the connecting seat 105 together form a four-bar linkage, thereby achieving stable rotation of the connecting seat 105 and limiting the motion trajectory of the connecting seat 105, thereby controlling the relative angular displacement and deployment rhythm of the several bionic wing ribs 106 that are independently rotated and mounted on the connecting seat 105. The geometric relationship between the first rocker arm 103, the connecting rod 104, the connecting seat 105, and the rotation center of the first rocker arm 103 and the rotation center of the connecting seat 105 exhibits the kinematic characteristics of a four-bar linkage. The line connecting the rotation center of the first rocker arm 103 and the rotation center of the connecting seat 105 limits the trajectory of the connecting seat 105 during motion, thereby controlling the relative angular displacement and deployment rhythm of several bionic wing ribs 106 mounted on the connecting seat 105.

[0022] The first driver 101 adopts a steering engine. During the driving process, the first driver 101 drives the first rocker arm 103 to rotate around its output shaft, and the first rocker arm 103 transmits force and angular displacement to the connecting seat 105 through the connecting rod 104, so that the connecting seat 105 rotates around the connecting point of the fuselage 4. Each bionic wing rib 106 on the connecting seat 105 is in rotational cooperation with the connecting seat 105 through a rotating shaft 111, for example, the connecting seat 105 is hinged with the rotating shaft 111, the rotating shaft 111 is fixedly connected with the bionic wing rib 106, or the connecting seat 105 is fixedly connected with the rotating shaft 111, and the rotating shaft 111 is hinged with the bionic wing rib 106. Therefore, when the connecting seat 105 rotates, part or all of the bionic wing ribs 106 will rotate in the same direction through the rotating shaft 111, realizing the transition from folding to radial expansion or from radial expansion to folding. Each bionic wing rib 106 can be arranged differently in length, offset angle and mounting radius, and can be arranged in a gradient from inside to outside, so as to form a continuous airfoil profile and generate a required aerodynamic curvature. The geometric parameters of the four-bar linkage can provide favorable torque transmission characteristics after optimization, so that the first driver 101 can bear a lower torque peak value when realizing a large angular displacement, and the entire main wing system 1 can realize a higher lift while maintaining a lower torque in the expanded state.

[0023] It should be noted that a connecting piece is fixed on the side of the fuselage 4, and a mounting shaft 110 is fixedly arranged on the connecting piece in the vertical direction. The connecting seat 105 includes an upper fixed sheet 1051 and a lower fixed sheet 1052 arranged in parallel and spaced apart in the vertical direction. One end of the upper fixed sheet 1051 and one end of the lower fixed sheet 1052 are rotatably sleeved on the upper and lower ends of the mounting shaft 110, respectively. The other end of the upper fixed sheet 1051 is connected to a limiting block 108 fixed on the lower fixed sheet 1052 through a connecting shaft, and the other end of the lower fixed sheet 1052 is hinged with the connecting rod 104. A plurality of rotating shafts 111 are arranged between the upper fixed sheet 1051 and the lower fixed sheet 1052, and are respectively used to connect each bionic wing rib 106. In addition, the first bionic wing rib 106 close to the fuselage 4 is fixedly connected with the mounting shaft 110, and a limiting sheet 109 is sleeved on the mounting shaft 110. The limiting sheet 109 abuts against the connecting piece on the side of the fuselage 4, so as to ensure that the first bionic wing rib 106 close to the fuselage 4 remains stationary and its length direction is always parallel to the length direction of the fuselage 4 when the connecting seat 105 rotates around the mounting shaft 110 under the driving of the first driver 101. Such a structure design avoids interference between the bionic wing rib 106 and the fuselage 4 during the expansion or folding process, and provides a reference constraint for the movement range of the entire folding main wing.

[0024] It should be noted that the left and right main wing systems 1 are independently driven and controlled, and the first drivers 101 on both sides respectively receive angle commands from the attitude controller and feedback position encoder signals to achieve precise positioning. Independent control allows the left and right main wings to be set differently in terms of deployment angle, yaw angle or damping parameters to meet the requirements of turning, crosswind compensation or differential lift, while facilitating unilateral or local folding during take-off and landing, or passing through narrow spaces. To ensure smooth deployment and retraction and impact resistance, low-friction bearings or bushings can be used at the pivot shafts 111, with appropriate clearances and frictional damping to prevent the bionic ribs 106 from being rigidly locked when subjected to external impact, and instead unloaded in the retraction direction along the predetermined path, reducing the risk of structural damage.

[0025] In addition, some of the bionic ribs 106 are arranged non-coaxially, i.e. the pivot shafts 111 of the multiple bionic ribs 106 are parallel and spaced apart, and each bionic rib 106 rotates around its pivot shaft 111 in the horizontal plane, which can improve structural reliability and achieve three-dimensional bending and twisting distribution of the airfoil, enhance the torsional stiffness and curvature retention capability of the wing surface, and effectively suppress the vibration and local stall of the thin film under high-speed airflow when forming a continuous wing surface with the thin film covering layer.

[0026] Overall, the four-bar linkage drive of the main wing system 1 and the radial arrangement of the bionic ribs 106 achieve a balance between significantly reducing the transportation volume and quickly and reliably deploying in terms of structure and kinematics, reducing the peak moment borne by the first driver 101 and the fuselage 4, thereby reducing energy consumption and improving the service life of the first driver 101; the non-coaxial ribs improve the airfoil retention and aerodynamic efficiency, effectively increasing the lift and reducing the moment, and suppressing the buffeting of the thin film main wing during high-speed flight; the adjustable angle setting brought by independent driving enhances the adaptability and maneuverability of the aircraft under different working conditions; the self-unloading feature without locking allows the main wing to release energy in a controllable manner when subjected to impact, significantly reducing the probability of structural damage and improving the reliability and recoverability of the entire machine. Overall, this scheme balances the aerodynamic performance, control flexibility and impact resistance robustness while maintaining the portability of folding and storage, and provides a systematic solution to the problems of easy damage, difficult airfoil maintenance and high driving load of traditional unmanned aircraft wings.

[0027] Further, the main wing system 1 uses a thin film main wing, and the thin film material is a non-elastic film. The non-elastic film itself has a thickness close to zero, so the target airfoil can be determined through aerodynamic analysis, and the camber line is extracted from the airfoil as the cross-sectional line of the thin film main wing, so that the deployed film surface presents the expected curvature. The camber line is used as a design reference to determine the three-dimensional arrangement of the ribs and the pre-tension direction of the film surface, so as to obtain the required lift characteristics under the condition of extremely small thickness.

[0028] In order to support the inelastic film and maintain the aerodynamic curvature, the upper surface of the bionic rib 106 and the lower surface of the inelastic film are combined by bonding or heat pressing process to form an inseparable bonding surface. Each bionic rib 106 is an upward convex streamline curved surface, wherein the upward convex refers to the upward convex in the upward direction of the aircraft. After the grading arrangement of the plurality of bionic ribs 106, a continuous camber and twist distribution is formed in three dimensions. The close fit of the inelastic film and the bionic rib 106 automatically forms a smooth aerodynamic shape and bears the flight load when unfolded; the bonding point and the tensioning scheme are controlled by the pre-tensioning of the tool and solidification to ensure that the curvature of the film surface is stable and highly repeatable in the working state.

[0029] In addition, the combination of the inelastic film and the bionic rib 106 not only bears the aerodynamic force in the flight process, but also limits the maximum rotation angle of each bionic rib 106 through geometric constraints. That is, when the connecting seat 105 rotates to drive each bionic rib 106 to gradually unfold, the geometric shape of the film surface at the limit position corresponds to a soft limit, so that the bionic rib 106 cannot exceed the maximum unfolding angle determined by the joint position of the inelastic film and the bionic rib 106.

[0030] In summary, the use of a medium camber section and an inseparable film and skeleton combination allows the thin film main wing to obtain higher lift and ideal airfoil retention ability under the premise of low thickness, improve the torsional stiffness of the wing surface and effectively suppress the thin film buffeting phenomenon under high-speed airflow, thereby improving stability and aerodynamic efficiency. The geometric limiting function of the film surface limits the maximum unfolding angle of the skeleton, avoids structural conflicts and reduces the peak moment demand of the first driver 101, thereby reducing the driving load and improving system durability. The actual measurement and verification show that the bionic aircraft maintains good shape repeatability and mechanical integrity under multiple unfolding and folding cycles and flight conditions, has a wide flight envelope, high speed and high lift, and has a large load carrying capacity while considering bionics, can perform various tasks, and effectively alleviates the problems of wing damage, wing type maintenance difficulty and buffeting in traditional micro unmanned aircraft in transportation, deployment and high-speed cruising.

[0031] Further, each main wing system 1 further comprises a main load-bearing beam 107 fixedly connected at the end of the connecting seat 105 away from the fuselage 4, and is limited by a limiting block 108 on the connecting seat 105, for ensuring the stability of the main load-bearing beam 107 relative to the connecting seat 105. A plurality of bionic ribs 106 are located between the fuselage 4 and the main load-bearing beam 107, and the lower surface of the inelastic film is fixedly connected with the upper surface of the main load-bearing beam 107 by adhesion, forming a leading edge constraint, so as to maintain the curved surface of the inelastic film by the cooperation of the main load-bearing beam 107 and the plurality of bionic ribs 106 as the framework of the thin-film main wing. The main load-bearing beam 107 acts as the leading edge of the thin-film main wing and rotates synchronously with the connecting seat 105, and the connecting seat 105 drives the main load-bearing beam 107 to move around the rotation support point close to the fuselage 4. In the unfolded position, the length direction of the main load-bearing beam 107 is substantially perpendicular to the length direction of the fuselage 4, which can limit the maximum unfolding angle of the bionic ribs 106; in the folded position, the length direction of the main load-bearing beam 107 is approximately parallel to the fuselage 4, which is convenient for compact storage. The plurality of bionic ribs 106 are located between the fuselage 4 and the main load-bearing beam 107, and the main load-bearing beam 107 is used to limit the maximum unfolding angle of the plurality of bionic ribs 106.

[0032] Further, the length unfolding direction of the plurality of bionic ribs 106 increases in turn, with the inside (close to the fuselage 4 side) being short and the outside (away from the fuselage 4 side) being long, and the projection of the end point on the same horizontal plane falls on an arc according to design, thereby forming a smooth arc profile in the plan view, so that the airflow distribution is more uniform, thereby reducing the induced drag, improving the smooth distribution of lift, and enabling the aircraft to maintain good flight performance in low-speed and cruising states. In addition, the arc layout is conducive to reducing the torsion and buffeting of the main wing under the action of airflow, especially in the design of thin-film main wing, the arc profile can assist the film surface to naturally form a curved surface, and enhance the aerodynamic stiffness and fatigue resistance.

[0033] Further, the bionic aircraft further comprises a tail wing system 2, which has the core function of realizing attitude adjustment. As shown in FIG. 1, the tail wing system 2 comprises a tail wing 201 and a tail wing drive system 202. Figure 6As shown, the tail system 2 includes horizontal tail systems arranged on both sides of the tail of the fuselage 4, each horizontal tail system including a second driver 201, a second rocker arm 202, a pull rod 203, and a horizontal tail including a first wing portion 2041 fixed on the side of the fuselage 4 and a second wing portion 2042 movably spliced on the first wing portion 2041 along the length direction of the fuselage 4. The movable part of the second wing portion 2042 can be driven to produce the necessary angular deflection, thereby achieving control of the pitch and roll of the aircraft. The second driver 201 is fixedly connected to the fuselage 4, one end of the second rocker arm 202 is connected to the output shaft of the second driver 201, the other end of the second rocker arm 202 is hingedly connected to one end of the pull rod 203, and the other end of the pull rod 203 is hingedly connected to a rudder angle 205 fixed to the second wing portion 2042. The second driver 201 is a steering gear, when the second driver 201 works, the second rocker arm 202 is driven to rotate through the output shaft thereof, the rotary motion of the second rocker arm 202 is transmitted to the rudder angle 205 through the pull rod 203, and the rudder angle 205 is transmitted to the second wing portion 2042, so that the second wing portion 2042 is controlled to rotate relative to the first wing portion 2041.

[0034] It should be noted that the second drivers 201 of the horizontal tail systems on both sides can be independently or jointly adjusted in the flight process through differential control cooperation, so as to realize accurate attitude control, including pitch and roll. For example, the second wing portions 2042 on both sides are simultaneously rotated upward or downward, which will produce pitch (aircraft lifting or diving), and the second wing portions 2042 on both sides are rotated upward and downward, which will produce roll.

[0035] Further, the tail system 2 further includes a vertical tail 206 fixedly connected to the top surface of the tail of the fuselage 4, which acts as a stabilizer and mainly provides directional stability of the aircraft to prevent lateral disturbance from causing the fuselage 4 to yaw. The vertical tail 206 does not have a main rudder surface, and its stability function is complementary to the active control of the horizontal tail, and together ensures the attitude stability of the aircraft in various flight states.

[0036] The design of the tail system 2 simplifies the aileron and rudder configuration of the conventional aircraft in structure and control, all flight control functions are realized through horizontal tail coupling, reduces the number of mechanical components, improves the response sensitivity and reliability of the system, and at the same time reduces the overall weight and manufacturing complexity. In addition, the connection of the second wing portion 2042 with the second rocker arm 202 and the pull rod 203 ensures the efficiency and accuracy of motion transmission, and the differential control allows flexible pitch and roll adjustment without increasing the complexity of the mechanism.

[0037] The whole tail wing layout and fuselage 4 proportion reference flying fish shape, realizes the bionics to flying fish appearance, strengthens the aerodynamic performance, also promotes the stability of aircraft in low speed and cruising state. Through this bionic design, the tail wing system 2 can not only effectively control the aircraft attitude, but also provide sufficient stability in different flight conditions, so that the aircraft has high control precision and safety.

[0038] Further, the bionic aircraft also includes a power system 3 arranged at the head of the fuselage 4, which plays a core role in providing stable thrust for the aircraft. As shown in Figure 7 The power system 3 includes a third driver 302, a paddle (not shown in the figure) and a streamlined shell 301, the third driver 302 is fixedly connected to the fuselage 4 through a third mounting seat 303, the third driver 302 adopts a motor, the output end of the motor is connected with the paddle, for driving the paddle to rotate, so that the air flow forms a thrust, thereby driving the aircraft to move forward. The fixed installation of the third driver 302 ensures the stability and reliability of power transmission, and ensures the continuity and balance of output torque during flight.

[0039] The paddle cuts the air to generate forward thrust when rotating, and its design is matched with the power of the third driver 302, so that the aircraft can maintain the required speed and acceleration in different flight states. In order to further optimize the aerodynamic performance of the power system 3 and protect the internal structure, the third driver 302 is wrapped with a streamlined shell 301, the shell 301 wraps outside the third driver 302, which not only effectively reduces air resistance and improves propulsion efficiency, but also prevents debris from impacting the third driver 302 during flight, thereby prolonging the service life of the power system 3.

[0040] Through the design of the power system 3, the bionic aircraft can achieve efficient propulsion in different flight tasks and environmental conditions, while maintaining the stability of the whole machine. The compact structure and good aerodynamic performance of the power system 3 enable the aircraft to obtain smooth and sufficient thrust output in low-speed take-off, climbing and cruising states, and through the shell 301 to optimize air flow, improve overall propulsion efficiency and reduce energy loss. This design not only ensures the reliability of power transmission, but also combines with the coordinated control of the main wing system 1 and the tail wing system 2, realizes the high maneuverability and high stability of the aircraft.

[0041] The above only describes the preferred embodiments of the present application and is not intended to limit the present application. For those skilled in the art, the present application can have various changes and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A biomimetic aircraft, characterized in that, The system includes a fuselage and main wing systems arranged on both sides of the middle of the fuselage. Each main wing system includes a first actuator, a first rocker arm, a connecting rod, a connecting seat, and several bionic wing ribs. The first actuator is fixedly connected to the fuselage. One end of the first rocker arm is connected to the output shaft of the first actuator. The other end of the first rocker arm is hinged to one end of the connecting rod. One end of the connecting seat is hinged to the other end of the connecting rod. The other end of the connecting seat is hinged to the fuselage. Several bionic wing ribs are respectively hinged to the connecting seat. The first actuator drives the first rocker arm to rotate. The first rocker arm drives the connecting seat to rotate around the fuselage via the connecting rod, thereby causing at least some of the bionic wing ribs to rotate relative to the connecting seat to unfold and form a radial arrangement.

2. The biomimetic aircraft according to claim 1, characterized in that, Each main wing system also includes an inelastic membrane covering the outer surface of several bionic wing ribs to limit the rotation angle of each bionic wing rib during deployment.

3. The biomimetic aircraft according to claim 1 or 2, characterized in that, The connecting seat includes an upper fixed plate and a lower fixed plate arranged in parallel and spaced apart. A mounting shaft is fixedly connected to the body. One end of the upper fixed plate and one end of the lower fixed plate are respectively hinged to the two ends of the mounting shaft. The other end of the upper fixed plate is connected to the lower fixed plate via a connecting shaft. The other end of the lower fixed plate is hinged to a connecting rod. Several rotating shafts are arranged at intervals between the upper fixed plate and the lower fixed plate. Each bionic wing rib is respectively hinged to a different rotating shaft.

4. The biomimetic aircraft according to claim 1 or 2, characterized in that, Each main wing system also includes a main load-bearing beam fixedly connected to the end of the connecting seat away from the fuselage, and several bionic wing ribs located between the fuselage and the main load-bearing beam. The main load-bearing beam is used to limit the maximum deployment angle of the several bionic wing ribs.

5. The biomimetic aircraft according to claim 4, characterized in that, The length of several bionic wing ribs increases sequentially along the direction from the fuselage to the main load-bearing beam, so that the projection line of several bionic wing ribs on the same horizontal plane after they are deployed is an arc.

6. The biomimetic aircraft according to claim 1 or 2, characterized in that, The outer surface of each biomimetic rib is a streamlined curved surface that convexes upwards.

7. The biomimetic aircraft according to claim 1 or 2, characterized in that, The biomimetic aircraft also includes a tail system, which includes horizontal tail systems arranged on both sides of the tail of the fuselage. Each horizontal tail system includes a second actuator, a second rocker arm, a lever, and a horizontal tail. The horizontal tail includes a first wing fixed to the side of the fuselage and a second wing that is movably spliced ​​onto the first wing along the length of the fuselage. The second actuator is fixedly connected to the fuselage. One end of the second rocker arm is connected to the output shaft of the second actuator, and the other end of the second rocker arm is hinged to one end of the lever. The other end of the lever is hinged to the second wing. The second actuator drives the second rocker arm to rotate, and the second rocker arm drives the second wing to rotate via the lever to adjust the attitude of the biomimetic aircraft.

8. The biomimetic aircraft according to claim 7, characterized in that, The second actuators of the two horizontal tail systems rotate asynchronously, which in turn drives the two second wings to rotate asynchronously in order to adjust the attitude of the biomimetic aircraft.

9. The biomimetic aircraft according to claim 7, characterized in that, The tail system also includes a vertical tail, which is fixedly attached to the top surface of the rear of the fuselage.

10. The biomimetic aircraft according to claim 1 or 2, characterized in that, The biomimetic aircraft also includes a power system located at the nose of the fuselage. The power system includes a third actuator, propeller blades, and a streamlined casing. The third actuator is fixedly connected to the fuselage, and its output end is connected to the propeller blades to drive the blades to rotate and generate flight power. The casing is fitted over the third actuator to protect it and improve aerodynamic performance.

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