Rotary wing structure

Abstract

The utility model belongs to the technical field of aviation aircrafts, and discloses a rotary wing structure which comprises a rotary main shaft, a servo motor, a transmission part, a main shaft support, a wing and a flight control part. The wing part is mounted on a rotating main shaft outside the aircraft body through a wing interface, and the servo motor controls the rotating main shaft to rotate through the transmission part so as to drive the wing part to rotate; the control performance of the aircraft is further improved by adding a propeller system, an elevator and a rudder on the wings, so that the aircraft has a helicopter flight mode and a fixed wing flight mode, and the conversion between the vertical take-off and landing state and the fixed wing flight state of the aircraft is facilitated.

Description

Technical Field

[0001] The utility model belongs to the technical field of aviation aircraft, and in particular relates to a rotary wing structure. Background Art

[0002] Aircraft have been widely used in civil transportation, surveying, and military missions. Although most fixed-wing aircraft have good cruising flight economy, they do not have vertical take-off and landing capabilities. Helicopters are convenient for vertical take-off and landing, and also have hovering functions, but they require high-power engines, consume a lot of fuel, have low endurance, have poor flight economy, and cannot perform long-duration flights. Therefore, composite wing aircraft combining fixed wings and rotors have begun to be used. There are currently three main structural forms. The first is the structural form represented by the American Osprey aircraft, which adds a tilt-rotating propeller to the end of the fixed wing. The second is a pure battery power supply mode in which a vertical take-off and landing rotor motor is added to the fixed wing. The third is a hybrid power mode in which a vertical take-off and landing rotor motor and a fuel engine are added to the fixed wing.

[0003] The advantages of these three forms are that they all have vertical take-off and landing functions, and also have some advantages of fixed-wing aircraft, but their disadvantages are also very obvious. First of all, the first type of tilt-power propeller is installed at the outer end of the fixed wing. Not only does the vibration have a destructive force on the wing structure, but in the vertical flight state, the downwash airflow of the propeller has a large sinking force on the fixed wing and the upper part of the fuselage, which seriously affects the maximum take-off weight of the aircraft and has a great impact on the take-off and landing maneuverability. Especially when converting from horizontal flight to vertical flight, the vortex generated by the propeller at the wingtip of the fixed wing directly affects the flight control performance. The multiple fatal accidents of the US Osprey aircraft are the best proof of this. The second type of fixed-wing aircraft is equipped with a pure battery power supply mode with a vertical take-off and landing rotor motor. Due to current technical limitations, the battery energy density is small and cannot be long-lasting. The endurance time and the heavy weight of the battery seriously affect the effective load, and it is only suitable for small-load aircraft and its application is limited. The third type of hybrid power mode is oil-electric. The rotor motor part only works during takeoff and landing. The oil engine is only responsible for the output of horizontal flight power. The rotor motor needs to be equipped with a considerable weight of batteries as reserve power. It is limited to a limited vertical landing time, which not only seriously affects the aircraft's effective load, but also has poor wind resistance and is limited in use under complex weather conditions. Based on the current technical status, it is impossible to complete the design and application of large-load aircraft, and the fuel power and battery power systems cannot be converted into each other in the oil-electric hybrid power system. Both power systems must exist, which undoubtedly increases the overall weight of the power system, increases the aircraft's own weight, and reduces the effective load.

[0004] Therefore, it is a difficult problem that technicians in this field need to solve urgently to develop a control structure that can fully utilize the propeller power system to smoothly switch between vertical flight and horizontal flight and reduce the sinking force of the propeller downwash on the fixed wing. Utility Model Content

[0005] In order to solve the problems existing in the background technology, the utility model provides a rotary wing structure, which includes a rotary main shaft, a servo motor, a transmission part, a main shaft bracket, a wing, a flight control, etc., wherein:

[0006] The rotating spindle is installed on the spindle bracket, the spindle bracket is installed on the fuselage structure, and the wing part is installed on the external interface of the rotating spindle through the wing interface; this split structure design is convenient for assembly and maintenance, and the vulnerable parts can also be replaced regularly according to the wear and tear and service life;

[0007] The servo motor controls the rotation of the main shaft through the transmission part, thereby driving the rotation of the wing part; this design allows the wing plane to freely switch between the vertical and horizontal planes. When the wing plane is in a vertical state with the aircraft plane, it can greatly reduce the sinking force of the downwash airflow on the wing and fuselage when the aircraft is in the working state of the rotor; when the wing plane is in a parallel state with the aircraft plane, it ensures that the fixed wing of the aircraft generates sufficient lift in the level flight state, increases the endurance of the aircraft, improves the economic performance of the aircraft, and also significantly improves the aircraft's service ceiling and high-altitude wind resistance.

[0008] The flight control, servo motor and transmission part form a servo system. This servo system mainly forms a closed-loop control of the flight attitude of the wing, ensuring a smooth transition between the helicopter flight state and the fixed-wing flight state, and further improving the aircraft's maneuverability and flight stability.

[0009] The wing structure has helicopter flight mode and fixed-wing flight mode, and the two modes can be switched controllably through the servo system. The purpose of the rotating wing structure is to solve the problem that the wing has helicopter flight mode and fixed-wing flight mode, and the two modes can be switched safely and smoothly.

[0010] Furthermore, the rotating main shaft is provided with a wing connection hole, a main shaft positioning hole, a sleeve, and a main shaft wing angle of attack zero position baseline, and the sleeve is provided with a keyway, a limit hole, and a sleeve assembly baseline, and the sleeve assembly baseline is consistent with the main shaft wing angle of attack zero position baseline, and the driven wheel is fixed to the main shaft through a special sleeve, a key, a limit pin, and a main shaft positioning hole. This design makes it easy to install and fix the rotating main shaft, and the sleeve is used to assist in strengthening the structure of the opening part, so that the main shaft body can still maintain sufficient strength despite processing, opening holes, etc., and also takes into account the connection and fixation of the supporting parts.

[0011] Furthermore, when the rotating main shaft is a left-right split structure, the servo system also has two sets of corresponding structures, and the servo system has the function of controlling the two sets of left-right split rotating main shafts separately and synchronously. This design is mainly to meet the requirements of different types of aircraft control performance. For example, for fighters with high maneuverability requirements, when the rotating main shaft adopts a left-right split structure, the differential of the left and right wings can quickly achieve tactical actions such as turning, rolling, and dogfighting. Ordinary transport aircraft can use a rotating main shaft with an integrated structure to meet normal flight missions. The structure is simple, the operation is smoother, and it is more economical to use.

[0012] Furthermore, the spindle support is composed of a bearing support, a bearing, and a bearing seal; wherein the bearing support is composed of a support body and a bearing sleeve, the support body is a conical hollow frame structure, the support body is provided with a support mounting hole matching the body structure, and is installed on the body structure through a support fixing piece; the bearing sleeve is a concave hollow structure, the center of which is provided with a rotating spindle through hole and the diameter is larger than the spindle and smaller than the inner ring of the bearing, the bearing sleeve and the bearing are a matching structure, and the support body and the bearing sleeve are an integrally formed structure; the bearing seal is a hollow seal plate structure, the hollow part is a cylindrical seal sleeve, the inner diameter of the seal sleeve and the spindle are a matching structure, a seal positioning hole corresponding to the spindle is provided on the seal sleeve, a number of reinforcing ribs are provided between the hollow seal plate and the seal sleeve, the hollow seal plate, the seal sleeve and the reinforcing ribs are an integral structure, and the bearing seal is fixed to the spindle by a seal limit pin through the seal positioning hole and the spindle positioning hole. This design is beneficial for the positioning, installation, calibration and adjustment of the main shaft on the fuselage. It can also effectively control the lateral limit of the main shaft to prevent the main shaft from moving left and right due to uneven force on the two wings, causing unstable flight.

[0013] Further, the wing interface is one or more combinations of plug-in connection, bolt connection, screw connection, and angle-variable joint. This design is conducive to matching different types of wings and loads.

[0014] Furthermore, the wing is a combination of one or more types of fixed wing, folding wing, and composite wing, adapted to the wings of different types of aircraft;

[0015] One or more combinations of horizontal thrusters / vertical thrusters are arranged on the rotating wing, which are adapted to power outputs of different types and directions; wherein when the horizontal thrusters are arranged on the rotating wing, the auxiliary control function of the left-right balance and the rolling motion of the aircraft is realized in the helicopter flight state through the differential of the power of the horizontal thrusters on the left and right wings, and the auxiliary control function of the left-right steering of the aircraft is realized in the fixed-wing flight; in addition, when the vertical thrusters are arranged on the rotating wing, the auxiliary control function of the left-right steering of the aircraft is realized in the helicopter flight state through the control of the power of the vertical thrusters on the left and right wings, and the auxiliary control function of the left-right balance and the rolling motion of the aircraft is realized in the fixed-wing flight;

[0016] One or more combinations of ailerons / elevators / rudders are set on the wings, so that it has the function of assisting the aircraft in left and right turning, front and rear translation, left and right translation, pitch, and roll motion control flight in both flight modes, further improving the aircraft's maneuverability in different flight states.

[0017] Furthermore, the transmission part is a turbine worm gear structure; the turbine (driven wheel) is a fan-shaped wheel structure, the keyway is installed on the inner side of the fan surface of the fan-shaped wheel, limit gears are set at both ends of the outer fan surface of the fan wheel, and the driven wheel wing angle of attack zero position baseline is set between the limit gears according to the design requirements, and the position of the limit gear and the driven wheel wing angle of attack zero position baseline is adjustable; an assembly baseline is set on the driven wheel, and the driven wheel assembly baseline is consistent with the shaft sleeve assembly baseline and the main shaft wing angle of attack zero position baseline; the driven wheel is fixed to the main shaft by a special shaft sleeve, a key, a limit pin, and a main shaft positioning hole. This design utilizes the low power, high torque and self-locking ability of the worm gear to reduce the power and weight of the servo motor, save energy consumption, and increase the overload capacity of air vibration caused by air disturbance, which is beneficial to flight stability; setting a limit gear to prevent the aircraft from entering an irreversible control state is a flight safety guarantee, and the adjustable gear is suitable for different aircraft models, making this set of components versatile and standardized; setting the wing angle of attack zero baseline and the driven wheel assembly baseline on the driven wheel is conducive to rapid assembly and ensuring installation accuracy, and is easy to calibrate with the factory initial standard during maintenance, reducing flight safety hazards.

[0018] Furthermore, the rotating main shaft is a hollow shaft and is provided with a main shaft pipeline through hole. The hollow shaft is conducive to the passage and layout of pipelines from the inside of the machine body to the outside of the machine body. Similarly, the hollow shaft can also reduce its weight under the same torque conditions; when the main shaft pipeline through hole is set on the inner side of the sleeve / bearing seal, a corresponding sleeve pipeline through hole is also set at the corresponding position of the sleeve / bearing seal sleeve. This design uses the principle that the sleeve has a compensatory effect on the main shaft structural strength, so that the sleeve pipeline through hole is set at the inner side of the sleeve / bearing seal sleeve corresponding to the main shaft position to minimize the impact on the main shaft strength.

[0019] The beneficial effects achieved by the utility model are:

[0020] The utility model realizes the smooth conversion between the helicopter flight mode and the fixed-wing flight mode through the innovative rotating wing structure design, optimizes the flight performance, improves the flight safety and flexibility, and provides a new idea and solution for the development of aviation aircraft technology.

[0021] First, the utility model designs a helicopter flight mode and a fixed-wing flight mode to achieve a smooth transition. The rotary wing structure provided by the utility model can flexibly switch between the helicopter flight mode and the fixed-wing flight mode to meet different flight requirements. In the helicopter mode, the aircraft can perform vertical take-off and landing and hover; in the fixed-wing mode, the aircraft can cruise efficiently. This dual-mode design greatly improves the versatility and flexibility of the aircraft.

[0022] Second, the fixed-wing wing surface can rotate to optimize flight performance. During vertical takeoff and landing, the fixed-wing wing surface rotates into a vertical plane perpendicular to the fuselage, which can significantly reduce the wind resistance generated by the rotor downwash and improve flight efficiency. In the fixed-wing flight state, the wing surface rotates to a horizontal position, which can generate maximum lift and enhance level flight performance.

[0023] Third, a rudder is installed on the fixed wing to improve the heading control performance. In the fixed wing mode, by adjusting the angle of the rudder, the heading of the aircraft can be effectively controlled to improve the flight stability and maneuverability.

[0024] Fourth, in helicopter flight mode, the propeller downwash airflow is set in the forward direction to reduce the sinking force. In helicopter mode, the propeller downwash airflow is set in the forward direction of the fixed wing, which minimizes the sinking force of the airflow on the fixed wing and improves the stability and safety of vertical take-off and landing.

[0025] Fifth, by rotating the fixed-wing to change the angle of attack, the flight performance can be optimized. By adjusting the angle of attack of the fixed-wing, it can adapt to different flight conditions and mission requirements, improve the flight performance of the aircraft, and make the aircraft more adaptable to complex and changeable flight environments.

[0026] Sixth, the vertical propellers and horizontal propellers share the same power system. This design simplifies the complexity of the power system, reduces the weight of the aircraft, improves energy efficiency, and reduces maintenance and operating costs.

[0027] Seventh, rotating fixed wings provide more auxiliary control methods and improve flight safety and reliability. By rotating fixed wings and adding thrusters, ailerons, rudders and other devices, the aircraft has more control methods during flight, especially in helicopter mode and take-off and landing phases, which greatly improves the accuracy and safety of flight.

[0028] Eighth, in helicopter mode, the movement and balance of the fuselage can be achieved by rotating the fixed wings at a small angle. In helicopter mode, the forward and backward movement and longitudinal dynamic balance of the fuselage can be achieved by fine-tuning the angle of the fixed wings, which improves the flexibility and stability of flight.

[0029] Ninth, the body roll and balance adjustment are achieved through the power differential of the left and right thrusters. In helicopter mode, the power differential of the left and right thrusters can be used to flexibly adjust the body's roll and balance state, enhancing the diversity and accuracy of flight control.

[0030] Tenth, ailerons (elevators) are added to the rotating fixed wings to achieve left and right steering and forward and backward movement. The addition of ailerons makes it possible to achieve left and right steering of the aircraft through differential operation of the left and right ailerons in helicopter mode; at the same time, synchronously opening the aileron rudder angles in the same direction can also achieve forward and backward movement of the aircraft, further improving the controllability of the flight.

[0031] Eleventh, the rotating fixed wing adds a rudder to achieve left and right movement of the fuselage. In helicopter mode, by synchronously opening the rudder angle in the same direction, the left and right translation of the fuselage can be achieved, enhancing the maneuverability and flexibility of the aircraft.

[0032] 12. In fixed-wing mode, steering is achieved by rotating the fixed wing to increase the propeller power differential. In fixed-wing mode, by adjusting the propeller power differential on the fixed wing, torque can be generated to cause the fuselage to turn. This control method is similar to traditional fixed-wing aircraft, but combines the advantages of rotating fixed wings to improve overall control performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a schematic diagram of the structure of the utility model;

[0034] Figure 2 This is a schematic diagram of the installation structure of the servo system of the utility model;

[0035] Figure 3 This is a schematic diagram of the installation of the bearing bracket of the utility model;

[0036] Figure 4 This is a large-scale drawing of the bearing bracket of the utility model;

[0037] Figure 5 This is a large-scale drawing of the installation structure of the main shaft and the driven wheel of the utility model;

[0038] Figure 6 This is a large-scale drawing of the wing structure of the utility model;

[0039] Figure 7 This is a schematic diagram of the flight mode control of the helicopter of the utility model;

[0040] Figure 8 It is a schematic diagram of the fixed-wing flight mode control of the utility model.

[0041] Numbers in the figure:

[0042] 1. Rotating spindle; 1-1. Spindle; 1-1-2. Wing connection hole; 1-1-3. Spindle positioning hole; 1-1-4. Bushing; 1-1-5. Limit pin; 1-1-6. Key; 1-1-7. Spindle pipeline through hole; 1-1-8. Bushing pipeline through hole; 1-1-9. Bushing positioning hole; 1-1-10. Bushing keyway; 1-1-11. Spindle wing angle of attack zero baseline; 1- 1-12, shaft sleeve assembly baseline; 1-2, spindle bracket; 1-2-1, bearing bracket; 1-2-1-1, bracket body; 1-2-1-2, bearing sleeve; 1-2-1-3, bracket mounting hole; 1-2-2, bearing; 1-2-3, bearing seal; 1-2-3-1, seal piece; 1-2-3-2, seal sleeve; 1-2-3-3, seal reinforcement rib; 1-2-3-4 , sealing positioning hole; 1-2-3-5, sealing pipeline passing hole; 1-2-4, sealing limit pin; 1-2-5, bearing bracket fixing piece; 2, servo system; 2-1, servo motor; 2-2, driving wheel; 2-3, driven wheel; 2-4, bearing bracket; 2-5, fixing piece; 2-6, limit gear; 2-7, coupling; 2-8, driven wheel wing angle of attack zero baseline; 2-9, driven wheel assembly baseline; 2-10, driven wheel keyway; 3, wing; 3-1, wing mainboard; 3-2, elevator; 3-3, wing interface; 3-4, thruster; 3-5, rudder; 3-6, folding wing interface; 4, fuselage structure; 4-1, fuselage bulkhead; 4-2, fuselage longitudinal beam; 4-3, fuselage transverse beam; 4-4, fuselage connecting plate; 4-5, skin; 5, flight control. DETAILED DESCRIPTION

[0043] The technical solution of the utility model will be clearly and completely described below in conjunction with the drawings in the utility model. In addition, the forms of the various structures recorded in the following embodiments are merely illustrative, and the utility model is not limited to the various structures recorded in the following embodiments. All other implementations obtained by ordinary technicians in this field without making creative work belong to the scope of protection of the utility model.

[0044] Reference Figure 1-Figure 8 , a rotating wing 3 structure, which includes a rotating main shaft 1, a servo motor 2-1, a transmission part, a main shaft bracket 1-2, a wing 3, and a flight control 5, wherein:

[0045] The rotating spindle 1 is mounted on the spindle bracket 1-2, the spindle bracket 1-2 is mounted on the fuselage structure 4, and the wing 3 is mounted on the outer interface of the rotating spindle 1 through the wing interface 3-3;

[0046] The servo motor 2-1 controls the rotation of the main shaft 1 through the transmission part, thereby driving the wing 3 part to rotate;

[0047] The flight control 5, the servo motor 2-1 and the transmission part constitute the servo system 2;

[0048] The rotating wing 3 structure has a helicopter flight mode and a fixed-wing flight mode, and the two modes can be controlled and converted through the servo system 2.

[0049] The rotating main shaft 1 is provided with a wing connecting hole 1-1-2, a main shaft positioning hole 1-1-3, a shaft sleeve 1-1-4, and a main shaft wing angle of attack zero position baseline 1-1-11; the shaft sleeve 1-1-4 is provided with a keyway (1-1-10), a limiting hole (1-1-9), and a shaft sleeve assembly baseline 1-1-12; the shaft sleeve 1-1-4 is installed in conjunction with the transmission part, and the shaft sleeve assembly baseline 1-1-12 is consistent with the main shaft wing angle of attack zero position baseline 1-1-11.

[0050] The rotating spindle 1 is a left-right split structure, and the servo system 2 is also two sets of corresponding structures. The servo system 2 has the function of separately controlling and synchronously controlling the two sets of left-right split rotating spindles 1.

[0051] The spindle support 1-2 is composed of a bearing support 1-2-1, a bearing 1-2-2, and a bearing seal 1-2-3; wherein the bearing support 1-2-1 is composed of a support body 1-2-1-1 and a bearing sleeve 1-2-1-2; the support body 1-2-1-1 is a conical hollow frame structure; the support body 1-2-1-1 is provided with a support mounting hole 1-2-1-3 which matches with the machine body structure 4, and is mounted on the machine body structure 4 through a support fixing member 2-5; the bearing sleeve 1-2-1-2 is a concave hollow structure, and a rotating spindle 1 through hole whose diameter is larger than the spindle 1-1 and smaller than the inner ring of the bearing 1-2-2 is provided in the center; the bearing sleeve 1-2-1-2 and the bearing 1-2-2 are a matching structure; the support body 1-2-1-1 and the bearing sleeve 1-2 -1-2 is an integrally formed structure; the bearing seal 1-2-3 is a hollow seal plate 1-2-3-1 structure, the hollow part is a cylindrical seal sleeve 1-2-3-2, the inner diameter of the seal sleeve 1-2-3-2 is a matching structure with the main shaft 1-1, a seal positioning hole 1-2-3-4 corresponding to the main shaft 1-1 is arranged on the seal sleeve 1-2-3-2, a plurality of reinforcing ribs (1-2-3-3) are arranged between the hollow seal plate 1-2-3-1 and the seal sleeve 1-2-3-2, the hollow seal plate 1-2-3-1, the seal sleeve 1-2-3-2 and the reinforcing ribs (1-2-3-3) are an integral structure, and the bearing seal 1-2-3 is fixed to the main shaft 1-1 by a seal limit pin 1-2-4 through the seal positioning hole 1-2-3-4 and the main shaft positioning hole 1-1-3.

[0052] The wing interface 3-3 of the utility model is one or more combinations of plug-in connection, bolt connection, screw connection, and angle-variable joint. The wing 3 is one or more combinations of fixed wing, folding wing, and composite wing. The transmission part is a turbine worm structure; the turbine (driven wheel 2-3) is a fan-shaped wheel structure, the driven wheel keyway 2-10 is installed on the inner side of the fan-shaped wheel fan surface, and limit gears 2-6 are set at both ends of the outer fan surface of the fan-shaped wheel 2-3. A driven wheel wing angle of attack zero position baseline 2-8 is set between the limit gears 2-6 according to design requirements, and the position of the limit gear 2-6 and the driven wheel wing angle of attack zero position baseline 2-8 are adjustable; a driven wheel assembly baseline 2-9 is set on the driven wheel 2-3, and the driven wheel assembly baseline 2-9 is consistent with the shaft sleeve assembly baseline 1-1-12 and the main shaft wing angle of attack zero position baseline 1-1-11; the driven wheel 2-3 is fixed to the main shaft 1-1 through a special shaft sleeve 1-1-4, a key 1-1-6, a limit pin 1-1-5, and a main shaft positioning hole 1-1-3.

[0053] The rotating spindle 1 is a hollow shaft and is provided with a spindle pipeline through hole 1-1-7; when the spindle pipeline through hole 1-1-7 is arranged on the inner side of the sleeve 1-1-4 / bearing seal 1-2-3, corresponding sleeve pipeline through holes 1-1-8 and seal pipeline through holes (1-2-3-5) are also arranged at the corresponding positions of the sleeve 1-1-4 / bearing seal 1-2-3 and the sleeve 1-1-4.

[0054] The rotating spindle 1 is mounted on the spindle bracket 1-2, the spindle bracket 1-2 is mounted on the fuselage structure 4, and the wing 3 is mounted on the rotating spindle 1 outside the fuselage through the wing interface 3-3; this split structure design is convenient for assembly and maintenance, and the vulnerable parts can also be replaced regularly according to the wear and tear and service life;

[0055] The servo motor 2-1 controls the rotation of the rotating main shaft 1 through the transmission part, thereby driving the wing 3 part to rotate; this design allows the wing 3 plane to freely switch between the vertical and horizontal planes. When the wing 3 plane is in a vertical state with the aircraft plane, it can greatly reduce the sinking force of the downwash airflow on the wing 3, fuselage, etc. when the aircraft is in the working state of the rotor; when the wing 3 plane is in a parallel state with the aircraft plane, it ensures that the fixed wing of the aircraft generates sufficient lift in the level flight state, increases the endurance of the aircraft, improves the economic performance of the aircraft, and also significantly improves the aircraft's service ceiling and high-altitude wind resistance.

[0056] The flight control 5, servo motor 2-1 and transmission part constitute the servo system 2. The servo system 2 mainly forms a closed-loop control on the flight attitude of the wing 3, ensuring a smooth transition between the helicopter flight state and the fixed-wing flight state, and further improving the aircraft's maneuverability and flight stability.

[0057] The wing 3 structure has a helicopter flight mode and a fixed-wing flight mode, and the two modes are controllably switched through the servo system 2. The rotating wing 3 structure is to solve the problem that the wing 3 has a helicopter flight mode and a fixed-wing flight mode, and the two modes are safely and smoothly switched.

[0058] A horizontal propeller 3-4 or a vertical propeller 3-4 is arranged on the wing 3, wherein when the horizontal propeller 3-4 is arranged on the rotating wing 3, the auxiliary control function of the left-right balance and the rolling motion of the aircraft is realized in the helicopter flight state through the differential power of the horizontal propeller 3-4 on the left and right wings 3, and the auxiliary control function of the left-right steering of the aircraft is realized in the fixed-wing flight; in addition, when the vertical propeller 3-4 is arranged on the rotating wing 3, the auxiliary control function of the left-right steering of the aircraft is realized in the helicopter flight state through the control of the power of the vertical propeller 3-4 on the left and right wings 3, and the auxiliary control function of the left-right balance and the rolling motion of the aircraft is realized in the fixed-wing flight;

[0059] One or more combinations of ailerons / elevators 3-2 / rudders 3-5 are arranged on the wing 3, so that it has the functions of assisting the aircraft in left and right steering, front and rear translation, left and right translation, pitch, and roll motion control of flight.

[0060] Furthermore, the rotating main shaft 1 is provided with a wing connection hole 1-1-2, a main shaft positioning hole 1-1-3, a sleeve 1-1-4, and a main shaft wing angle of attack zero position baseline 1-1-11. The sleeve 1-1-4 is provided with a keyway 1-1-10, a limit hole 1-1-9, and a sleeve assembly baseline 1-1-12. The sleeve assembly baseline 1-1-12 is consistent with the main shaft wing angle of attack zero position baseline 1-1-11. The driven wheel 2-3 is fixed to the main shaft 1-1 through a special sleeve 1-1-4, a key 1-1-6, a limit pin 1-1-5, and a main shaft positioning hole 1-1-3. This design makes the rotating main shaft 1 convenient to install and fix, and the sleeve 1-1-4 is used to assist in strengthening the structure of the opening part, so that the main shaft 1-1 can still maintain sufficient strength despite processing, opening holes, etc., and also takes into account the connection and fixation of the supporting parts.

[0061] Furthermore, when the rotating main shaft 1 is a left-right split structure, the servo system 2 is also two sets of corresponding structures, and the servo system 2 has the function of controlling the two sets of left-right split rotating main shafts 1 separately and synchronously. This design is mainly to meet the requirements of different types of aircraft control performance. For example, for fighters with high maneuverability requirements, when the rotating main shaft 1 adopts a left-right split structure, the differential of the left and right wings 3 can quickly achieve tactical actions such as turning, rolling, and dogfighting, while ordinary transport aircraft can use a rotating main shaft 1 with an integrated structure to meet normal flight tasks. The structure is simple, the operation is smoother, and it is more economical to use.

[0062] Furthermore, the spindle support 1-2 is composed of a bearing support 1-2-1, a bearing 1-2-2, and a bearing seal 1-2-3; wherein the bearing support 1-2-1 is composed of a support body 1-2-1-1 and a bearing sleeve 1-2-1-2, the support body 1-2-1-1 is a conical hollow frame structure, the support body 1-2-1-1 is provided with a support mounting hole 1-2-1-3 which cooperates with the machine body structure 4, and is installed on the machine body structure 4 through a support fixing member 1-2-5; the bearing sleeve 1-2-1-2 is a concave hollow structure, the center of which is provided with a rotating spindle 1 through hole and the diameter of which is larger than the spindle 1-1 and smaller than the inner ring of the bearing 1-2-2, the bearing sleeve 1-2-1-2 and the bearing 1-2-2 are a matching structure, the support body 1-2-1-1 and the bearing The sleeve 1-2-1-2 is an integrally formed structure; the bearing seal 1-2-3 is a hollow seal piece 1-2-3-1 structure, the hollow part is a cylindrical seal sleeve 1-2-3-2, the inner diameter of the seal sleeve 1-2-3-2 is a matching structure with the main shaft 1-1, a seal positioning hole 1-2-3-4 corresponding to the main shaft 1-1 is arranged on the seal sleeve 1-2-3-2, a plurality of reinforcing ribs 1-2-3-3 are arranged between the hollow seal piece 1-2-3-1 and the seal sleeve 1-2-3-2, the hollow seal piece 1-2-3-1, the seal sleeve 1-2-3-2 and the reinforcing rib 1-2-3-3 are an integral structure, and the bearing seal 1-2-3 is fixed to the main shaft 1-1 by a seal limit pin 1-2-4 through the seal positioning hole 1-2-3-4 and the main shaft positioning hole 1-1-3. This design is beneficial to the positioning, installation, calibration and adjustment of the main shaft 1-1 on the fuselage. It can also effectively control the lateral limit of the main shaft 1-1 to prevent the main shaft 1-1 from moving left and right due to uneven force on the two wings, thus causing unstable flight.

[0063] Furthermore, the wing interface 3-3 is one or more combinations of plug-in connection, bolt connection, screw connection, and angle-variable joint; this design is conducive to matching different types of wings 3 and loads.

[0064] Furthermore, the wing 3 is one or more combinations of fixed wings, folding wings, and composite wings; adapted to different types of wings 3; one or more combinations of horizontal thrusters 3-4 and vertical thrusters 3-4 are arranged on the wing 3, adapted to power output of different types and directions; one or more combinations of elevators 3-2 and rudders 3-5 are arranged on the wing 3, so that it has the functions of left and right steering, front and rear translation, left and right translation, and pitch control, further improving the maneuverability of the aircraft under different flight conditions.

[0065] Furthermore, the transmission part is a turbine worm structure; the turbine (driven wheel 2-3) is a fan-shaped wheel structure, the driven wheel keyway 2-10 is installed on the inner side of the fan surface of the fan-shaped wheel, and limit gears 2-6 are set at both ends of the outer fan surface of the fan wheel. A driven wheel wing angle of attack zero baseline 2-8 is set between the limit gears 2-6 according to design requirements, and the position of the limit gear 2-6 and the driven wheel wing angle of attack zero baseline 2-8 are adjustable; an assembly baseline is set on the driven wheel 2-3, and the driven wheel assembly baseline 2-9 is consistent with the shaft sleeve assembly baseline 1-1-12 and the main shaft wing angle of attack zero baseline 1-1-11; the driven wheel 2-3 is fixed to the main shaft 1-1 by a special shaft sleeve 1-1-4, a key 1-1-6, a limit pin 1-1-5, and a main shaft positioning hole 1-1-3. This design utilizes the low power and high torque and self-locking ability of the worm gear to reduce the power and weight of the servo motor 2-1, save energy consumption, and improve the overload capacity of the air flow caused by air disturbance vibration, which is beneficial to flight stability; setting the limit gear 2-6 to prevent the aircraft from entering an irreversible control state is a flight safety guarantee, and the adjustable gear is suitable for different models, making this set of components have good versatility and can be standardized for application; setting the wing 3 angle of attack zero baseline 2-8 and the driven wheel assembly baseline 2-9 on the driven wheel 2-3 is conducive to rapid assembly and ensuring installation accuracy, and is convenient for calibration with the factory initial standard during maintenance, reducing flight safety hazards.

[0066] Furthermore, the rotating main shaft 1 is a hollow shaft and is provided with a main shaft 1-1 pipeline passing hole. The hollow shaft is conducive to the passing and layout of pipelines from the inside of the machine body to the outside of the machine body. Similarly, the hollow shaft can also reduce its weight under the same torque conditions; when the main shaft 1-1 pipeline passing hole is set on the inner side of the sleeve 1-1-4 / bearing seal 1-2-3, corresponding sleeve pipeline passing holes 1-1-8 and seal pipeline passing holes 1-2-3-5 are also set at the corresponding positions of the sleeve 1-1-4 / bearing seal 1-2-3 sleeve 1-1-4. This design uses the principle that the sleeve 1-1-4 has a compensatory effect on the structural strength of the main shaft 1-1, so that the sleeve pipeline passing hole 1-1-8 is set at the inner side of the sleeve 1-1-4 / bearing seal 1-2-3 sleeve 1-1-4 corresponding to the position of the main shaft 1-1, which minimizes the impact on the strength of the main shaft 1-1.

[0067] The utility model provides a method for assembling a rotating wing 3 structure: the servo system 2 includes a turbine worm structure, and the specific steps are as follows:

[0068] S1. Installation of driven wheel 2-3: Insert sleeve 1-1-4 into spindle 1-1 so that sleeve positioning hole 1-1-9 is aligned with spindle positioning hole 1-1-3, then put key 1-1-6 into sleeve keyway 1-1-10 of sleeve 1-1-4, then pass driven wheel 2-3 through spindle 1-1 so that keyway 1-1-10 of driven wheel 2-3 is aligned with key 1-1-6, insert into sleeve 1-1-4, adjust sleeve assembly baseline 1-1-12 of driven wheel 2-3 with spindle machine The wing attack angle zero position baseline 1-1-11 is consistent, and the driven wheel 2-3 is locked to the left and right limits by using limit pins 1-1-5 to pass through the bushing positioning hole 1-1-9 and the main shaft positioning hole 1-1-3 on both sides of the driven wheel 2-3; if the main shaft pipeline through hole 1-1-7 and the bushing pipeline through hole 1-1-8 are provided at this position, the limit pin 1-1-5 is installed after the two are aligned; if the main shaft 1-1 is a split structure, a set of driven wheels 2-3 can be installed on the left and right main shafts 1-1 respectively.

[0069] S2. Assembly of the spindle support 1-2; first, insert the bearing seal 1-2-3 from one end of the spindle 1-1, so that the seal limit pin 1-2-4 hole on the seal sleeve 1-2-3-2 is aligned with the spindle positioning hole 1-1-3 of the spindle 1-1. If a spindle pipeline through hole 1-1-7 is provided at this position, it should also be aligned with the seal pipeline through hole 1-2-3-5, and then the seal limit pin 1-2-4 is passed through the seal pipeline through hole 1-2-3-4 and the spindle positioning hole 1-1-3 respectively to limit and lock the bearing seal 1-2-3; then, insert the bearing 1-2-2 into the spindle 1-1 and push it to the position of the stopper 1-2-3-1 of the bearing seal 1-2-3, and then insert the support body 1-2-1-1 of the bearing support 1-2-1 into the spindle 1-1 and push it to the bearing seal 1-2 -3's baffle 1-2-3-1 position allows the bearing sleeve 1-2-1-2 to fit the bearing 1-2-2; after the main shaft bracket 1-2 at the other end is assembled by the same method and steps, the main shaft bracket 1-2 and the body structure 4 can be positioned and installed, and the bracket mounting holes 1-2-1-3 on the assembled main shaft bracket 1-2 mounting base are aligned with the mounting holes on the body connecting plate 4-4 corresponding to the body bulkhead 4-1, and the two sides of the main shaft bracket 1-2 are leveled and marked with reference marks, and then installed and fixed with the bearing bracket fixing part 1-2-5; in order to improve the structural strength, the body bulkhead 4-1 main shaft bracket 1-2 mounting position is connected and reinforced with the body longitudinal beam 4-2 and the body transverse beam 4-3 through structural support parts.

[0070] S3. Assembly of servo system 2: After the assembly of the main shaft bracket 1-2 is completed, the position of the driven wheel 2-3 is determined. First, connect the main shaft 1-1 of the servo motor 2-1 and the worm of the driving wheel 2-2 through the shaft coupling 2-7, and then preliminarily connect the bearing bracket 2-4 at the other end of the worm (driving wheel) with the body connecting plate 4-4 of the body transverse beam 4-3 through the fixing piece 2-5, and then insert the servo motor 2-1 and the worm (driving wheel) at the other end of the driving wheel 2-2 into the bearing bracket 2-4. In the process, adjust the matching clearance and initial position of the driving wheel 2-2 and the driven wheel 2-3, and then fix the servo motor 2-1 and the bearing bracket 2-4 on the body connecting plate 4-4 of the body transverse beam 4-3 with the fixing parts 2-5 respectively. Power on the servo motor 2-1 to test the engagement of the driving wheel 2-2 and the driven wheel 2-3 in forward and reverse rotation, and then accurately adjust the matching accuracy, synchronously detect the limit gear 2-6 switch of the driven wheel 2-3 and the driven wheel wing angle of attack zero baseline 2-8, and mark after the correction accuracy meets the standard;

[0071] S4, assembling of wing 3; after the assembly and calibration of the main shaft bracket 1-2 and the servo system 2 are completed, the wing 3 can be assembled. First, the perforated skin 4-5 of this part passes through the ports of the main shaft 1-1 on both sides of the fuselage and is installed and fixed to the fuselage bulkhead 4-1 or the stringer of the fuselage structure 4. If there are pipelines connected to the equipment lines on the wing 3, the corresponding pipeline joints must be connected first. After normal inspection, the wings 3 on both sides are connected and fixed to the connecting holes of the main shaft 1-1 through the wing interface 3-3. The flight control 5 and the servo system 2 are connected to test and calibrate the control performance of the wing 3, and the assembly of the rotating wing 3 structure is completed. The opposite operation is the disassembly process.

[0072] After assembly and debugging, in order to better illustrate the advantages and characteristics of this structure, the structural form of a tandem twin-rotor helicopter plus a rotating fixed wing is taken as an example to explain the control performance of the flight state, and a propeller 3-4, an elevator (aileron) 3-2, and a rudder 3-5 are added to the rotating fixed wing; the attack angle α of the wing 3 (including the rudder angle setting of the aileron or elevator 3-2) is set to be positive in the upward counterclockwise direction, and the rudder angle β of the rudder 3-5 is set to be positive in the counterclockwise direction; the working principle of a rotating wing 3 structure provided by the utility model in the helicopter flight mode and the fixed-wing flight mode is introduced respectively:

[0073] Helicopter flight mode: refer to Figure 1 , Figure 2 , Figure 6 , Figure 7 .

[0074] ①Vertical take-off and landing and hovering: reference Figure 7-A, the attack angle of the rotating fixed wing α=90°, the rudder angle β=0° of the rudder 3-5, the power and the total torque of the rotor and the rotating fixed wing propeller 3-4 are increased synchronously, when the comprehensive lift is greater than the weight of the aircraft at this time, the aircraft is in a take-off state, when the comprehensive lift is equal to the weight of the aircraft at this time, the aircraft is in a hovering state, when the comprehensive lift is less than the weight of the aircraft at this time, the aircraft is in a descending state, and the left and right balance attitude of the aircraft can be corrected by adjusting the power of the propeller 3-4 on the left and right rotating fixed wings;

[0075] ② Forward and backward: In the hovering state, when the angle of the rotating fixed wing α is changed from 90° to 70° and the rudder 3-5 rudder angle β = 0°, the aircraft has a horizontal pull forward and moves forward. On the contrary, when the angle of the rotating fixed wing α is changed from 90° to 110°, it moves backward. Figure 7 -B, 7-C;

[0076] ③ Left and right steering: When the angle of the rotating fixed wing α is 90° and the rudder angle β of rudder 3-5 is 0°, the right wing 3 ailerons are flipped toward the rear of the fuselage and the left wing 3 ailerons are flipped toward the front of the fuselage. Under the action of the downwash generated by the rotor (including the thrust propeller of propeller 3-4), the fuselage will turn to the left. Figure 7 -D, reverse operation will turn the machine to the right. Figure 7 -E;

[0077] ④ Left and right translation: When the angle of the rotating fixed wing α is 90°, by synchronously changing the rudder angle β of the rudder 3-5 to the right, the fuselage will translate to the left under the action of the downwash airflow generated by the rotor (including the thrust propeller of the propeller 3-4).

[0078] like Figure 7 -F, reverse operation will move the machine to the right. Figure 7 -G;

[0079] ⑤ Left and right roll measurement: When the angle of the rotating fixed wing α is 90° and the rudder 3-5 rudder angle β = 0°, the power of the left and right wings 3 propellers 3-4 is adjusted differentially to make the pulling force on both sides unbalanced, causing the body to tilt left and right and generate a side roll movement. For example, if the pulling force of the right wing propeller 3-4 is increased and the pulling force of the left wing propeller 3-4 is reduced, the body will roll to the left, and the reverse operation will roll to the right.

[0080] Fixed wing flight mode: refer to Figure 1 , Figure 2 , Figure 6 , Figure 8 ,

[0081] ① Level flight: When the angle of the rotating fixed wing α is 0°, the rudder 3-5 rudder angle β = 0°, the rotor is tilted forward or the thrust generated by the propellers 3-4 of the fixed wings on both sides is equal, and the lift generated by the rotor tilting forward and the fixed wings on both sides is equal to the weight of the aircraft, the aircraft is in a level flight state, such as Figure 8 -a;

[0082] ② Climb and dive: In level flight, by changing the angle of the rotating fixed-wing elevator 3-2α, the fuselage generates a rotational torque around the Y axis to change the flight attitude of the aircraft. The fixed-wing elevator 3-2α angle flips upward to generate a clockwise torque. The aircraft is in a climbing state when its head is raised upward. Figure 8 -c; The fixed-wing elevator flips downward at an angle of 3-2α, generating a counterclockwise torque, and the aircraft is in a dive state with its head down. Figure 8 -b;

[0083] ③ Left and right steering: In the level flight state, by changing the rudder angle β of the rotating fixed wing 3-5, the aircraft body generates a rotational torque around the Z axis to change the aircraft's flight attitude, and by changing the rudder angle β of the rotating fixed wing left wing 3-5, the aircraft turns left, such as Figure 8 -d; change the right rudder angle of the rotating fixed wing by 3-5 degrees β, and the aircraft turns right, such as Figure 8 -e; The aircraft can also be turned by differentially changing the power of the left and right fixed-wing propellers 3-4. For example, if the power of the right fixed-wing propeller 3-4 is increased and the power of the left fixed-wing propeller 3-4 is reduced, the aircraft can be turned left. Otherwise, the aircraft can be turned right.

[0084] ④ Left and right translation: In the level flight state, by synchronously changing the rudder angle β of the left and right wings of the rotating fixed wing in the same direction, the rotation moments around the Z axis generated by the aircraft body are offset, and the lateral thrust generated on the aircraft body is retained to cause the aircraft to translate left and right (the actual movement is a side slip). For example, if the rudder angle β of the left and right wings of the rotating fixed wing is synchronously changed to deflect to the right, the aircraft translates to the left. Figure 8 -f; Synchronous reverse operation, the aircraft will move to the right, such as Figure 8 -g;

[0085] ⑤ Roll motion: In level flight, the α angles of the left and right ailerons of the rotating fixed wing are changed differentially, so that the fuselage generates a rotational torque around the X-axis to change the flight attitude of the aircraft and generate roll motion. For example, if the α angle of the right aileron of the rotating fixed wing is flipped upward and the α angle of the left aileron of the rotating fixed wing is flipped downward, the fuselage rotates right around the X-axis and generates a right-side roll motion. The reverse operation generates a left-side roll motion.

[0086] Flight mode conversion:

[0087] ① Convert from helicopter flight mode to fixed-wing flight mode: In helicopter flight mode, place the aircraft at a safe flight altitude, change the angle of the rotating fixed wing α from 90° to 70°, return the rudder angle β of 3-5 to 0°, increase the level flight speed and balance attitude of the aircraft, and then gradually change the angle of the rotating fixed wing α from 70° to 0°, and maintain stable flight to complete the conversion from helicopter flight mode to fixed-wing flight mode;

[0088] ② Convert from fixed-wing flight mode to helicopter flight mode: In the fixed-wing flight mode, return the rudder angle β of rudder 3-5 to 0°, adjust the power of rotating fixed-wing propeller 3-4 to low power state or zero output, increase the vertical lift of the rotor to reach the weight of the aircraft while reducing the level flight speed, so that the aircraft is in a hovering or low-speed flight state, and then send a command to the servo system 2 through the flight control system 5 to gradually transition the angle of the rotating fixed wing α from 0° to 90°, and adjust the power of the rotating fixed-wing propeller 3-4 to adapt to the helicopter flight mode.

[0089] Finally, a few points should be explained: First, in the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, and can be mechanical or electrical connections, or internal connectivity between two components, or direct connection. "Up", "down", "left", "right", etc. are only used to indicate relative position relationships. When the absolute position of the described object changes, the relative position relationship may change; secondly: in the drawings of the embodiments disclosed in the present invention, only the structures involved in the embodiments disclosed in the present invention are involved, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other; finally: the above is only the preferred embodiment of the present invention, and is not used to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A rotary wing structure, characterized in that: It comprises a rotating spindle (1), a servo motor (2-1), a transmission part, a spindle support (1-2), a wing (3), and a flight control (5), wherein: The rotating main shaft (1) is mounted on a main shaft bracket (1-2), the main shaft bracket (1-2) is mounted on a body structure (4), and the wing (3) is partially mounted on an outer interface of the rotating main shaft (1) via a wing interface (3-3); The servo motor (2-1) controls the rotation of the rotating main shaft (1) through the transmission part, thereby driving the wing (3) part to rotate; The flight control (5), the servo motor (2-1) and the transmission part constitute a servo system (2); The rotary wing structure has a helicopter flight mode and a fixed-wing flight mode, and the two modes can be controlled and switched through a servo system (2).

2. The rotary wing structure according to claim 1, characterized in that: The rotating main shaft (1) is provided with a wing connection hole (1-1-2), a main shaft positioning hole (1-1-3), a shaft sleeve (1-1-4), and a main shaft wing angle of attack zero position baseline (1-1-11); the shaft sleeve (1-1-4) is provided with a keyway (1-1-10), a limit hole (1-1-9), and a shaft sleeve assembly baseline (1-1-12); the shaft sleeve (1-1-4) is installed in conjunction with the transmission part, and the shaft sleeve assembly baseline (1-1-12) is consistent with the main shaft wing angle of attack zero position baseline (1-1-11).

3. The rotary wing structure according to claim 1, characterized in that: The rotating spindle (1) is a left-right split structure, and the servo system (2) is also two sets of corresponding structures. The servo system (2) controls the two sets of left-right split rotating spindles (1) separately or synchronously.

4. The rotary wing structure according to claim 1, characterized in that: The spindle support (1-2) is composed of a bearing support (1-2-1), a bearing (1-2-2), and a bearing seal (1-2-3); wherein the bearing support (1-2-1) is composed of a support body (1-2-1-1) and a bearing sleeve (1-2-1-2); the support body (1-2-1-1) is a conical hollow frame structure; the support body (1-2-1-1) is provided with a support mounting hole (1-2-1-1) that matches the machine body structure (4) 1-2-1-3), and is installed on the machine body structure (4) through a bracket fixing member (1-2-5); the bearing sleeve (1-2-1-2) is a concave hollow structure, and a rotating main shaft (1) passing hole with a diameter larger than the main shaft (1-1) and smaller than the inner ring of the bearing (1-2-2) is arranged at the center; the bearing sleeve (1-2-1-2) and the bearing (1-2-2) are a matching structure, and the bracket body (1-2-1-1) and the bearing sleeve (1-2- 1-2) is an integrally formed structure; the bearing seal (1-2-3) is composed of a hollow seal plate (1-2-3-1), a seal sleeve (1-2-3-2) and a reinforcing rib (1-2-3-3), wherein the inner diameter of the seal sleeve (1-2-3-2) and the main shaft (1-1) are a matching structure, and the seal sleeve (1-2-3-2) is provided with a seal positioning hole (1-2-3-4) corresponding to the main shaft (1-1), and the hollow seal plate (1-2 A plurality of reinforcing ribs (1-2-3-3) are arranged between the bearing block (1-3-1) and the sealing sleeve (1-2-3-2); the hollow sealing piece (1-2-3-1), the sealing sleeve (1-2-3-2) and the reinforcing ribs (1-2-3-3) are an integrated structure; the bearing sealing (1-2-3) is fixed on the main shaft (1-1) by means of a sealing limiting pin (1-2-4) through a sealing positioning hole (1-2-3-4) and a main shaft positioning hole (1-1-3).

5. The rotary wing structure according to claim 1, characterized in that: The wing interface (3-3) is one or more combinations of plug-in connection, bolt connection, screw connection, and angle-variable joint.

6. The rotary wing structure according to claim 1, characterized in that: The wing (3) is one or more combinations of fixed wings, folding wings, and composite wings; the rotating wing is provided with a horizontal propeller or a vertical propeller; the wing is provided with one or more combinations of ailerons, elevators, and rudders.

7. The rotary wing structure according to claim 1, characterized in that: The transmission part is a turbine worm structure; the turbine is a fan-shaped wheel structure; the driven wheel keyway (2-10) is installed on the inner side of the fan-shaped wheel fan surface; limit gears (2-6) are arranged at both ends of the fan-shaped wheel outer fan surface; a driven wheel wing angle of attack zero position baseline (2-8) is arranged between the limit gears (2-6) according to design requirements; the limit gears (2-6) and the driven wheel wing angle of attack zero position baseline (2-8) are adjustable in position; a driven wheel assembly baseline (2-9) is arranged on the driven wheel (2-3); the driven wheel assembly baseline (2-9) is consistent with the shaft sleeve assembly baseline (1-1-12) and the main shaft wing angle of attack zero position baseline (1-1-11); the driven wheel (2-3) is fixed on the main shaft (1-1) through a special shaft sleeve (1-1-4), a key (1-1-6), a limit pin (1-1-5) and a main shaft positioning hole (1-1-3).

8. The rotary wing structure according to claim 1, characterized in that: The rotating main shaft (1) is a hollow shaft and is provided with a main shaft pipeline passing hole (1-1-7); when the main shaft pipeline passing hole (1-1-7) is located inside the shaft sleeve (1-1-4) / bearing seal (1-2-3), corresponding shaft sleeve pipeline passing holes (1-1-8) and seal pipeline through holes (1-2-3-5) are also provided at corresponding positions of the shaft sleeve (1-1-4) / bearing seal (1-2-3) and the main shaft (1-1) pipeline passing hole (1-1-7).

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