CN117125247A - Coupling deformation mechanism device for push-out wing, unscrew wing and control wing and working method - Google Patents

Abstract

The invention relates to the technical field of design of variable aircraft, in particular to a coupling deformation mechanism device of a push-out wing, a unscrewing wing and an operating wing, which comprises the following components: the machine body comprises a machine body base plate, wherein frames are arranged on two sides of the machine body base plate, a unscrewing airfoil surface, a pushing airfoil surface and a control airfoil surface are arranged in the frames, unlocking grooves are formed in the unscrewing airfoil surface and the pushing airfoil surface, the pushing airfoil surface is provided with an initial position and a pushing position, and a telescopic transmission rod is arranged between the pushing airfoil surface and the control airfoil surface; the pushing mechanism is arranged on the machine body base plate and is connected with the pushing airfoil; the coupling deformation mechanism device of the push-out wing, the rotating-out wing and the control wing can adapt to various different flight environments by changing the overall pneumatic configuration of the aircraft in a large scale on the deformation scale, and greatly improves the overall pneumatic performance and the flight efficiency of the aircraft.

Description

Coupled deformation mechanism device and working method of push-out wing, spin-out wing and control wing

Technical field

The invention relates to the technical fields of variable-body aircraft design, wing surface deformation mechanism design, and aircraft mechanism transmission technology. Specifically, it relates to a coupling deformation mechanism device and working method of a push-out wing, a swing-out wing and a control wing.

Background technique

Modern aircraft are developing towards high Mach numbers, high maneuverability, and ultra-long attack range, which requires them to be able to adapt to a variety of flight modes: subsonic flight, transonic flight, supersonic flight, etc., and should have good controllability , maneuverability, good lift-to-drag ratio, large pitch angle range, stable flight and easy control and other performance requirements. However, the aerodynamic shape of a simple fixed-wing aircraft is difficult to meet the above requirements, so deformable airfoils have become a hot topic in domestic and foreign research. Deformable airfoils are mainly divided into expandable airfoils, folding airfoils, and flexible deformable airfoils. The deformed airfoil can adapt to the aircraft's different flight conditions and provide better aerodynamic lift-to-drag ratio characteristics. By changing the lift surface of the airfoil, it can increase flight lift, improve fuel utilization, and thus increase flight distance.

The difficulties in the structural design of morphing aircraft are: 1. The internal structure design problem of the morphing wing with large deformation and high load-bearing capacity; 2. The deformation decision-making problem of the morphing wing under different flight conditions; 3. Extremely high Mach Drive control and stiffness maintenance issues under airfoil deformation. Technical means such as multi-disciplinary optimal design, intelligent materials and structural design provide feasible ideas for the research of morphing aircraft.

Large-scale deformation of aircraft is the most effective, reliable and direct deformation method of morphing aircraft. At this stage, the mature deformation methods of aircraft are mainly local small deformation and medium-scale deformation, which have certain limitations on the overall flight mode of the aircraft and do not greatly improve the flight efficiency of the aircraft. Large-scale deformation of an aircraft mainly changes the overall aerodynamic configuration of the aircraft to meet the requirements of different flight modes. The most typical deformation method is to use the wings, the main aerodynamic lift component of the aircraft, as the deformation object, and large-scale deformation has a negative impact on the aircraft. The shape and structure have the greatest impact, and also change the aerodynamic performance of the aircraft the most.

Contents of the invention

Therefore, the present invention provides a coupling deformation mechanism device and a working method of a push-out wing, a swing-out wing and a control wing.

In order to solve the above technical problems, the present invention provides a coupling deformation mechanism device for a push-out wing, a swing-out wing and a control wing, which includes: a fuselage base plate, frames are provided on both sides of the fuselage base plate, and a frame is provided inside the frame. There are a spin-out airfoil and a push-out airfoil, as well as a control airfoil. The spin-out airfoil and the push-out airfoil are provided with unlocking grooves. The push-out airfoil has an initial position and a push-out position. The push-out airfoil and A telescopic transmission rod is provided between the control wing surfaces; a push-out mechanism is provided on the fuselage base plate, and the push-out mechanism is connected to the push-out wing surface; an unlocking mechanism is provided on the fuselage base plate The unlocking mechanism includes an unlocking lever and a flexible unlocking component. The unlocking lever is provided with an unlocking boss. The unlocking boss is adapted to the unlocking groove. The flexible unlocking component unlocks or locks the unlocking groove. The unlocking groove and the unlocking boss, the swing-out airfoil and the push-out airfoil are switched between the initial position and the push-out position; a one-way transmission mechanism is provided on the fuselage base plate, and the one-way transmission mechanism is connected with the The telescopic transmission rod is connected and drives the control airfoil to rotate relative to the push-out airfoil.

Further, there are multiple unlocking levers, and the plurality of unlocking levers are located on both sides of the fuselage base plate and are arranged at intervals.

Further, the flexible unlocking component includes: a tension spring, located on one end of the fuselage base plate; a locking device, located on the other end of the fuselage base plate, and a flexible drawstring is connected to the locking device. and unlocking lever, and tension spring.

Further, the push-out mechanism includes: a plurality of fixed blocks staggered on the fuselage base plate; a guide rod inserted into the fixed block, and one end of the guide rod is connected to the push-out wing. surface connection; a thrust rod is located in the middle of the fuselage base plate, and the thrust rod pushes the push-out airfoil toward both sides of the fuselage base plate.

Further, the one-way transmission mechanism includes a driving component and a one-way transmission component. The driving component is connected to the one-way transmission component, and the one-way transmission component is connected to the telescopic transmission rod.

Further, the driving assembly includes a servo motor and a planetary reducer, and both the servo motor and the planetary reducer are provided on the fuselage substrate.

Further, the one-way transmission assembly includes a worm gear and a worm, and a base. The worm gear and the worm are arranged on the base. The worm is connected to the planetary reducer, and the worm gear is connected to the telescopic transmission rod.

Further, a rotating shaft is provided in the telescopic transmission rod, and the rotating shaft is connected to the worm gear.

Further, a hollow portion is provided on the fuselage substrate, and the one-way transmission mechanism is provided in the hollow portion.

The invention also provides a working method of the coupling deformation mechanism device using the push-out wing, the swing-out wing and the control wing, including:

When locking, the inside of the frame is set before the deformation of the unscrewed and pushed out airfoils. The unlocking lever cooperates with the unlocking groove of the unscrewed and pushed out airfoils through the unlocking boss. The pressure required for the design index is designed according to the flight conditions. Tightening force, adjust the flexible unlocking component and have the tensioning force. The unlocking rod acts on the spin-out and push-out airfoils, eliminating the gap between the spin-out and push-out airfoils, and improving the stability of the spin-out and push-out airfoils. Stiffness, fundamental frequency;

When unlocking, the flexible unlocking component triggers the unlocking, and the flexible unlocking component unlocks the unlocking groove and the unlocking boss, and the unscrewed airfoil and push-out airfoil jointly push out to both sides of the fuselage base plate under the action of the push-out mechanism, and produce deformation;

When the deformation command is received, the control wing surface is pushed out to both sides of the fuselage base plate together with the push-out wing surface. After reaching the position, the one-way transmission mechanism drives the control wing surface to rotate relative to the push-out wing surface.

The technical solution of the present invention has the following advantages:

1. The coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing provided by the present invention includes: a fuselage base plate, frames are provided on both sides of the fuselage base plate, and a swing-out wing surface and a swing-out wing surface are provided in the frame. The push-out airfoil and the control airfoil are provided with unlocking grooves. The push-out airfoil has an initial position and a push-out position. There is an unlocking groove between the push-out airfoil and the control airfoil. There is a telescopic transmission rod; a push-out mechanism located on the fuselage base plate, and the push-out mechanism is connected to the push-out wing surface; an unlocking mechanism, the unlocking mechanism is disposed on the fuselage base plate, and the unlocking mechanism It includes an unlocking lever and a flexible unlocking component. The unlocking lever is provided with an unlocking boss. The unlocking boss is adapted to the unlocking groove. The flexible unlocking component unlocks or locks the unlocking groove and the unlocking boss. platform, the swing-out airfoil and the push-out airfoil are switched between the initial position and the push-out position; a one-way transmission mechanism is provided on the fuselage base plate, and the one-way transmission mechanism is connected with the telescopic transmission rod, And drive the control airfoil to rotate relative to the push-out airfoil.

By setting frames on both sides of the fuselage base plate, and installing the swing-out wing surface, push-out wing surface, and control wing surface on the frame; the swing-out wing surface, push-out wing surface, and control wing surface are all set on the frame in the initial state. In the push-out state, the push-out airfoil is pushed out of the frame through the push-out mechanism. At the same time, the swing-out airfoil and the control airfoil are pushed out of the frame together, that is, the push-out airfoil reaches the push-out position from the initial position. The push-out wing surface reaches the push-out position from the initial position, and is unlocked by the unlocking mechanism. The unlocking lever is set on the fuselage base plate and the unlocking groove set on the swing-out wing surface and the push-out wing surface is unlocked, that is, the flexible unlocking component The unlocking boss on the driving unlocking rod slides out from the unlocking groove, thereby realizing the unlocking of the swing-out and push-out airfoils, and facilitating the push-out of the swing-out and push-out airfoils, as well as the control airfoils from the frame. The one-way transmission mechanism is then used to connect with the telescopic transmission rod arranged between the push-out airfoil and the control airfoil, that is, the one-way transmission mechanism is used to drive the telescopic transmission rod to rotate, thereby realizing the rotation of the control airfoil relative to the push-out airfoil.

The coupling deformation mechanism of the push-out wing, the swing-out wing and the control wing is installed on the deformation scale to change the overall aerodynamic configuration of the aircraft on a large scale. It can adapt to a variety of different flight environments and greatly improve the overall aerodynamic performance and flight performance of the aircraft. Efficiency; at the same time, the deformation method is novel, with a small space layout, compact structure, and good vibration and impact resistance; in addition, the push-out mechanism is small in size, has large output force, and is quickly actuated to quickly and effectively move the movable airfoil under the guidance of It is pushed out in a straight line, and the guide adopts the form of a guide rod and a fixed block. The mechanism is simple and effective, and conforms to the actual flight conditions; the control wing can be linked with the push-out wing, and the deflection moment of the control wing is greatly improved through the one-way transmission mechanism, which is effective Improve the overall flight control level of the aircraft.

2. The coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing provided by the present invention, the flexible unlocking component includes: a tension spring, located on one end of the fuselage base plate; a locking device, located on the fuselage base plate. At the other end of the fuselage base plate, a flexible pull cord connects the locking device and the unlocking lever, as well as the tension spring.

The locking device is arranged on the fuselage base plate, and the locking device is connected to a flexible pull rope. According to the pressing force required by the design specifications of the flight conditions, the flexible pull rope is adjusted to have a tightening force, thereby unlocking the lever. It acts on the spin-out and push-out airfoils, eliminates the gaps between the spin-out and push-out airfoils, and improves their stiffness and fundamental frequency.

3. The coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing provided by the present invention. The push-out mechanism includes: a plurality of fixed blocks, which are staggered on the fuselage base plate; a guide rod inserted on the fuselage base plate. In the fixed block, one end of the guide rod is connected to the push-out airfoil; a thrust rod is located in the middle of the fuselage base plate, and the thrust rod pushes the push rod toward both sides of the fuselage base plate. Push out the airfoil.

The fixed blocks are staggered on the fuselage base plate, so that the guide rods can be inserted into the fixed blocks and guided. At the same time, one end of the guide rods is connected to push out the airfoil, and the thrust rod is used to push out the airfoil, and the guide rod is used to set At both ends of the push-out airfoil, the push-out of the push-out airfoil is realized.

This Summary is provided to introduce a selection of concepts in a simplified form that are further described below in the Detailed Description. This Summary is not intended to identify key features or essential features of the disclosure, nor is it intended to limit the scope of the disclosure.

Description of the drawings

In order to more clearly explain the specific embodiments of the present invention or the technical solutions in the prior art, the accompanying drawings that need to be used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings in the following description The drawings illustrate some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without exerting any creative effort.

Figure 1 is a schematic structural diagram of the initial position of the coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing provided by the present invention;

Figure 2 is a schematic structural diagram of the push-out position of the coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing provided by the present invention;

Figure 3 is an exploded view of the coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing provided by the present invention;

Figure 4 is a schematic structural diagram of the one-way transmission mechanism of the coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing provided by the present invention;

Figure 5 is a schematic structural diagram of the unlocking mechanism of the coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing provided by the present invention;

Figure 6 is a schematic structural view of the unlocking lever of the coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing provided by the present invention;

Figure 7 is a schematic structural diagram of the push-out wing surface of the coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing provided by the present invention;

Figure 8 is a schematic structural diagram of the swing-out wing surface of the coupling deformation mechanism device of the push-out wing, swing-out wing and control wing provided by the present invention.

Explanation of reference symbols:

1. Fuselage base plate; 2. Frame; 3. Swing-out wing surface; 4. Push-out wing surface; 5. Control wing surface; 6. Unlocking groove; 7. Telescopic transmission rod; 8. Push-out mechanism; 9. Unlocking mechanism ; 10. Unlocking lever; 11. Flexible unlocking component; 12. Unlocking boss; 13. One-way transmission mechanism; 14. Tension spring; 15. Locking device; 16. Flexible drawstring; 17. Fixed block; 18. Guide rod; 19. Thrust rod; 20. Servo motor; 21. Planetary reducer; 22. Worm gear; 23. Worm; 24. Base; 25. Rotating shaft; 26. Hollow part.

Detailed ways

In the following, only certain exemplary embodiments are briefly described. As those skilled in the art would realize, the described embodiments may be modified in various different ways without departing from the spirit or scope of the disclosure. Accordingly, the drawings and description are to be regarded as illustrative in nature and not restrictive.

In the description of the present disclosure, it needs to be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " The directions indicated by "back", "left", "right", "upright", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" etc. or The positional relationship is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present disclosure and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, Therefore, it is not to be construed as a limitation on the present disclosure. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features. Therefore, features defined as "first" and "second" may explicitly or implicitly include one or more of the described features. In the description of the present disclosure, "plurality" means two or more than two, unless otherwise explicitly and specifically limited.

In the description of the present disclosure, it should be noted that, unless otherwise clearly stated and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection or a detachable connection. Connection, or integral connection: it can be mechanical connection, electrical connection or mutual communication; it can be directly connected, or it can be indirectly connected through an intermediary, it can be the internal connection of two elements or the interaction of two elements relation. For those of ordinary skill in the art, the specific meanings of the above terms in this disclosure can be understood according to specific circumstances.

In this disclosure, unless otherwise expressly stated and limited, a first feature "on" or "below" a second feature may include the first and second features in direct contact, or may include the first and second features. Not in direct contact but through additional characteristic contact between them. Furthermore, the terms "above", "above" and "above" the first feature "above" the second feature include the first feature being directly above and diagonally above the second feature, or simply means that the first feature is higher in level than the second feature. "Below", "below" and "beneath" the first feature of the second feature includes the first feature being directly above and diagonally above the second feature, or simply means that the first feature is less horizontally than the second feature.

The following disclosure provides many different embodiments or examples for implementing various structures of the present disclosure. To simplify the disclosure of the present disclosure, the components and arrangements of specific examples are described below. Of course, they are merely examples and are not intended to limit the disclosure. Furthermore, this disclosure may repeat reference numbers and/or reference letters in different examples, such repetition being for purposes of simplicity and clarity and does not by itself indicate a relationship between the various embodiments and/or arrangements discussed. Furthermore, this disclosure provides examples of various specific processes and materials, but one of ordinary skill in the art will recognize the application of other processes and/or the use of other materials.

Preferred embodiments of the present disclosure will be described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described here are only used to illustrate and explain the present disclosure, and are not intended to limit the present disclosure.

Referring to Figures 1 to 8, the present invention provides a coupling deformation mechanism device for a push-out wing, a swing-out wing and a control wing, which includes: a fuselage base plate 1 with frames on both sides of the fuselage base plate 1 2. The frame 2 is provided with a swing-out wing surface 3, a push-out wing surface 4, and a control wing surface 5. The swing-out wing surface 3 and push-out wing surface 4 are provided with an unlocking groove 6. The push-out wing surface The surface 4 has an initial position and a push-out position. A telescopic transmission rod 7 is provided between the push-out wing surface 4 and the control wing surface 5; a push-out mechanism 8 is provided on the fuselage base plate 1, and the push-out mechanism 8 is connected to the fuselage base plate 1. The push-out wing surface 4 is connected; an unlocking mechanism 9 is provided on the fuselage base plate 1. The unlocking mechanism 9 includes an unlocking lever 10 and a flexible unlocking component 11. The unlocking lever 10 is provided with Unlocking boss 12, the unlocking boss 12 is adapted to the unlocking groove 6, the flexible unlocking component 11 unlocks or locks the unlocking groove 6 and the unlocking boss 12, the swing-out airfoil 3 and the push-out airfoil 4 switches between the initial position and the push-out position; the one-way transmission mechanism 13 is provided on the fuselage base plate 1, the one-way transmission mechanism 13 is connected to the telescopic transmission rod 7, and drives all The control airfoil 5 rotates relative to the push-out airfoil 4 .

By setting the frame 2 on both sides of the fuselage base plate 1, and installing the swing-out wing surface 3, the push-out wing surface 4, and the control wing surface 5 on the frame 2; the swing-out wing surface 3, the push-out wing surface 4, and the control wing surface 5 are all set in the frame 2 in the initial state. In the push-out state, the push-out airfoil 4 is pushed out of the frame 2 through the push-out mechanism 8. At the same time, the swing-out airfoil 3 and the control airfoil 5 are pushed out of the frame 2 together. That is, the push-out airfoil 4 reaches the push-out position from the initial position. The push-out wing surface 4 reaches the push-out position from the initial position, and is unlocked by the unlocking mechanism 9. The unlocking lever 10 provided on the fuselage base plate 1 is between the unlocking groove 6 provided on the swing-out wing surface 3 and the push-out wing surface 4. To unlock, that is, the flexible unlocking component 11 drives the unlocking boss 12 on the unlocking rod 10 to slide out of the unlocking groove 6, thereby realizing the unlocking of the unscrewed airfoil 3 and the push-out airfoil 4, making it easier to unscrew the unscrewed airfoil 3. The push-out airfoil 4 and the control airfoil 5 are pushed out from the frame 2, and then the one-way transmission mechanism 13 is used to connect with the telescopic transmission rod 7 provided between the push-out airfoil 4 and the control airfoil 5, that is, the one-way transmission mechanism 13 is used to connect the push-out airfoil 4 and the control airfoil 5. The transmission mechanism 13 drives the telescopic transmission rod 7 to rotate, thereby realizing the rotation of the control airfoil 5 relative to the push-out airfoil 4 .

The coupling deformation mechanism of the push-out wing, the swing-out wing and the control wing is installed on the deformation scale to change the overall aerodynamic configuration of the aircraft on a large scale. It can adapt to a variety of different flight environments and greatly improve the overall aerodynamic performance and flight performance of the aircraft. Efficiency; at the same time, the deformation method is novel, has a small space layout, compact structure, and good vibration and impact resistance; and, the push-out mechanism 8 is small in size, has large output force, can be actuated quickly, and can quickly and effectively move the movable airfoil in the guiding role It is pushed out in a straight line, and the guide is in the form of a guide rod 18 and a fixed block 17. The mechanism is simple and effective and conforms to the actual flight conditions; the control wing 5 can be linked with the push-out wing 4, and the control is greatly improved through the one-way transmission mechanism 13 The deflection moment of the wing effectively improves the overall flight control level of the aircraft.

In some optional embodiments, there are multiple unlocking levers 10 , and the multiple unlocking levers 10 are located on both sides of the fuselage base plate 1 and are arranged at intervals.

Through the arrangement of the unlocking lever 10, the unlocking boss 12 on the unlocking lever 10 can be used to cooperate with the unlocking groove 6 on the unscrewing airfoil 3 and the push-out airfoil 4, thereby realizing the unscrewing and pushing-out of the airfoil 3. The locking and unlocking of the airfoil 4 facilitates the switching of the unscrewed airfoil 3 and the push-out airfoil 4 between the initial position and the push-out position.

There are six unlocking levers 10 , which are respectively arranged on both sides of the fuselage base plate 1 . That is, three unlocking levers 10 are provided on one side of the fuselage base plate 1 .

In this embodiment, two unlocking levers 10 are provided on one side of the fuselage base plate 1 , that is, four unlocking levers 10 are provided on the fuselage base plate 1 , and the other two unlocking levers 10 are provided on the swing-out wing surface 3 .

In some optional embodiments, the flexible unlocking component 11 includes a tension spring 14, a lock 15, and a flexible drawstring 16; wherein the tension spring 14 is provided at one end of the fuselage base plate 1; The locking device 15 is provided at the other end of the fuselage base plate 1 , and a flexible drawstring 16 connects the locking device 15 to the unlocking lever 10 and the tension spring 14 .

The locking device 15 is arranged on the fuselage base plate 1, and the locking device 15 is connected to the flexible pull rope 16. According to the pressing force required by the flight condition design index, the flexible pull rope 16 is adjusted to have a tightening force. , so that the unlocking rod 10 acts on the swing-out airfoil 3 and the push-out airfoil 4, eliminating the gap between the swing-out airfoil 3 and the push-out airfoil 4, and improving its stiffness and fundamental frequency.

When unlocking, the unscrewing airfoil 3 and the pushing airfoil 4 need to be in an active state, and the pressing and limiting of the unlocking lever 10 need to be released. First, the locking device 15 is triggered to unlock and release the tension on the flexible rope 16. The unlocking rod 10 is stretched to one side under the action of the tension spring 14, thereby releasing the locking force between the unscrewed airfoil 3 and the push-out airfoil 4. With the cooperation of the unlocking boss 12 and the unlocking groove 6, the swing-out airfoil 3 and the push-out airfoil 4 deform outwards under the action of the push-out mechanism 8.

The flexible drawstring 16 has multiple sections, which are respectively connected to the two connected unlocking rods 10 .

The unlocker is arranged between two adjacent unlocking rods 10, and the unlocker is an SMA ball head lock 15. The SMA ball head lock 15 has a large bearing capacity, a fast release speed, and will not cause damage to the lock. Other electrical components cause magnetic interference.

In some optional embodiments, the push-out mechanism 8 includes: multiple fixed blocks 17, staggered on the fuselage base plate 1; guide rods 18 inserted into the fixed blocks 17, and One end of the guide rod 18 is connected to the push-out airfoil 4; a thrust rod 19 is located in the middle of the fuselage base plate 1, and the thrust rod 19 pushes the push-out airfoil 4 toward both sides of the fuselage base plate 1. Wing surface 4.

The fixed blocks 17 are staggered on the fuselage base plate 1, so that the guide rods 18 can be inserted into the fixed blocks 17 and guided. At the same time, one end of the guide rods 18 is connected to push out the airfoil 4, and the thrust rod 19 is used to push out the wing. surface 4, and use guide rods 18 to be arranged at both ends of the push-out airfoil 4, thereby realizing the push-out of the push-out airfoil 4.

Among them, a rotation axis 25 is provided at the connection between the push-out airfoil 4 and the swing-out airfoil 3, and the swing-out airfoil 3 rotates relative to the push-out airfoil 4 through the rotation axis 25.

In some optional embodiments, the one-way transmission mechanism 13 includes a driving component and a one-way transmission component, the driving component is connected to the one-way transmission component, and the one-way transmission component is connected to the telescopic transmission rod 7 .

Through the arrangement of the driving assembly, the driving assembly can be used to drive the one-way transmission assembly to rotate, and then drive the telescopic transmission rod 7 to rotate, so that the control wing surface 5 rotates relative to the push-out wing surface 4, and the rotation angle is ±30°.

In some optional embodiments, the driving assembly includes a servo motor 20 and a planetary reducer 21 , and both the servo motor 20 and the planetary reducer 21 are provided on the fuselage base plate 1 . Moreover, the one-way transmission assembly includes a worm gear 22 and a worm 23, and a base 24. The worm gear 22 and the worm 23 are provided on the base 24. The worm 23 is connected to the planetary reducer 21. The worm gear 22 and the telescopic transmission Rod 7 is connected.

The servo motor 20 and the planetary reducer 21 are an integral driving source. The planetary reducer 21 is installed at the front end of the servo motor 20, and the key shaft and the worm 23 are used to cooperate. The worm gear 22 and the worm 23 cooperate with each other, and the worm gear 22 and the worm 23 are used to achieve driving. steering and transmission;

Specifically, the telescopic transmission rod 7 can realize the deflection of the control wing surface 5. One end of the telescopic transmission rod 7 is fixed on the control wing, and the other end is fixed on the worm gear 22 and the worm 23 base 24.

In the initial state, the control wing surface 5 is set at the tail of the push-out wing surface 4, and before deformation, the push-out wing surface 4 and the control wing surface 5 are set inside the fuselage outer frame 2. When receiving the deformation command, the control wing surface 5 Along with the push-out airfoil 4, it is pushed outward. After reaching the position, the servo motor 20 makes the control airfoil 5 deflect at a positive or negative large angle through the worm gear 22, the worm 23, and the telescopic transmission rod 7.

In some optional embodiments, the telescopic transmission rod 7 is provided with a rotating shaft 25 , and the rotating shaft 25 is connected to the worm gear 22 . Through the arrangement of the rotating shaft 25, the rotation of the control airfoil 5 relative to the push-out airfoil 4 is realized, and the degree of freedom of rotation of the control airfoil 5 and the push-out airfoil 4 is increased.

In some optional embodiments, the fuselage substrate 1 is provided with a hollow portion 26 , and the one-way transmission mechanism 13 is provided in the hollow portion 26 . The arrangement of the hollow portion 26 reduces the overall mass of the fuselage substrate 1 and at the same time facilitates the installation of the one-way transmission mechanism 13 in the hollow portion 26 , providing an installation location for the one-way transmission mechanism 13 .

The invention also provides a working method of the coupling deformation mechanism of the push-out wing, the swing-out wing and the control wing, which includes:

When locking, the unscrewed airfoil 3 and the pushed-out airfoil 4 are set inside the frame 2 before deformation. The unlocking lever 10 cooperates with the unlocking groove 6 of the unscrewed airfoil 3 and the pushed-out airfoil 4 through the unlocking boss 12. According to the flight The pressing force required by the working condition design index is adjusted to the flexible unlocking component 11 and has a tightening force. The unlocking rod 10 acts on the unscrewed airfoil 3 and the pushed-out airfoil 4 to eliminate the unscrewed airfoil 3 and pushed-out airfoil. The gap of 4 increases the stiffness and fundamental frequency of the spin-out airfoil 3 and the push-out airfoil 4;

When unlocking, the flexible unlocking component 11 triggers unlocking. The flexible unlocking component 11 unlocks the unlocking groove 6 and the unlocking boss 12. The unscrewed airfoil 3 and the push-out airfoil 4 jointly move towards the fuselage under the action of the push-out mechanism 8. Both sides of the substrate 1 are pushed out and deformed;

When receiving the deformation command, the control wing surface 5 and the push-out wing surface 4 are pushed out to both sides of the fuselage base plate 1. After reaching the position, the one-way transmission mechanism 13 drives the control wing surface 5 to rotate relative to the push-out wing surface 4.

The specific working method of the coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing includes:

When locked, the swing-out wing surface 3, the push-out wing surface 4 and the control wing surface 5 are all located inside the frame 2, and the unlocking lever 10 connects with the unlocking groove 6 of the swing-out wing surface 3 and the push-out wing surface 4 through the unlocking boss 12 Cooperate with each other and adjust the locking device 15, the flexible pull rope 16, and the tension spring 14 according to the pressing force required by the flight condition design index, so that the flexible unlocking component 11 has a tightening force, and acts on the rotation through the unlocking lever 10. On the airfoil 3 and airfoil 4, eliminate the gap between airfoil 3 and airfoil 4, and improve the stiffness and fundamental frequency of airfoil 3 and airfoil 4;

When unlocking, adjust the locking device 15, the flexible drawstring 16, and the tension spring 14 to release the tension on the flexible drawstring 16. The unlocking lever 10 is stretched to one side under the action of the tension spring 14, thereby releasing the tension. Cooperating with the unlocking grooves 6 of the swing-out wing surface 3 and the push-out wing surface 4, the swing-out wing surface 3 and the push-out wing surface 4 jointly push out to both sides of the fuselage base plate 1 under the action of the push-out mechanism 8, and generate deformation;

When receiving the deformation command, the control wing surface 5 is pushed out to both sides of the fuselage base plate 1 together with the push-out wing surface 4. After reaching the position, the servo motor 20 drives the control through the worm gear 22, the worm 23, the telescopic transmission rod 7 and other transmission mechanisms. The airfoil 5 undergoes positive and negative large angle deflections.

Obviously, the above-mentioned embodiments are only examples for clear explanation and are not intended to limit the implementation. For those of ordinary skill in the art, other different forms of changes or modifications can be made based on the above description. An exhaustive list of all implementations is not necessary or possible. The obvious changes or modifications derived therefrom are still within the protection scope of the present invention.

Claims (10)

1. A coupling deformation mechanism device for a push-out wing, a swing-out wing and a control wing, which is characterized in that it includes: The fuselage base plate (1) is provided with frames (2) on both sides of the fuselage base plate (1). The frame (2) is provided with a swing-out airfoil (3), a push-out airfoil (4), and a control airfoil (4). 5), the unscrewing airfoil (3) and the push-out airfoil (4) are provided with unlocking grooves (6), the push-out airfoil (4) has an initial position and a push-out position, and the push-out airfoil (4) and the control airfoil are There is a telescopic transmission rod (7) between (5); The push-out mechanism (8) is located on the fuselage base plate (1), and the push-out mechanism (8) is connected to the push-out wing surface (4); The unlocking mechanism (9) is located on the fuselage base plate (1). The unlocking mechanism (9) includes an unlocking lever (10) and a flexible unlocking component (11). The unlocking lever (10) is provided with an unlocking protrusion. platform (12), the unlocking boss (12) matches the unlocking groove (6), the flexible unlocking component (11) unlocks or locks the unlocking groove (6) and the unlocking boss (12), and rotates out the airfoil ( 3) and the push-out airfoil (4) switch between the initial position and the push-out position; The one-way transmission mechanism (13) is located on the fuselage base plate (1). The one-way transmission mechanism (13) is connected to the telescopic transmission rod (7) and drives the control wing surface (5) to rotate relative to the push-out wing surface (4). . 2. The coupled deformation mechanism device of push-out wings, swing-out wings and control wings according to claim 1, characterized in that there are multiple unlocking levers (10), and the multiple unlocking levers (10) are located on the fuselage base plate (1 ) on both sides, and the intervals are set. 3. The coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing according to claim 2, characterized in that the flexible unlocking assembly (11) includes: Tension spring (14), located at one end of the fuselage base plate (1); The locking device (15) is located at the other end of the fuselage base plate (1), and the flexible drawstring (16) connects the locking device (15), the unlocking lever (10), and the tension spring (14). 4. The coupling deformation mechanism device of push-out wing, swing-out wing and control wing according to any one of claims 1-3, characterized in that the push-out mechanism (8) includes: There are multiple fixed blocks (17), which are staggered on the fuselage base plate (1); The guide rod (18) is inserted into the fixed block (17), and one end of the guide rod (18) is connected to the push-out airfoil (4); The thrust rod (19) is located in the middle of the fuselage base plate (1), and the thrust rod (19) pushes and pushes out the airfoil (4) toward both sides of the fuselage base plate (1). 5. The coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing according to claim 4, characterized in that the one-way transmission mechanism (13) includes a driving assembly and a one-way transmission assembly, and the driving assembly and the one-way transmission assembly The components are connected, and the one-way transmission component is connected with the telescopic transmission rod (7). 6. The coupling deformation mechanism device of push-out wing, swing-out wing and control wing according to claim 5, characterized in that the driving assembly includes a servo motor (20) and a planetary reducer (21), and the servo motor (20) and The planetary reducers (21) are all located on the fuselage base plate (1). 7. The coupling deformation mechanism device of push-out wing, swing-out wing and control wing according to claim 6, characterized in that the one-way transmission assembly includes a worm gear (22), a worm screw (23), and a base (24), and the worm gear (22) and the worm (23) are located on the base (24), the worm (23) is connected to the planetary reducer (21), and the worm gear (22) is connected to the telescopic transmission rod (7). 8. The coupling deformation mechanism device of push-out wing, swing-out wing and control wing according to claim 7, characterized in that the telescopic transmission rod (7) is provided with a rotating shaft (25), and the rotating shaft (25) and the worm gear (22) )connect. 9. The coupled deformation mechanism device of the push-out wing, the swing-out wing and the control wing according to claim 1, characterized in that the fuselage base plate (1) is provided with a hollow portion (26), and the one-way transmission mechanism (13) It is located in the hollow part (26). 10. A working method using the coupling deformation mechanism device of the push-out wing, the swing-out wing and the control wing according to any one of claims 1-9, characterized in that it includes: When locking, the unscrewed airfoil (3) and pushed-out airfoil (4) are set inside the frame (2) before deformation. The unlocking lever (10) communicates with the unscrewed airfoil (3) and pushed-out airfoil through the unlocking boss (12). The unlocking grooves (6) on the surface (4) cooperate with each other, and the flexible unlocking component (11) is adjusted to have a tightening force according to the pressing force required by the design specifications of the flight conditions, and the unlocking rod (10) acts to unscrew it. on the airfoil (3) and push-out airfoil (4), eliminate the gap between the spin-out airfoil (3) and push-out airfoil (4), and improve the stiffness of the spin-out airfoil (3) and push-out airfoil (4). Baseband; When unlocking, the flexible unlocking component (11) triggers unlocking, and the flexible unlocking component (11) unlocks the unlocking groove (6) and the unlocking boss (12), and rotates out the airfoil (3) and pushes out the airfoil (4) in the push-out mechanism. (8) are pushed together to both sides of the fuselage base plate (1) and deformed; When receiving the deformation command, the control wing surface (5) and the push-out wing surface (4) are pushed out to both sides of the fuselage base plate (1). After being in place, the one-way transmission mechanism (13) drives the control wing surface (5) to face each other. Push out the airfoil (4) to rotate.