Double-guide-rail type rigid high-speed variable-sweepback wing

Abstract

The invention belongs to the field of variable sweepback aircraft wing mechanism design, and particularly relates to a double-guide-rail type rigid high-speed variable sweepback wing. Comprising a fuselage connecting part, and the fuselage connecting part is provided with a fixed support and a wing rotating shaft penetrating through the fixed support; the front edge of the root of the movable wing is connected with the wing rotating shaft through a bearing, and the movable wing can rotate around the wing rotating shaft to change the sweepback angle; the transmission mechanism is connected between the fuselage connecting part and the movable wings and is used for driving the movable wings to rotate; the guide assembly is arranged between the fuselage connecting part and the root of the movable wing, the guide assembly comprises an arc-shaped double guide rail arranged on the fuselage connecting part and a sliding block arranged in the middle section of the root of the movable wing, and the sliding block is slidably embedded in the arc-shaped double guide rail and used for providing guidance in the sweepback changing process of the movable wing; and the thermal protection sealing assembly is arranged at a relative movement gap between the movable wing and the fuselage connecting part.

Description

Technical Field

[0001] This application belongs to the field of variable sweep aircraft wing mechanism design, and specifically relates to a dual-rail rigid high-speed variable sweep wing. Background Technology

[0002] Aircraft aerodynamic performance is crucial to its loiter time. For multi-purpose / high-speed aircraft, variable-sweep wing technology enables good aerodynamic efficiency in various scenarios and is one of the key technologies in the design of such aircraft. Traditional variable-sweep wing mechanisms generally adopt a single-rail sliding mechanism around a major axis of rotation, which has a simple mechanical structure, direct force transmission, and high practicality.

[0003] However, as the flight speed of new-generation aircraft gradually increases, the flight service environment becomes more severe, and strong vibrations caused by aerodynamics and heat are difficult to avoid. Traditional single-rail variator mechanisms have weak vibration resistance due to insufficient support stiffness, and cannot guarantee the safety and reliability of the variator process at high speeds. At the same time, the thermal structure and thermal protection design of the variator mechanism in high-speed environments are also technical challenges.

[0004] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Summary of the Invention

[0005] The purpose of this application is to provide a dual-rail rigid high-speed variable-sweep wing to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] A dual-rail rigid high-speed variable-sweep wing includes:

[0008] The fuselage connection part is provided with a fixed support and a wing rotation shaft passing through the fixed support;

[0009] A movable wing, the leading edge of which is connected to the wing rotation axis via a bearing, and is capable of rotating about the wing rotation axis to change the sweep angle;

[0010] A transmission mechanism is connected between the fuselage connection portion and the movable wing, and is used to drive the movable wing to rotate;

[0011] A guide assembly is disposed between the fuselage connection portion and the root of the movable wing. The guide assembly includes an arc-shaped double guide rail disposed in the fuselage connection portion and a slider disposed in the middle section of the root of the movable wing. The slider is slidably fitted onto the arc-shaped double guide rail and is used to provide guidance during the variable sweep of the movable wing.

[0012] A thermal protection sealing assembly is disposed at the relative movement gap between the movable wing and the fuselage connection.

[0013] In at least one embodiment of this application, the leading edge of the movable wing is made of a high-temperature resistant carbon-carbon composite material.

[0014] In at least one embodiment of this application, the bearing is a deep groove ball bearing.

[0015] In at least one embodiment of this application, the transmission mechanism is a drive that includes a worm gear mechanism.

[0016] In at least one embodiment of this application, the arc-shaped double guide rail is made of brass.

[0017] In at least one embodiment of this application, the mating surfaces of the arc-shaped double guide rail and the slider adopt a T-shaped mating structure.

[0018] In at least one embodiment of this application, the thermal protection sealing assembly includes:

[0019] A sealing block is slidably installed in a groove of the movable wing, and the sealing block can move with the change of thickness or position of the movable wing to maintain a close fit;

[0020] A high-temperature felt is connected to the sealing block via a spring, which provides the high-temperature felt with an elastic force that keeps it pressed against the surface of the movable wing.

[0021] The invention has at least the following beneficial technical effects:

[0022] The dual-rail rigid high-speed variable-sweep wing of this application can be applied to the variator mechanism design of high-speed variable-sweep aircraft. While improving the load-bearing capacity and stability of the variator mechanism, it also increases its heat insulation and heat load-bearing performance, thereby ensuring that the variator mechanism can work safely and reliably in high-speed environments and avoiding the risk of accidents. Attached Figure Description

[0023] Figure 1 This is an overall schematic diagram of a dual-rail rigid high-speed variable-sweep wing according to one embodiment of this application;

[0024] Figure 2 This is a schematic diagram of the leading edge of a movable wing according to one embodiment of this application;

[0025] Figure 3 This is a schematic diagram of the transmission mechanism of one embodiment of this application from one angle;

[0026] Figure 4 This is a schematic diagram of the connection between a movable wing and a transmission mechanism according to one embodiment of this application;

[0027] Figure 5 This is a schematic diagram of the transmission mechanism according to one embodiment of this application from another angle;

[0028] Figure 6 This is a third-angle schematic diagram of the transmission mechanism according to one embodiment of this application;

[0029] Figure 7 This is a schematic diagram of a guide component according to one embodiment of this application at an angle;

[0030] Figure 8 This is another schematic diagram of the guide component according to one embodiment of this application;

[0031] Figure 9 This is a schematic diagram of a slider according to one embodiment of this application;

[0032] Figure 10 This is a schematic diagram of a heat protection sealing assembly according to one embodiment of this application from an angle;

[0033] Figure 11 Another schematic diagram of a thermal protection sealing assembly according to one embodiment of this application.

[0034] in:

[0035] 1-Fuselage connection; 2-Mobility wing; 3-Transmission mechanism; 31-Turbine; 32-Worm; 33-Main shaft; 34-Driver; 4-Guide assembly; 41-Arc-shaped double guide rail; 42-Slider; 5-Thermal protection sealing assembly; 51-Spring; 52-High temperature felt. Detailed Implementation

[0036] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0037] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0038] The following is in conjunction with the appendix Figures 1 to 11 This application will be described in further detail.

[0039] This application provides a dual-rail rigid high-speed variable-sweep wing, including: a fuselage connection part 1, a movable wing 2, a transmission mechanism 3, a guide assembly 4, and a thermal protection sealing assembly 5.

[0040] Specifically, such as Figure 1-2 As shown, the fuselage connection 1 is equipped with a fixed support and a wing rotation shaft passing through the fixed support; the leading edge of the root of the movable wing 2 is connected to the wing rotation shaft via a bearing and can rotate around the wing rotation shaft to change the sweep angle. By arranging a rotating shaft at the leading edge of the root of the movable wing 2 and connecting it to the fuselage connection 1, the axial and radial loads during flight are carried by the rotating bearing to improve its stability. The shaft center serves as the rotation center of the movable wing 2. The movable wing 2 is connected to the wing rotation shaft via a pair of deep groove ball bearings. The movable wing 2 achieves changes in sweep angle under the drive of the transmission mechanism 3. Considering the high temperature of the leading edge of the movable wing 2 during high-speed flight, it is preferable that the leading edge of the movable wing 2 is made of high-temperature resistant carbon-carbon composite material, which can withstand high temperatures while reducing heat transfer to the wing interior.

[0041] like Figure 3-6 As shown, the transmission mechanism 3 is connected between the fuselage connection part 1 and the movable wing 2, and is used to drive the movable wing 2 to rotate. Considering that the movable wing 2 is always subjected to a large load during the flight of the aircraft, the transmission mechanism 3 is required to have reliable stability and load-bearing capacity. In the preferred embodiment of this application, a transmission mechanism 3 with self-locking characteristics is selected. The transmission mechanism 3 includes a turbine 31, a worm gear 32, a main shaft 33, and a driver 34. The driver, which includes the turbine-worm gear mechanism, serves as the transmission scheme of the variable sweep angle structure mechanism and can be locked at any angle. In this embodiment, the transmission mechanism 3 can be locked at any angle between 16° and 72°. An ear-shaped structure extends from the root of the movable wing 2 as part of the variable sweep angle transmission mechanism 3, with the center of the ear-shaped structure serving as the rotation center of the variable sweep angle. Driven by the driver 34, the movable wing 2 achieves servo movement within the active space of the fuselage connection part. The transmission area is located inside the fuselage and is connected to the fixed frame inside the fuselage through the main shaft 33. The movable wing 2 is connected to the turbine 31 of the transmission section by bolts.

[0042] Considering that the transmission mechanism 3 occupies as little internal space as possible, a circular arc tooth worm gear transmission mechanism with characteristics such as high load-bearing capacity, high transmission efficiency, and small size is selected. Weight-reduction holes are also designed to further reduce volume and weight. During high-speed flight, the aircraft generates severe vibrations. To maintain the stability of the movable wing 2, the transmission part is required to have sufficient rigidity and stability. Therefore, a double-end support scheme is adopted for the worm 32. Both ends of the worm 32 are fixed to bearing seats, and axial positioning is achieved through set screws. The bearing seats are fixedly installed to the fuselage via connecting bases.

[0043] like Figure 7-9 As shown, the guide assembly 4 is disposed between the fuselage connection 1 and the root of the movable wing 2. The guide assembly includes an arc-shaped double guide rail 41 disposed in the fuselage connection 1 and a slider 42 disposed in the middle section of the root of the movable wing 2. The slider 42 is slidably fitted onto the arc-shaped double guide rail 41 to provide guidance during the sweep-back process of the movable wing 2. The mating surface of the arc-shaped double guide rail 41 and the slider 42 adopts a T-type fit structure, and a gap is provided at the contact point to prevent mechanical jamming caused by thermal load. In this embodiment, by arranging two sets of guide assemblies 4 between the fuselage connection 1 and the movable wing 2, the load-bearing and vibration resistance of the movable wing 2 is improved. To prevent the transmission mechanism 3 from deforming, reducing transmission efficiency, or jamming when the wing structure is subjected to longitudinal aerodynamic loads during flight, a dual-rail transmission scheme was designed. Two sets of upper and lower guide rails and a slider 42 fixedly connected to the root of the movable wing 2 are designed in the middle and rear section of the fuselage frame structure. These can respectively bear the aerodynamic forces and torques generated by the movable wing 2 in the spanwise and chordwise directions, ensuring that the worm gear has a smooth transmission state.

[0044] In a preferred embodiment of this application, the slider 45 is connected to the movable wing 2 by bolts, and protrusions are designed on the upper and lower surfaces of the slider 45. An arc-shaped double guide rail 41 is placed at a corresponding position on the lower base plate of the fuselage connection part 1. When the movable wing 2 is subjected to aerodynamic loads, the movable wing 2 transfers a portion of the normal load to the lower base plate of the fuselage connection part 1 through the slider 41, thereby reducing the torque on the main shaft 33. Simultaneously, during the change of sweep angle of the movable wing 2, the arc-shaped double guide rail 41 can also maintain the stability of the wing's rotation trajectory. Preferably, the arc-shaped double guide rail 41 is made of brass to reduce the frictional force generated when the wing changes sweep angle.

[0045] Furthermore, such as Figure 10-11As shown, the thermal protection sealing assembly 5 is disposed at the relative movement gap between the movable wing 2 and the fuselage connection 1. The movable wing 2 has a groove for installing the thermal protection sealing assembly 5. The thermal protection sealing assembly includes a sealing block and a high-temperature felt 52. The sealing block is slidably installed in the groove of the movable wing 2 and can move with changes in the thickness or position of the movable wing 2 to maintain a close fit. The high-temperature felt 52 is connected to the sealing block via a spring 51, which provides elastic force to keep the high-temperature felt 52 pressed firmly against the surface of the movable wing 2. To address the sealing problem between the movable wing 2 and the fuselage connection 1 during sweep-off rotation, elastic high-temperature felt is arranged at the openings in the rotating joint and the fuselage. During rotation, the movable wing 2 is tightly fitted with the high-temperature felt 52, effectively preventing external heat from entering the fuselage. During the rotation of the movable wing 2, the size of the fuselage opening changes continuously due to the changes in the thickness of the leading, trailing, and middle sections of the airfoil. To solve the sealing problem of the leading edge wing opening during rotation, a movable high-temperature felt that moves up and down along the slide is adopted. This solves the problem of inconsistent opening size of the leading edge wing during rotation, which leads to poor sealing. The spring 51 provides the closing thrust, so that the high-temperature felt 52 can always be in close contact with the upper and lower surfaces of the movable wing 2, avoiding the influence of gaps on the flow field.

[0046] This application discloses a dual-rail rigid high-speed variable-sweep wing, capable of variable-sweep operation under high-temperature and high-vibration environments. The dual-rail design enhances support rigidity to resist vibration; a worm gear mechanism is used to achieve wing sweep, improving actuation efficiency; elastic high-temperature felt is placed at the joints and fuselage openings to provide thermal insulation; and spring-supported movable high-temperature felt is laid within the grooves to prevent gaps from affecting aerodynamic performance. This application features good stability, high load-bearing capacity, and adaptability to high operating temperatures, ensuring successful implementation of the variable-sweep process during high-speed flight, and provides valuable reference for aircraft design.

[0047] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A dual-rail rigid high-speed variable-sweep wing, characterized in that, include: The fuselage connection part is provided with a fixed support and a wing rotation shaft passing through the fixed support; A movable wing, the leading edge of which is connected to the wing rotation axis via a bearing, and is capable of rotating about the wing rotation axis to change the sweep angle; A transmission mechanism is connected between the fuselage connection portion and the movable wing, and is used to drive the movable wing to rotate; A guide assembly is disposed between the fuselage connection portion and the root of the movable wing. The guide assembly includes an arc-shaped double guide rail disposed in the fuselage connection portion and a slider disposed in the middle section of the root of the movable wing. The slider is slidably fitted onto the arc-shaped double guide rail and is used to provide guidance during the variable sweep of the movable wing. A thermal protection sealing assembly is disposed at the relative movement gap between the movable wing and the fuselage connection.

2. The dual-rail rigid high-speed variable-sweep wing according to claim 1, characterized in that, The leading edge of the movable wing is made of high-temperature resistant carbon-carbon composite material.

3. The dual-rail rigid high-speed variable-sweep wing according to claim 1, characterized in that, The bearing is a deep groove ball bearing.

4. The dual-rail rigid high-speed variable-sweep wing according to claim 1, characterized in that, The transmission mechanism is a drive that includes a worm gear mechanism.

5. The dual-rail rigid high-speed variable-sweep wing according to claim 1, characterized in that, The arc-shaped double guide rails are made of brass.

6. The dual-rail rigid high-speed variable-sweep wing according to claim 1, characterized in that, The mating surfaces of the arc-shaped double guide rails and the slider adopt a T-shaped fit structure.

7. The dual-rail rigid high-speed variable-sweep wing according to claim 1, characterized in that, The thermal protection sealing assembly includes: A sealing block is slidably installed in a groove of the movable wing, and the sealing block can move with the change of thickness or position of the movable wing to maintain a close fit; A high-temperature felt is connected to the sealing block via a spring, which provides the high-temperature felt with an elastic force that keeps it pressed against the surface of the movable wing.

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