A two-way unfolding mechanism for a folding wing with a skin support structure

Abstract

The invention relates to a bidirectional unfolding mechanism of a folding wing with a skin support structure, belonging to the field of folding wing design; the mechanism comprises an inner wing, an outer wing, a driving mechanism and n supporting devices; wherein the inner wing and the outer wing are placed opposite to each other, and a gap is left between the inner wing and the outer wing; the driving mechanism is located at the gap between the inner wing and the outer wing, and the outer wing is driven to rotate relative to the inner wing by the driving mechanism; the n supporting devices are horizontally arranged at the gap between the inner wing and the outer wing, and each supporting device is evenly distributed on both sides of the driving mechanism with the driving mechanism as the center; the n supporting devices realize auxiliary support between the inner wing and the outer wing; the invention has a large reduction ratio, can reduce the power demand of the driver, and can provide a connection and fixing function of the outer structure and a supporting function of the skin at the bending part, and is suitable for a high-speed variant aircraft structure with high dimensional requirements, limited configurable driving torque, and the need for bidirectional folding.

Description

Technical Field

[0001] The invention belongs to the field of folding wing design and relates to a folding wing bidirectional unfolding mechanism with a skin support structure. Background Art

[0002] For aircraft with a flight speed higher than Ma1, they will experience a low-speed takeoff and landing stage and a high-speed cruising flight stage in their flight mission profile. In order to achieve higher flight performance, each stage requires a different aerodynamic shape. For example, in the low-speed takeoff and landing stage, the aircraft needs to have a larger aspect ratio to increase the lift level. At this time, the aircraft wing should be a straight wing or have a small angle of dihedral to improve the lateral stability of the aircraft. In the high-speed cruising state, the aircraft wing folding upward can enhance the lateral heading stability, and the wing folding downward can enhance the lateral stability while capturing the shock wave lift, thereby further enhancing the lift and drag characteristics of the entire aircraft. In short, for high-speed aircraft, due to the large speed domain span, changing the plane shape of the wing becomes a very effective means to improve flight performance.

[0003] At the same time, aircraft that achieve deformation by folding wings face the following difficulties. First, high-speed aircraft usually do not allow large gaps on major lift components such as wings to avoid serious aerodynamic heating that causes structural and internal equipment cable burns. Therefore, to achieve a continuous and smooth outer surface of the folded wing, the wing skin at the folded position needs to be replaced with a flexible material, and an internal structure is required to support it to ensure that the flexible skin can overcome the aerodynamic load without large normal deformation and damage. Secondly, at high speed, the outer section of the wing that needs to be folded downward (upward) is subjected to a greater aerodynamic load than at low speed. This load is borne by the folding drive mechanism and transmitted to the root of the wing. In order to reduce the selection requirements of the drive, a drive mechanism with a certain reduction ratio is required, and the mechanism has the function of self-locking at any position. Finally, the existing folding wing structure can usually only be folded in a single direction. It is difficult to achieve a two-way folding function of the same mechanism upward or downward under the premise of meeting the above two requirements. In summary, the design of the folding wing structure mechanism of high-speed aircraft is difficult. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and propose a folding wing bidirectional unfolding mechanism with a skin support structure, which has a large reduction ratio and can reduce the power demand of the drive. At the same time, it can provide a connection and fixing function for the outer section structure and a supporting function for the skin at the bending point. It is suitable for high-speed variant aircraft structures with high dimensional requirements, limited drive torque, and the need for bidirectional folding.

[0005] The solution of the present invention is:

[0006] A folding wing bidirectional unfolding mechanism with a skin support structure comprises an inner wing, an outer wing, a driving mechanism and n supporting devices; wherein the inner wing and the outer wing are placed opposite to each other, and a gap is left between the inner wing and the outer wing; the driving mechanism is located at the gap between the inner wing and the outer wing, and the outer wing is driven to rotate relative to the inner wing by the driving mechanism; the n supporting devices are horizontally arranged at the gap between the inner wing and the outer wing, and each supporting device is evenly distributed on both sides of the driving mechanism with the driving mechanism as the center; the n supporting devices realize auxiliary support between the inner wing and the outer wing.

[0007] In the above-mentioned folding wing bidirectional unfolding mechanism with a skin support structure, n is a positive integer and n is not less than 2; the gap between the inner wing and the outer wing is covered with skin, and the skin is supported by a supporting device.

[0008] In the above-mentioned folding wing bidirectional unfolding mechanism with a skin support structure, the supporting device includes a rotating supporting structure and a skin supporting structure; the two ends of the rotating supporting structure are respectively connected to the mating surfaces of the inner wing and the outer wing; the skin supporting structure is respectively connected to the mating surfaces of the inner wing and the outer wing; the rotating supporting structure and the skin supporting structure are placed horizontally side by side; and when installed, the rotating supporting structure of each supporting device points to the driving mechanism, and the skin supporting structure is arranged away from the driving mechanism.

[0009] In the above-mentioned bidirectional unfolding mechanism of a folding wing with a skin support structure, the driving mechanism includes a worm fixing seat, a turbine transmission seat, m worms and m turbines; wherein the worm fixing seat is fixedly mounted on the side wall of the inner wing pointing to the outer wing; the turbine transmission seat is fixedly mounted on the side wall of the outer wing pointing to the inner wing; and the positions of the worm fixing seat and the turbine transmission seat correspond to each other; the m worms are arranged in a row and evenly mounted on the worm fixing seat; the m turbines are arranged in a row and evenly mounted on the turbine transmission seat; and the worms are meshed and matched with the turbines in a one-to-one correspondence.

[0010] In the above-mentioned folding wing bidirectional unfolding mechanism with a skin support structure, m is a positive integer, and m is not less than 4; when the turbine transmission seat is driven to rotate by m worm gears through m turbines, the outer wing is linked to rotate.

[0011] In the above-mentioned folding wing bidirectional unfolding mechanism with skin support structure, the reduction ratio of each set of worm and turbine is 16-40; m sets of worm and turbine can amplify the input torque by 16m-40m times.

[0012] In the above-mentioned folding wing bidirectional unfolding mechanism with a skin support structure, the rotating support structure includes two inner wing ears, one outer wing ear and a rotating shaft; wherein the two inner wing ears are installed in parallel on the side wall of the inner wing pointing to the outer wing; the outer wing ear is installed on the side wall of the outer wing pointing to the inner wing; the head end of the outer wing ear extends between the head ends of the two inner wing ears, and the head end of the outer wing ear and the head ends of the two inner wing ears are connected by a rotating shaft, so that the outer wing ear can rotate relative to the two inner wing ears with the rotating shaft as the axis.

[0013] In the above-mentioned folding wing bidirectional unfolding mechanism with a skin support structure, the skin support structure includes 4 ear supports and q fork rod assemblies; the 4 ear supports are grouped in pairs, one group is fixedly installed on the side wall of the outer wing pointing to the inner wing; the other group is installed on the side wall of the inner wing pointing to the outer wing; the q fork rod assemblies are connected in sequence into a row through pins; and the fork rod assemblies located on the two sides are respectively connected to the corresponding two ear supports through two pins; q is a positive integer, and q is greater than or equal to 2.

[0014] In the above-mentioned folding wing bidirectional unfolding mechanism with a skin support structure, the fork rod assembly includes two connecting rods; the two connecting rods are crossed into an X shape; and the intersection of the two connecting rods is connected by a pin shaft; the two connecting rods of each fork rod assembly are able to rotate relative to each other; the connecting rod head ends extending from two adjacent fork rod assemblies are interconnected by installing a pin shaft.

[0015] In the above-mentioned folding wing bidirectional unfolding mechanism with a skin support structure, when the inner wing and the outer wing are in the same horizontal plane, it is set to 0°; the clockwise rotation direction of the outer wing is set to positive, and the counterclockwise rotation direction of the outer wing is set to negative; the rotation range of the outer wing is -45° to 60°.

[0016] The beneficial effects of the present invention compared with the prior art are:

[0017] (1) The present invention provides a skin support structure, wherein q fork rod assemblies are sequentially connected to form a row through pins; and the fork rod assemblies located on two sides are respectively connected to two corresponding ear plate supports through two pins, and the skin support structure ensures that the flexible skin can overcome the aerodynamic load without causing large normal deformation and damage;

[0018] (2) The reduction ratio of each set of worm and turbine of the present invention is 16-40; m sets of worm and turbine can amplify the input torque by 16m-40m times, so that it can withstand greater aerodynamic load at high speed;

[0019] (3) The present invention can realize the upward or downward bidirectional folding function with the same set of mechanisms. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is an overall schematic diagram of the bidirectional unfolding mechanism of the present invention;

[0021] Figure 2 It is a schematic diagram of the structure of the driving mechanism of the present invention;

[0022] Figure 3 It is a schematic diagram of the rotary support structure of the present invention;

[0023] Figure 4 This is a schematic diagram of the skin support structure of the present invention;

[0024] Figure 5 This is a schematic diagram of the outer wing of the present invention when it is rotated 60°;

[0025] Figure 6 This is a schematic diagram of the outer wing of the present invention rotated -45°. DETAILED DESCRIPTION

[0026] The present invention will be further described below in conjunction with the embodiments.

[0027] The present invention provides a two-way unfolding mechanism of a folding wing with a skin support structure. When the aircraft needs to flip up and down the outer side of the wing to change the aerodynamic performance, the structural mechanism has a large reduction ratio, which can reduce the power demand of the driver, and at the same time can provide the connection and fixing function of the outer section structure and the supporting function of the skin at the bending part. It is suitable for the structural mechanism design of high-speed variant aircraft with high dimensional requirements, limited drive torque, and the need for two-way folding.

[0028] Folding wing bidirectional deployment mechanism, such as Figure 1 As shown, it specifically includes an inner wing 1, an outer wing 2, a driving mechanism 3 and n supporting devices; wherein, the inner wing 1 and the outer wing 2 are placed opposite to each other, and a gap is left between the inner wing 1 and the outer wing 2; the driving mechanism 3 is located at the gap between the inner wing 1 and the outer wing 2, and the outer wing 2 is driven to rotate relative to the inner wing 1 by the driving mechanism 3; n supporting devices are horizontally arranged at the gap between the inner wing 1 and the outer wing 2, and each supporting device is centered on the driving mechanism 3 and evenly distributed on both sides of the driving mechanism 3; the n supporting devices realize auxiliary support between the inner wing 1 and the outer wing 2. n is a positive integer and n is not less than 2; the gap between the inner wing 1 and the outer wing 2 is covered with skin, and the skin is supported by the supporting device.

[0029] In the present invention, the support device is designed to be divided into two parts, specifically, the support device includes a rotating support structure 4 and a skin support structure 5; the two ends of the rotating support structure 4 are respectively connected to the docking surfaces of the inner wing 1 and the outer wing 2; the skin support structure 5 is respectively connected to the docking surfaces of the inner wing 1 and the outer wing 2; the rotating support structure 4 and the skin support structure 5 are placed horizontally side by side; and when installed, the rotating support structure 4 of each support device points to the driving mechanism 3, and the skin support structure 5 is set away from the driving mechanism 3.

[0030] like Figure 2 As shown, the driving mechanism 3 includes a worm fixing seat 31, a turbine transmission seat 32, m worms 33 and m turbines 34; wherein the worm fixing seat 31 is fixedly mounted on the side wall of the inner wing 1 pointing to the outer wing 2; the turbine transmission seat 32 is fixedly mounted on the side wall of the outer wing 2 pointing to the inner wing 1; and the positions of the worm fixing seat 31 and the turbine transmission seat 32 correspond; m worms 33 are arranged in a row and evenly mounted on the worm fixing seat 31; m turbines 34 are arranged in a row and evenly mounted on the turbine transmission seat 32; and the worms 33 and the turbines 34 are meshed and matched one by one. m is a positive integer, and m is not less than 4; when the turbine transmission seat 32 is driven to rotate by the m worms 33 through the m turbines 34, the outer wing 2 is linked to rotate.

[0031] In order to achieve a larger reduction ratio and provide a larger extended torque, the reduction ratio of each set of worm 33 and turbine 34 is 16-40; m sets of worm 33 and turbine 34 can amplify the input torque by 16m-40m times.

[0032] like Figure 3 As shown, the rotating support structure 4 includes two inner wing ears 41, one outer wing ear 42 and a rotating shaft 43; wherein, the two inner wing ears 41 are installed in parallel on the side wall of the inner wing 1 pointing to the outer wing 2; the outer wing ear 42 is installed on the side wall of the outer wing 2 pointing to the inner wing 1; the head end of the outer wing ear 42 extends between the head ends of the two inner wing ears 41, and the head end of the outer wing ear 42 and the head ends of the two inner wing ears 41 are connected by the rotating shaft 43, so that the outer wing ear 42 can rotate relative to the two inner wing ears 41 with the rotating shaft 43 as the axis.

[0033] like Figure 4 As shown, the skin support structure 5 includes 4 ear supports 51 and q fork rod assemblies; the 4 ear supports 51 are grouped in pairs, and one group is fixedly mounted on the side wall of the outer wing 2 pointing to the inner wing 1; the other group is mounted on the side wall of the inner wing 1 pointing to the outer wing 2; the q fork rod assemblies are connected in sequence into a row through pins 52; and the fork rod assemblies located on the two sides are respectively connected to the corresponding two ear supports 51 through two pins 52; q is a positive integer, and q is greater than or equal to 2.

[0034] The fork rod assembly includes two connecting rods 53; the two connecting rods 53 cross to form an X shape; and the intersection of the two connecting rods 53 is connected by a pin 52; the two connecting rods 53 of each fork rod assembly are able to rotate relative to each other; the head ends of the connecting rods 53 extending from two adjacent fork rod assemblies are interconnected by installing the pin 52.

[0035] When the inner wing 1 and the outer wing 2 are in the same horizontal plane, it is set to 0°; the clockwise rotation direction of the outer wing 2 is set to positive, and the counterclockwise rotation direction of the outer wing 2 is set to negative; the rotation range of the outer wing 2 is -45° to 60°, such as Figure 5, Figure 6 shown.

[0036] In the present invention, the skin support structure 5 provides support for the entire skin structure. The structure is composed of multiple links 53; and fixed ear support 51 connected to the wings on both sides, such as Figure 4 As shown. The connecting rods 53 are connected to each other through the pins 52 to form a linkage mechanism. Except for the pins 52 located in the middle position, the other pins 52 will be connected to the skin covering it, and the connection method is binding, wherein the corresponding skin position needs to be equipped with a strap. When the wings on both sides rotate relative to each other, the ear support 51 drives the connecting rod mechanism to move, so that the pins 52 are still in a relatively smooth profile position, providing dimensional support for the outer skin.

[0037] The driving mechanism 3 is used to drive the outer wing 2 to rotate and at the same time supports and fixes the outer wing 2. The mechanism includes: a worm fixing seat 31, a turbine transmission seat 32, m worms 33 and m turbines 34. Figure 2 As shown. The worm 33 will be connected to the driving motor located inside the fixed wing and installed on the inner section wing surface through the worm fixing seat 31. The worm gear rotating seat 32 is fixedly connected to the outer section wing 2. When the worm gear rotating seat 32 is driven to rotate by the worm 34, the outer section wing 2 is directly linked to rotate. Since the angle of the outer section wing 2 to flip up or down is limited, a complete worm gear structure is not required, so the rotating seat only has half of the worm gear structure. The entire driving mechanism 3 is composed of multiple groups of worm gear transmission mechanisms to withstand the hinge torque caused by the aerodynamic force of the outer section wing surface. In addition to providing a larger reduction ratio, the worm gear transmission mechanism also has a self-locking function. After the driving motor no longer drives the worm to rotate, the outer section wing surface is locked in the current position, and no additional mechanical locking mechanism is required to maintain the current position.

[0038] The rotating support structure 4 is used for the hinged connection between the inner wing 1 and the outer wing 2. It includes an inner wing ear 41, an outer wing ear 42, and a rotating shaft 43. The inner wing ear 41 is fixedly connected to the inner wing 1, the outer wing ear 42 is fixedly connected to the outer wing 2, and the rotating shaft 43 is used as a rotating shaft for the connection and rotation positioning of the two wing surfaces.

[0039] The present invention realizes that when the aircraft needs to flip the outer side of the wing up and down to change the aerodynamic performance, the structural mechanism has a large reduction ratio, which can reduce the power demand of the driver, and at the same time can provide a connection and fixation function for the outer section structure, and a supporting function for the skin at the bend. It is suitable for the structural mechanism design of high-speed variant aircraft with high dimensional requirements, limited drive torque, and the need for two-way folding.

[0040] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A two-way unfolding mechanism for a folding wing with a skin support structure, characterized in that: The invention comprises an inner wing (1), an outer wing (2), a driving mechanism (3) and n supporting devices; wherein the inner wing (1) and the outer wing (2) are arranged opposite to each other, and a gap is left between the inner wing (1) and the outer wing (2); the driving mechanism (3) is located at the gap between the inner wing (1) and the outer wing (2), and the outer wing (2) is driven to rotate relative to the inner wing (1) by the driving mechanism (3); the n supporting devices are horizontally arranged at the gap between the inner wing (1) and the outer wing (2), and each supporting device is evenly distributed on both sides of the driving mechanism (3) with the driving mechanism (3) as the center; the n supporting devices realize auxiliary support between the inner wing (1) and the outer wing (2); The support device comprises a rotating support structure (4) and a skin support structure (5); the two ends of the rotating support structure (4) are respectively connected to the butt joint surfaces of the inner wing (1) and the outer wing (2); the skin support structure (5) is respectively connected to the butt joint surfaces of the inner wing (1) and the outer wing (2); the rotating support structure (4) and the skin support structure (5) are horizontally arranged side by side; and when installed, the rotating support structure (4) of each support device points to the driving mechanism (3), and the skin support structure (5) is arranged away from the driving mechanism (3); The skin support structure (5) comprises four ear supports (51) and q fork rod assemblies; the four ear supports (51) are arranged in groups of two, one group of which is fixedly mounted on the side wall of the outer wing (2) pointing to the inner wing (1); the other group of which is mounted on the side wall of the inner wing (1) pointing to the outer wing (2); the q fork rod assemblies are connected in sequence into a row through pins (52); and the fork rod assemblies located on the two sides are respectively connected to the corresponding two ear supports (51) through two pins (52); q is a positive integer, and q is greater than or equal to 2.

2. A folding wing bidirectional deployment mechanism with a skin support structure according to claim 1, characterized in that: n is a positive integer and is not less than 2; the gap between the inner wing (1) and the outer wing (2) is covered with a skin, and the skin is supported by a supporting device.

3. A folding wing bidirectional deployment mechanism with a skin support structure according to claim 1, characterized in that: The driving mechanism (3) comprises a worm fixing seat (31), a turbine transmission seat (32), m worms (33) and m turbines (34); wherein the worm fixing seat (31) is fixedly mounted on the side wall of the inner wing (1) pointing to the outer wing (2); the turbine transmission seat (32) is fixedly mounted on the side wall of the outer wing (2) pointing to the inner wing (1); and the positions of the worm fixing seat (31) and the turbine transmission seat (32) correspond; the m worms (33) are arranged in a row and evenly mounted on the worm fixing seat (31); the m turbines (34) are arranged in a row and evenly mounted on the turbine transmission seat (32); and the worms (33) and the turbines (34) are meshed and matched in a one-to-one correspondence.

4. A folding wing bidirectional deployment mechanism with a skin support structure according to claim 3, characterized in that: The m is a positive integer and is not less than 4; when the turbine transmission seat (32) is driven to rotate by the m worm gears (33) through the m turbines (34), the outer wing (2) is also driven to rotate.

5. A folding wing bidirectional deployment mechanism with a skin support structure according to claim 4, characterized in that: The reduction ratio of each set of worm gears (33) and turbine gears (34) is 16-40; m sets of worm gears (33) and turbine gears (34) can amplify the input torque by 16m-40m times.

6. A folding wing bidirectional deployment mechanism with a skin support structure according to claim 1, characterized in that: The rotating support structure (4) comprises two inner wing ears (41), one outer wing ear (42) and a rotating shaft (43); wherein the two inner wing ears (41) are mounted in parallel on the side wall of the inner wing (1) pointing to the outer wing (2); the outer wing ear (42) is mounted on the side wall of the outer wing (2) pointing to the inner wing (1); the head end of the outer wing ear (42) extends between the head ends of the two inner wing ears (41), and the head end of the outer wing ear (42) and the head ends of the two inner wing ears (41) are connected via the rotating shaft (43), so that the outer wing ear (42) can rotate relative to the two inner wing ears (41) with the rotating shaft (43) as the axis.

7. A folding wing bidirectional deployment mechanism with a skin support structure according to claim 1, characterized in that: The fork rod assembly comprises two connecting rods (53); the two connecting rods (53) are crossed to form an X shape; and the intersection of the two connecting rods (53) is connected by a pin shaft (52); the two connecting rods (53) of each fork rod assembly are able to rotate relative to each other; and the head ends of the connecting rods (53) extending from two adjacent fork rod assemblies are interconnected by installing the pin shaft (52).

8. The bidirectional unfolding mechanism of a folding wing with a skin support structure according to claim 1, characterized in that: When the inner wing (1) and the outer wing (2) are located in the same horizontal plane, the angle is set to 0°; the clockwise rotation direction of the outer wing (2) is set to positive, and the counterclockwise rotation direction of the outer wing (2) is set to negative; the rotation range of the outer wing (2) is from -45° to 60°.

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