Aircraft wing attack angle adjusting device

Abstract

The utility model discloses an aircraft wing attack angle adjusting device and belongs to the technical field of aircraft component adjustment. The method is used for solving the problems that a traditional wing attack angle adjusting mode is complex in operation, limited in adjusting precision, time-consuming in installation and difficult to meet the high requirements of modern aircraft manufacturing for flight performance and safety. The outer ring is detachably and fixedly connected with the machine body through a mounting frame, the outer ring is arranged outside the inner ring in a sleeving mode and rotationally connected with the inner ring, the sliding assembly is arranged at the lower end of the inner side wall of the inner ring, the fixing assembly is arranged in the inner ring, and the lower end of the fixing assembly is fixedly connected with the upper end of the sliding assembly; the left end and the right end of the fixing assembly are slidably connected with the inner side wall of the inner ring, and the rotating assembly is arranged on the outer ring and rotationally connected with the inner ring. According to the utility model, the attack angle of the wing can be quickly and accurately adjusted. The indication assembly improves the adjustment accuracy. The fixing assembly ensures stable installation of the wings. The structure is simple, operation is convenient, maintenance and replacement are easy, and the manufacturing and maintaining cost of the aircraft is reduced.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the technical field of aircraft component adjustment, especially relates to a plane wing angle of attack adjusting device. BACKGROUND

[0002] In the aircraft manufacturing process, the wing angle of attack is one of the key factors affecting the lift and drag of the aircraft, and the wing angle of attack has a crucial influence on the flight performance. The change of the angle of attack directly affects the lift, drag and flight attitude of the aircraft. When the wing is installed, the traditional wing angle of attack adjustment mode is often complex to operate, the adjustment precision is limited, and the maintenance cost is high, so that the wing not only consumes time in the installation process, but also is difficult to meet the high requirements of modern aircraft manufacturing on flight performance and safety. Therefore, it is particularly important to develop a wing angle of attack adjustment device with simple structure, accurate adjustment and easy operation. SUMMARY

[0003] The utility model aims at providing a plane wing angle of attack adjusting device, which solves the problems of the traditional wing angle of attack adjustment mode, such as complex operation, limited adjustment precision, time-consuming installation and difficulty in meeting the high requirements of modern aircraft manufacturing on flight performance and safety.

[0004] To achieve the above-mentioned purpose, the utility model adopts the following technical scheme: a plane wing angle of attack adjusting device, comprising an outer ring, an inner ring, a fixed component, a sliding component and a rotating component, a plurality of mounting frames are arranged on the rear end surface of the outer ring, the mounting frames are detachably fixedly connected with the fuselage through fixing bolts, the outer ring is sleeved outside the inner ring, the inner side wall of the outer ring is rotatably connected with the outer side wall of the inner ring, the sliding component is arranged on the lower end of the inner side wall of the inner ring along the axial direction of the inner ring, the fixed component is arranged in the inner ring, the lower end of the fixed component is fixedly connected with the upper end of the sliding component, the left and right ends of the fixed component are slidably connected with the inner side wall of the inner ring, and the rotating component is arranged on the outer ring and rotatably connected with the inner ring.

[0005] Further, the fixed component comprises a lower fixed groove, a lower positioning block, an upper positioning plate and an upper positioning block, the lower positioning block is arranged in the lower fixed groove, the upper end of the lower positioning block is matched with the lower end of the wing, the lower end of the upper positioning plate is provided with the upper positioning block, the lower end of the upper positioning block is matched with the upper end of the wing, in use, the wing is arranged between the lower fixed groove and the upper positioning plate, the upper end of the lower fixed groove is detachably fixedly connected with the upper positioning plate through positioning bolts, the upper end surface of the lower positioning block is tightly matched with the lower end surface of the wing, and the lower end surface of the upper positioning block is tightly matched with the upper end surface of the wing.

[0006] Further, the sliding assembly comprises a mounting plate, a hydraulic cylinder and a support, the mounting plate is vertically arranged at the front end of the inner side wall of the inner ring, the hydraulic cylinder is arranged at the middle of the front end face of the mounting plate, the lower end of the inner side wall of the inner ring is provided with a sliding channel along the axial direction of the inner ring, the support is slidingly arranged in the sliding channel, the hydraulic rod of the hydraulic cylinder is fixedly connected with the front end face of the support through the mounting plate, the hydraulic cylinder drives the support to slide in the sliding channel, and the upper end face of the support is fixedly connected with the lower end face of the lower fixed groove.

[0007] Further, the rotating assembly comprises a rotating motor and a gear, the rotating motor is arranged on the front end face of the outer ring, the side wall of the outer ring is provided with a through groove, the gear is arranged in the through groove, the gear is rotationally connected with the front and rear side walls of the through groove through a rotating shaft, the output end of the rotating motor is fixedly connected with one end of the rotating shaft through the outer ring, the rotating motor drives the gear to rotate, and a plurality of gear teeth are uniformly arranged on the corresponding positions of the outer side wall of the inner ring along the axial direction of the inner ring.

[0008] Further, the front end face of the outer ring is provided with an arc-shaped scale plate, the upper end face of the arc-shaped scale plate is provided with a scale line and an angle mark, and the front end face of the outer ring is provided with an indicating arrow.

[0009] Compared with the prior art, the beneficial effects of the utility model are:

[0010] 1、The utility model discloses a hydraulic cylinder and rotating motor's synergies realize the quick, accurate adjustment of the wing angle of attack.

[0011] 2、The utility model discloses the setting of arc-shaped scale plate and indicating arrow, the adjustment angle of intuitive reading of operator is convenient, improves the adjustment accuracy.

[0012] 3、The utility model discloses the design of fixed assembly ensures the firm installation of wing, improves flight safety.

[0013] 4、The utility model discloses simple structure, convenient operation, easy maintenance and replacement, has reduced the cost of airplane manufacturing and maintenance. ACCURACY

[0014] Figure 1 It is the overall structure schematic of the utility model Figure 1 ;

[0015] Figure 2 It is the overall structure schematic of the utility model Figure 2 ;

[0016] Figure 3 It is the overall structure schematic of the utility model Figure 3 ;

[0017] Figure 4 It is the front view of the utility model;

[0018] Figure 5 is Figure 4 an enlarged view of A in

[0019] Figure 6 is a sectional view of the present application.

[0020] The component names and reference numerals involved in the above drawings are as follows:

[0021] 1, outer ring; 2, inner ring; 3, mounting bracket; 4, fixing bolt; 5, fixing assembly; 6, wing; 7, support; 8, hydraulic cylinder; 9, mounting plate; 10, through slot; 11, gear; 12, rotating motor; 13, arc-shaped scale plate; 14, indicating arrow; 15, tooth; 16, hydraulic rod; 17, sliding groove; 18, lower fixing groove; 19, lower positioning block; 20, upper positioning plate; 21, upper positioning block; 22, positioning bolt; 23, sliding block. DETAILED DESCRIPTION

[0022] The technical solutions in the present application will be described clearly and completely below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative efforts fall within the scope of protection of the present application.

[0023] DETAILED DESCRIPTION: As shown in Figures 1-6 the present embodiment discloses an aircraft wing angle of attack adjusting device, which comprises an outer ring 1, an inner ring 2, a fixing assembly 5, a sliding assembly and a rotating assembly. The rear end surface of the outer ring 1 is provided with a plurality of mounting brackets 3. The mounting brackets 3 are detachably fixedly connected to the fuselage by fixing bolts 4. The outer ring 1 is sleeved outside the inner ring 2. The inner side wall of the outer ring 1 is rotationally connected to the outer side wall of the inner ring 2. The sliding assembly is arranged on the inner side wall of the inner ring 2 at the lower end in the axial direction of the inner ring 2. The fixing assembly is arranged in the inner ring 2. The lower end of the fixing assembly is fixedly connected to the upper end of the sliding assembly. The left and right ends of the fixing assembly are respectively slidably connected to the inner side wall of the inner ring 2. The rotating assembly is arranged on the outer ring 1. The rotating assembly is rotationally connected to the inner ring 2.

[0024] Furthermore, the fixing component 5 includes a lower fixing groove 18, a lower positioning block 19, an upper positioning plate 20, and an upper positioning block 21. The lower fixing groove 18 is provided with the lower positioning block 19, and the upper end of the lower positioning block 19 is matched with the lower end of the wing 6. The upper positioning plate 20 is provided with the upper positioning block 21 at its lower end, and the lower end of the upper positioning block 21 is matched with the upper end of the wing 6. In use, the wing 6 is positioned between the lower fixing groove 18 and the upper positioning plate 20. The upper positioning plate 20 is detachably fixed to the upper end of the lower fixing groove 18 by positioning bolts 22. The upper end face of the lower positioning block 19 is tightly fitted to the lower end face of the wing 6, and the lower end face of the upper positioning block 21 is tightly fitted to the upper end face of the wing 6. The left and right ends of the inner sidewall of the inner ring 2 are symmetrically provided with sliding grooves 17 along the axial direction of the inner ring 2. The left and right outer sidewalls of the lower fixing groove 18 are slidably connected to the corresponding sliding grooves 17 by sliders 23.

[0025] Furthermore, the sliding assembly includes a mounting plate 9, a hydraulic cylinder 8, and a support 7. The mounting plate 9 is vertically disposed at the front end of the inner sidewall of the inner ring 2. The hydraulic cylinder 8 is disposed at the middle of the front end face of the mounting plate 9. A slide rail is provided at the lower end of the inner sidewall of the inner ring 2 along the axial direction of the inner ring 2. The support 7 is slidably disposed in the slide rail. The hydraulic rod 16 of the hydraulic cylinder 8 passes through the mounting plate 9 and is fixedly connected to the front end face of the support 7. The hydraulic cylinder 8 drives the support 7 to slide in the slide rail. The upper end face of the support 7 is fixedly connected to the lower end face of the lower fixing groove 18.

[0026] Furthermore, the rotating assembly includes a rotating motor 12 and a gear 11. The rotating motor 12 is disposed on the front end face of the outer ring 1. A through groove 10 is opened on the side wall of the outer ring 1. The gear 11 is disposed in the through groove 10. The gear 11 is rotatably connected to the front and rear side walls of the through groove 10 through a rotating shaft. The output end of the rotating motor 12 passes through the outer ring 1 and is fixedly connected to one end of the rotating shaft. The rotating motor 12 drives the gear 11 to rotate. A plurality of teeth 15 are evenly distributed along the axial direction of the inner ring 2 at the corresponding positions of the gear 11 on the outer side wall of the inner ring 2. The plurality of teeth 15 mesh with the gear 11.

[0027] Furthermore, the inner side of the front end face of the outer ring 1 is provided with an arc-shaped scale plate 13, the upper end face of the arc-shaped scale plate 13 is provided with scale lines and angle markings, and the outer side of the front end face of the inner ring 2 is provided with an indicator arrow 14, which is matched with the arc-shaped scale plate 13.

[0028] Specific structural installation:

[0029] Installation of outer ring 1 and mounting bracket 3:

[0030] The outer ring 1 is made of high-strength, lightweight alloy material, and multiple mounting brackets 3 are evenly distributed on its rear end face. Each mounting bracket 3 has a pre-drilled screw hole, which is tightly connected to the corresponding position on the fuselage by fixing bolts 4, ensuring that the entire adjustment device is securely installed on the aircraft.

[0031] The inner ring 2 is rotatably connected with the outer ring 1:

[0032] The inner ring 2 is also made of light alloy material, and the outer side wall is designed with a rolling bearing structure matched with the inner side wall of the outer ring 1, realizing smooth rotation connection between the two. The axial position of the inner ring 2 is kept stable by the limiting action of the outer ring 1.

[0033] Installation of the fixing assembly 5:

[0034] The fixing assembly 5 includes a lower fixing groove 18, a lower positioning block 19, an upper positioning plate 20 and an upper positioning block 21. The lower fixing groove 18 is arranged in the inner ring 2, and the left and right sides thereof are slidably connected with the sliding grooves 17 of the inner side wall of the inner ring 2 through the sliding blocks 23. The lower positioning block 19 is arranged on the lower fixing groove 18, the upper positioning block 21 is arranged on the upper positioning plate 20, and the upper positioning plate 20 is detachably connected with the upper end surface of the lower fixing groove 18 through the positioning bolt 22, forming a clamping action on the wing 6.

[0035] Installation of the sliding assembly:

[0036] The sliding assembly is composed of a mounting plate 9, a hydraulic cylinder 8 and a support 7. The mounting plate 9 is vertically welded to the front end of the inner side wall of the inner ring 2, and the hydraulic cylinder 8 is fixed to the middle of the front end surface of the mounting plate 9 through bolts. The support 7 is slidably arranged in the slide at the lower end of the inner side wall of the inner ring 2, and the hydraulic rod 16 of the hydraulic cylinder 8 is fixedly connected with the front end surface of the support 7 through the mounting plate 9.

[0037] Installation of the rotating assembly:

[0038] The rotating assembly includes a rotating motor 12 and a gear 11. The rotating motor 12 is fixedly installed on the front end surface of the outer ring 1 through a support, and its output end is fixedly connected with the rotating shaft of the gear 11 through the through slot 10 of the side wall of the outer ring 1. The gear 11 is arranged in the through slot 10 and rotatably connected with the front and rear side walls of the through slot 10 through bearings. The outer side wall of the inner ring 2 is uniformly provided with a plurality of teeth 15 engaged with the gear 11 along the axial direction.

[0039] Installation of the indicating assembly:

[0040] An arc-shaped scale plate 13 is pasted on the inner side of the front end surface of the outer ring 1, and clear scale lines and angle marks are engraved on the upper end surface thereof. An indicating arrow 14 is welded on the outer side of the front end surface of the inner ring 2, which is used to point to the scale on the arc-shaped scale plate 13, so as to directly display the adjustment angle of the angle of attack of the wing 6.

[0041] Working principle:

[0042] Clamping and fixing of the wing 6:

[0043] The wing 6 is placed between the lower fixed groove 18 and the upper positioning plate 20, and the upper end surface of the lower positioning block 19 is tightly fitted with the lower end surface of the wing 6, and the lower end surface of the upper positioning block 21 is tightly fitted with the upper end surface of the wing 6 by adjusting the position of the upper positioning plate 20 and fastening with the positioning bolt 22, so as to realize the stable clamping and fixing of the wing 6.

[0044] Angle of attack adjustment of the wing 6:

[0045] The hydraulic cylinder 8 is started, and the support 7 is driven to slide in the slide way through the extension and retraction of the hydraulic rod 16, and then the lower fixed groove 18 and the wing 6 are driven to move along the axial direction of the inner ring 2 to the required position. Then the rotating motor 12 is started, and the output end drives the gear 11 to rotate, and since the gear 11 is engaged with the teeth 15 on the outer side wall of the inner ring 2, the rotation of the gear 11 will drive the inner ring 2 to rotate relative to the outer ring 1, so as to change the angle of attack of the wing 6.

[0046] Angle of attack display and reading:

[0047] During the adjustment process, the position change of the indicating arrow 14 on the arc-shaped scale plate 13 on the front end surface of the inner ring 2 can be observed, so as to intuitively read the adjustment angle of the current angle of attack of the wing 6. The scale lines and angle marks on the arc-shaped scale plate 13 provide accurate reference for the operator.

[0048] Working process:

[0049] Preparation stage:

[0050] The entire adjustment device is stably installed on the fuselage of the aircraft through the mounting frame 3 and the fixing bolt 4, and the connection between the device and the fuselage is ensured to be reliable.

[0051] Wing 6 installation:

[0052] The wing 6 is placed in the correct direction between the lower fixed groove 18 and the upper positioning plate 20, and the upper positioning plate 20 is fastened on the upper end surface of the lower fixed groove 18 through the positioning bolt 22, so as to complete the clamping and fixing of the wing 6.

[0053] Angle of attack adjustment:

[0054] The hydraulic cylinder 8 is started to adjust the axial position of the wing 6, and then the rotating motor 12 is started to drive the inner ring 2 to rotate relative to the outer ring 1 to the required angle of attack position. During the adjustment process, the operator needs to observe the position change of the indicating arrow 14 on the arc-shaped scale plate 13 at all times to ensure the adjustment accuracy.

[0055] Inspection and confirmation:

[0056] After the adjustment is completed, the clamping state of the wing 6 is checked again to see whether it is stable, the angle of attack is accurate, and the connection of each part is reliable. After confirming that there is no error, the installation operation of the wing 6 and the fuselage can be performed. After installation, the reverse operation is performed to release the fixation of the adjustment device and the wing 6. The adjustment device completes the adjustment work this time, resets and then is used next time.

[0057] The angle-of-attack adjustment device has the advantages of simple structure, easy operation, accurate adjustment, easy maintenance and the like, and can be widely applied to the wing angle-of-attack adjustment of various aircrafts.

[0058] It is obvious for those skilled in the art that the utility model is not limited to the details of the above-mentioned exemplary embodiments, and the utility model can be realized in other forms without departing from the spirit or basic characteristics of the utility model. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive, the scope of the utility model is defined by the appended claims rather than the above description, and therefore all changes falling within the meaning and scope of the equivalent conditions of the claims should be included in the utility model. Any figure mark in the claims should not be regarded as limiting the involved claims.

[0059] In addition, it should be understood that although the present specification is described in terms of embodiments, not every embodiment contains only one independent technical solution, and the description manner of the specification is only for the sake of clarity, and those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be properly combined to form other embodiments which can be understood by those skilled in the art.

Claims

1. An aircraft wing angle of attack adjustment device, characterised in that: The utility model provides a kind of wing folding mechanism, including outer ring (1), inner ring (2), fixed assembly (5), sliding assembly and rotating assembly, the rear end surface of the outer ring (1) is provided with multiple mounting racks (3), mounting rack (3) is detachably fixedly connected with fuselage by fixed bolt (4) arrangement, outer ring (1) is set outside inner ring (2), outer ring (1) inner side wall is rotationally connected with the outer side wall of inner ring (2), sliding assembly is arranged in inner ring (2) inner side wall lower end along the axial direction of inner ring (2), fixed assembly is arranged in inner ring (2), and the upper end of fixed assembly is fixedly connected with sliding assembly, and the left and right ends of fixed assembly are slidably connected with the inner side wall of inner ring (2) respectively, and rotating assembly is arranged on outer ring (1), and rotating assembly is rotationally connected with inner ring (2).

2. An aircraft wing angle of attack adjustment device as claimed in claim 1, characterised in that: The fixed assembly (5) includes lower fixed groove (18), lower positioning block (19), upper positioning plate (20) and upper positioning block (21), the lower fixed groove (18) is provided with lower positioning block (19) in, and the upper end of lower positioning block (19) is matched with the lower end of wing (6) arrangement, and the lower end of upper positioning plate (20) is provided with upper positioning block (21), and the lower end of upper positioning block (21) is matched with the upper end of wing (6) arrangement, when using, wing (6) is arranged between lower fixed groove (18) and upper positioning plate (20), and upper positioning plate (20) is detachably fixedly connected with the upper end of lower fixed groove (18) by positioning bolt (22) arrangement, and the upper end of lower positioning block (19) is closely combined with the lower end surface of wing (6) arrangement, and the lower end surface of upper positioning block (21) is closely combined with the upper end surface of wing (6), and the left and right ends of inner ring (2) inner side wall are respectively arranged symmetrically along the axial direction of inner ring (2) sliding groove (17), and the left and right outer side walls of lower fixed groove (18) are slidably connected with corresponding sliding groove (17) by sliding block (23) respectively.

3. An aircraft wing incidence adjustment device as claimed in claim 2, characterised in that: The sliding assembly includes mounting plate (9), hydraulic cylinder (8) and support (7), the mounting plate (9) is vertically arranged in the front end of the inner side wall of inner ring (2), the hydraulic cylinder (8) is arranged in the front end surface of mounting plate (9), the lower end of the inner side wall of inner ring (2) is provided with a slide along the axial direction of inner ring (2), the support (7) is slidably arranged in the slide, the hydraulic rod (16) of hydraulic cylinder (8) passes through mounting plate (9) and is fixedly connected with the front end surface of support (7), and hydraulic cylinder (8) drives support (7) to slide in the slide, and the upper end surface of support (7) is fixedly connected with the lower end surface of lower fixed groove (18) arrangement.

4. An aircraft wing incidence adjustment device as claimed in claim 3, characterised in that: The rotating assembly includes rotating motor (12) and gear (11), the rotating motor (12) is arranged on the front end surface of outer ring (1), the side wall of outer ring (1) is provided with a through slot (10), the gear (11) is arranged in the through slot (10), the gear (11) is rotationally connected with the front and back two side walls of through slot (10) by rotating shaft, and the output end of rotating motor (12) is fixedly connected with one end of rotating shaft by passing through outer ring (1), and rotating motor (12) drives gear (11) to rotate, the outer side wall of inner ring (2) is uniformly provided with a plurality of teeth (15) along the axial direction of inner ring (2) at corresponding position of gear (11), and a plurality of teeth (15) are engaged with gear (11).

5. An aircraft wing incidence adjustment device as claimed in claim 4, characterised in that: The outer ring (1) is provided with an arc-shaped scale plate (13) on the inner side of the front end face, the upper end face of the arc-shaped scale plate (13) is provided with scale lines and angle marks, and the inner ring (2) is provided with an indicating arrow (14) on the outer side of the front end face, and the indicating arrow (14) is matched with the arc-shaped scale plate (13).

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