Airplane horizontal tail composite material rudder

Abstract

The utility model discloses an airplane horizontal tail composite material rudder in the technical field of composite material products, which comprises a long beam in a C shape on the whole; the trailing edge rib is fixed on the outer surface of the long beam; the upper skin is fixed on the trailing edge rib, and the front end of the upper skin extends and is fixed at the upper end of the outer surface of the long beam; the lower skin is fixed on the trailing edge rib, and the front end of the lower skin extends and is fixed at the lower end of the outer surface of the long beam; the trailing edge is fixedly connected with the rear end of the trailing edge rib, the rear end of the upper skin and the rear end of the lower skin; the front edge rib is fixed on the inner surface of the long beam, the front end is arc-shaped, and the rear end follows the inner surface of the long beam; the front edge skin is fixed on the front edge rib, and the rear end of the front edge skin extends and is fixed at the upper and lower ends of the outer surface of the long beam and is butted with the front end of the upper skin and the front end of the lower skin; the long beam, the trailing edge rib, the upper skin, the lower skin, the trailing edge, the leading edge rib and the leading edge skin are all made of composite materials. The weight of the rudder is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of composite products, in particular to an aircraft horizontal tail rudder. Background Art

[0002] Traditional horizontal tail rudders are mostly formed by riveting aluminum alloy skins and aluminum alloy ribs. Metal materials have yield or conditional yield due to their isotropic properties. To obtain the required performance, they can only be achieved by increasing the thickness, which will result in a heavier mass after the product is assembled. In addition, metal materials have low fatigue resistance. For aircraft that often fly over the sea, metal materials have poor acid and alkali corrosion resistance. Therefore, using composite materials instead of metal materials will have the advantages of light weight, high strength and corrosion resistance. Utility Model Content

[0003] Aiming at the deficiencies in the prior art, the utility model provides an aircraft horizontal tail composite material rudder, which reduces the weight of the rudder.

[0004] The purpose of the utility model is achieved as follows: an aircraft horizontal tail composite material rudder, comprising:

[0005] Long beam, overall C-shaped;

[0006] trailing edge ribs, fixed to the outer surface of the long beam;

[0007] An upper skin fixed to the trailing edge rib, extending at the front end and fixed to the upper end of the outer surface of the long beam;

[0008] A lower skin, fixed to the trailing edge rib, extending forward and fixed to the lower end of the outer surface of the long beam;

[0009] The trailing edge is fixedly connected to the rear end of the trailing edge rib, the rear end of the upper skin, and the rear end of the lower skin;

[0010] The front edge rib is fixed on the inner surface of the long beam, with the front end being arc-shaped and the rear end being in line with the inner surface of the long beam;

[0011] The leading edge skin is fixed on the leading edge rib, the rear end is extended and fixed on the upper and lower ends of the outer surface of the long beam, and is butted with the front end of the upper skin and the front end of the lower skin;

[0012] The long beam, trailing edge rib, upper skin, lower skin, trailing edge, leading edge rib and leading edge skin are all made of composite materials.

[0013] Furthermore, the upper skin includes an upper honeycomb sandwiched between an upper outer skin and an upper inner skin.

[0014] Furthermore, the lower skin includes a lower honeycomb sandwiched between the lower outer skin and the lower inner skin.

[0015] Furthermore, the trailing edge ribs include end ribs and middle ribs.

[0016] Furthermore, a weight-reducing hole is provided on the middle rib.

[0017] Furthermore, the leading edge ribs are provided in plurality, and every two leading edge ribs are combined with a leading edge skin, with a gap being left between each combination.

[0018] Furthermore, a connecting seat is installed inside the long beam in the gap.

[0019] Compared with the prior art, the beneficial effects of the utility model are:

[0020] 1) The use of composite materials can reduce weight, and composite materials have high specific strength and specific stiffness, and are superior to metal materials in terms of performance and lightweight;

[0021] 2) Strong corrosion resistance. Composite material rudders have strong acid and alkali corrosion resistance. Since the rudder is located in the open part of the leading edge of the horizontal tail, it needs to have a certain corrosion resistance. Compared with metal materials, carbon fiber has sufficient guarantee in corrosion resistance;

[0022] 3) Strong fatigue resistance: Carbon fiber composite materials have excellent fatigue resistance compared to metal materials. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings in the following description are only embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0024] Figure 1 This is a schematic diagram of the structure of the utility model Figure 1 .

[0025] Figure 2 This is a schematic diagram of the structure of the utility model Figure 2 .

[0026] Figure 3 It is a schematic diagram of the rear edge rib structure of the utility model.

[0027] Figure 4 It is an enlarged side view of the utility model.

[0028] Figure 5 This is a cross-sectional view of the utility model.

[0029] Figure 6 for Figure 5 Enlarged view of point A in the middle.

[0030] Figure 7 for Figure 5 Enlarged view of point B in the middle.

[0031] Among them, 100 long beam, 200 trailing edge ribs, 201 end ribs, 202 middle ribs, 300 upper skin, 301 upper outer skin, 302 upper inner skin, 303 upper honeycomb, 400 lower skin, 401 lower outer skin, 402 lower inner skin, 403 lower honeycomb, 500 trailing edge, 600 leading edge ribs, 700 leading edge skin, and 800 connecting seat. DETAILED DESCRIPTION

[0032] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model. Example

[0033] like Figure 1-7 A composite rudder for a horizontal tail of an aircraft is shown, comprising:

[0034] The long beam 100 is C-shaped overall;

[0035] The trailing edge rib 200 is fixed on the outer surface of the long beam 100;

[0036] The upper skin 300 is fixed on the trailing edge rib 200, the front end of which extends and is fixed on the upper end of the outer surface of the long beam 100;

[0037] The lower skin 400 is fixed on the trailing edge rib 200, the front end of which extends and is fixed to the lower end of the outer surface of the long beam 100;

[0038] The trailing edge 500 is fixedly connected to the rear end of the trailing edge rib 200, the rear end of the upper skin 300, and the rear end of the lower skin 400;

[0039] The front edge rib 600 is fixed to the inner surface of the long beam 100, with the front end being arc-shaped and the rear end being in the same shape as the inner surface of the long beam 100;

[0040] The leading edge skin 700 is fixed on the leading edge rib 600, the rear end of which is extended and fixed to the upper and lower ends of the outer surface of the long beam 100, and is butted with the front end of the upper skin 300 and the front end of the lower skin 400;

[0041] The long beam 100, the trailing edge rib 200, the upper skin 300, the lower skin 400, the trailing edge 500, the leading edge rib 600 and the leading edge skin 700 are all made of composite materials.

[0042] Specifically, the leading edge rib 600 and the long beam 100 are fixed by gluing; the leading edge skin 700, the leading edge rib 600 and the long beam 100 are connected and fixed by nailing; the upper skin 300, the lower skin 400 and the long beam 100 are connected by nailing; the upper skin 300, the lower skin 400 and the trailing edge rib 200 are fixed by gluing; the long beam 100 and the trailing edge rib 200 are connected and fixed by nailing; the trailing edge 500 and the upper skin 300, the lower skin 400 are connected and fixed by adhesive film.

[0043] It should be noted that, through the above structure and fixing method, the weight of the rudder is greatly reduced while ensuring the overall rudder connection strength.

[0044] Furthermore, the upper skin 300 includes an upper honeycomb 303 sandwiched between the upper outer skin 301 and the upper inner skin 302 .

[0045] Specifically, the thickness of the two middle areas of the upper outer skin 301 is smaller than that of other areas, and is used to place the corresponding two upper honeycombs 303. The thickness of the front end of the upper inner skin is greater than that of other areas, and serves as a connection with the long beam 100 to ensure strength.

[0046] Furthermore, the lower skin 400 includes a lower honeycomb 403 sandwiched between the lower outer skin 401 and the lower inner skin 402 .

[0047] Specifically, the thickness of the two middle areas of the lower outer skin 401 is smaller than that of other areas, and is used to place the corresponding two lower honeycombs 403. The thickness of the front end of the lower inner skin is greater than that of other areas, and serves as a connection with the long beam 100 to ensure strength.

[0048] Furthermore, the trailing edge rib 200 includes an end rib 201 and a middle rib 202 , and the middle rib 202 is provided with a weight-reducing hole.

[0049] Specifically, this embodiment involves two end ribs 201 and two middle ribs 202 .

[0050] It should be noted that both the end ribs 201 and the middle ribs 202 have a supporting function. Since the middle position must be closed, a weight-reducing hole is opened on the middle rib 202 to further reduce the overall weight of the rudder.

[0051] Furthermore, a plurality of leading edge ribs 600 are provided, and every two leading edge ribs 600 are combined with a leading edge skin 700, with a gap being left between each combination.

[0052] Specifically, in this embodiment, eight leading edge ribs 600 are provided, with a total of four groups, which can be adjusted as appropriate according to actual needs, and the gap design is to facilitate connection with the fuselage.

[0053] Furthermore, a connecting seat 800 is installed inside the long beam 100 in the gap.

[0054] This design further facilitates the connection with the fuselage.

[0055] The above embodiments are only used to help understand the method and core idea of ​​the utility model. It should be pointed out that, for ordinary technicians in this technical field, several improvements and modifications can be made to the utility model without departing from the principle of the utility model, and these improvements and modifications also fall within the scope of protection of the claims of the utility model.

Claims

1. An aircraft horizontal tail composite rudder, characterized in that: include: The long beam (100) is C-shaped overall; A trailing edge rib (200) fixed to the outer surface of the long beam (100); An upper skin (300) is fixed on the trailing edge rib (200), the front end of which extends and is fixed on the upper end of the outer surface of the long beam (100); A lower skin (400) is fixed on the trailing edge rib (200), the front end of which extends and is fixed to the lower end of the outer surface of the long beam (100); The trailing edge (500) is fixedly connected to the rear end of the trailing edge rib (200), the rear end of the upper skin (300), and the rear end of the lower skin (400); The front edge rib (600) is fixed to the inner surface of the long beam (100), the front end is arc-shaped, and the rear end is in the same shape as the inner surface of the long beam (100); The leading edge skin (700) is fixed on the leading edge rib (600), the rear end of which is extended and fixed on the upper and lower ends of the outer surface of the long beam (100), and is butted against the front end of the upper skin (300) and the front end of the lower skin (400); The long beam (100), the trailing edge rib (200), the upper skin (300), the lower skin (400), the trailing edge (500), the leading edge rib (600), and the leading edge skin (700) are all made of composite materials.

2. The composite rudder for aircraft tailplane according to claim 1, characterized in that: The upper skin (300) comprises an upper honeycomb (303) sandwiched between an upper outer skin (301) and an upper inner skin (302).

3. An aircraft horizontal tail composite rudder according to claim 1 or 2, characterized in that: The lower skin (400) comprises a lower honeycomb (403) sandwiched between a lower outer skin (401) and a lower inner skin (402).

4. The composite material rudder for aircraft horizontal tail according to claim 1 or 2, characterized in that: The trailing edge rib (200) comprises an end rib (201) and a middle rib (202).

5. The composite material rudder for aircraft horizontal tail according to claim 4, characterized in that: The middle rib (202) is provided with a weight-reducing hole.

6. The composite material rudder for aircraft horizontal tail according to claim 1 or 2, characterized in that: A plurality of leading edge ribs (600) are provided, and every two leading edge ribs (600) are combined with a leading edge skin (700), with a gap left between each combination.

7. The composite rudder for aircraft tailplane according to claim 6, characterized in that: A connecting seat (800) is installed inside the long beam (100) in the gap.

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