Supporting rib, control surface and method

Abstract

The invention discloses a supporting rib, a control surface and a method. Comprising a rib body (1) integrally of a trapezoidal structure, flanges (2) are arranged at the large end and the two side edges of the rib body (1), and the flanges (2) on the two side edges enable the small end of the rib body (1) to be of an opening structure (3). And the opening structure (3) is connected with the connecting rib (4) through a connecting piece.

Description

Technical Field

[0001] The invention relates to the technical field of aerospace manufacturing and aircraft assembly, and in particular to a glass cloth honeycomb high-quality hole-making tool and method. Background Art

[0002] Composite materials are lightweight and high-strength, and have been widely used in the manufacture of aircraft wing edge structural parts to reduce aircraft weight and improve overall performance. The control surface structure of aircraft wings is generally a typical honeycomb sandwich structure. In order to further reduce the weight of the aircraft, the control surface structure including ailerons, flaps, split rudders, rudders and other products often removes some of the heavier honeycombs and replaces them with lighter beams (main beams, auxiliary beams / secondary beams / rear beams) and support rib structures to ensure product strength and stiffness (such as Figure 1 As shown). Aircraft control surface products are usually manufactured using a secondary bonding process, which requires a thermal history. Due to the mismatch of thermal expansion coefficients of various components and molds, the beams of the products are deformed after bonding. At the same time, in order to ensure the quality of product bonding and prevent non-destructive problems such as debonding of panels during the bonding process, it is necessary to reduce the constraints on the parts and provide sufficient degrees of freedom, which leads to the offset of various parts (including beams) relative to the theoretical state after the structural parts are bonded. The above two factors cause the relative position between the main beam and the rear beam to not meet the design requirements. When installing the support ribs, the gap between the support ribs and the main beam and rear beam is too large, or the support ribs interfere with the main beam and rear beam and cannot be installed. These greatly affect the manufacturing progress, quality and safety of the products, and may even lead to product scrapping.

[0003] At present, the industry generally adopts the method of adding gaskets to the contact surface between the support rib and the beam, and manually grinding and making conformal gaskets to compensate for the deformation and offset of the beam caused by the bonding process. However, the above solution has many disadvantages: (1) Directly adding gaskets to the structure changes the thickness of the sandwich between the support rib and the beam, so it is necessary to change the standard parts with longer specifications to achieve a smooth connection, which increases the cost of product manufacturing. (2) The method of directly adding gaskets for compensation is more inclined to solve the problem of increasing the distance between the main beam and the rear beam, but it is difficult to solve the installation problem of decreasing the distance between the beams. (3) Adding gaskets to the contact surface between the support rib and the beam requires repeated manual grinding and adaptation to achieve the conformal shape of the rib, beam, and gasket, which greatly increases the manufacturing cycle. Summary of the invention

[0004] The purpose of the present invention is to provide a support rib, a control surface and a method. The present invention improves the efficiency of aircraft assembly.

[0005] Technical solution: A supporting rib comprises a rib body with an overall trapezoidal structure, wherein flanges are arranged on the large end and both sides of the rib body, and the flanges on both sides make the small end of the rib body present an open structure; the open structure is connected to the connecting rib via a connecting piece.

[0006] In the aforementioned supporting ribs, the connecting ribs are T-shaped ribs, C-shaped ribs, L-shaped ribs or double-sided L-shaped ribs.

[0007] In the aforementioned supporting ribs, the connecting ribs are made of composite material, aluminum alloy and / or stainless steel.

[0008] A control surface for an airplane comprises the above-mentioned supporting rib; the flange at the large end of the rib body is connected to the main beam via a connecting piece; and the connecting ribs are connected to the rear beam via the connecting piece.

[0009] In the aforementioned rudder surface, the bonding surfaces of the connecting ribs, the rib body, the rear beam, and the main beam are sealed using sealants and adhesives;

[0010] In the above-mentioned rudder surface, each connecting part is wet assembled using sealant and adhesive.

[0011] In the aforementioned rudder surface, the sealant is HM112 or HM109, and the adhesive is J-168 or DG-3.

[0012] In the aforementioned rudder surface, the connecting members are bolts or draw nails; the bolts include high-locking bolts, self-locking bolts and / or ordinary bolts.

[0013] A method for assembling a rudder surface as described above comprises the following steps:

[0014] S1. Position the connecting ribs to ensure that the relative position of the connecting ribs and the rear beam is correct and fits tightly;

[0015] S2. Drill the initial hole for connecting the connecting rib and the rear beam, and expand and ream to the final hole;

[0016] S3. Use the connector to pass through the end hole of step S2 to connect the connecting ribs to the rear beam;

[0017] S4. Pre-install the rib body; use the assembly tool to adjust the position of the rib body to ensure that the rib body is closely fitted with the web surface of the main beam and the connecting ribs, and then use the tool to fix the rib body;

[0018] S5. Drill the initial holes for connection between the rib body and the main beam, and between the rib body and the connecting reinforcement, and expand and ream to the final holes;

[0019] S6. Use connectors to connect the rib body and the connecting ribs;

[0020] S7. Use sealants and adhesives to seal the mating surfaces of connecting ribs, rib bodies, rear beams, and main beams. Use sealants and adhesives to wet-assemble the connectors.

[0021] Beneficial effect: The present invention provides a support rib that can adapt to deformation of aircraft rudder products, which can achieve simple and efficient installation under the premise that the relative distance between the main beam and the rear beam changes during the bonding process of the aircraft rudder products and there is a small angle (within 10°) deviation in the relative position of the web surface of the main beam and the rear beam.

[0022] The supporting rib involved in the present invention is divided into two parts. Different from the traditional supporting ribs and beams in which the distance and angle of the two flange surfaces cannot be changed, the supporting ribs of the present invention adopt a split structure, which can be connected to the rear beam and the main beam respectively, and then the supporting rib body and the connecting ribs are connected, which can adapt to the distance and angle changes between the rear beam and the main beam of the adhesively deformed product.

[0023] The present invention can be widely applied to all scenarios where support ribs need to be installed on aircraft, greatly reducing the difficulty of installation, ensuring installation quality, increasing deformation adaptability, and being compatible with more working conditions.

[0024] In summary, the present invention adopts a split support rib, which solves the problem of gap or interference in the installation of the support rib when the relative distance and angle between the main beam and the rear beam change after the composite rudder products are glued. The installation period after the problem occurs is shortened by more than 80%, the installation quality is improved, and the deformation adaptability is increased. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 This is a schematic diagram of the traditional rudder assembly structure;

[0026] Figure 2 It is a schematic diagram of the supporting rib structure of the present invention;

[0027] Figure 3 It is a schematic diagram of the connecting reinforcement structure. DETAILED DESCRIPTION

[0028] Embodiment 1. A supporting rib comprises a rib body 1 of overall trapezoidal structure, wherein flanges 2 are arranged at the large end and both sides of the rib body 1, and the flanges 2 at both sides make the small end of the rib body 1 present an open structure 3; the open structure 3 is connected to the connecting rib 4 via a connecting piece.

[0029] The aforementioned connecting ribs 4 are T-shaped ribs, C-shaped ribs, L-shaped ribs or double-sided L-shaped ribs.

[0030] The aforementioned connecting rib 4 is made of composite material, aluminum alloy and / or stainless steel.

[0031] A control surface for an aircraft comprises the aforementioned supporting rib; a flange 2 at the large end of a rib body 1 is connected to a main beam via a connector; and a connecting rib 4 is connected to a rear beam via a connector.

[0032] Use sealants and adhesives to seal the joint surfaces of the connecting ribs, rib bodies, rear beams, and main beams;

[0033] Each connector is wet assembled using sealants and adhesives

[0034] The aforementioned sealant is HM112 or HM109, and the adhesive is J-168 or DG-3.

[0035] The aforementioned connecting piece is a bolt or a draw nail; the bolt includes a high-locking bolt, a self-locking bolt and / or a common bolt.

[0036] like Figure 2 As shown, the support rib of the present invention is composed of three parts, a rib body (open at the small end and without flange), connecting ribs, and connecting parts (bolts, draw nails, etc.).

[0037] The rib body adopts the traditional supporting rib form, and the flange profile is set according to the inner cavity profile of the product. The flange is removed at the small end and set to an open state.

[0038] The connecting ribs can be made of composite materials, or metals such as aluminum alloy and stainless steel. Figure 2 The T-shaped ribs shown can also be Figure 3 C-shaped ribs, L-shaped ribs, double-sided L-shaped ribs, etc., can also be reinforced by adding ribs inside the ribs. Its material, structure, size, thickness and other factors need to be optimized by structural designers through a series of boundary conditions (such as structural strength, structural weight, whether it is anti-corrosion and other indicators) simulation during the product design stage. The connection rib form of products with different structural forms and different load conditions needs to be determined based on the actual simulation results.

[0039] The device and method of the present invention are used in the following steps:

[0040] (1) Position the connecting ribs to ensure that they are in the correct relative position to the rear beam and fit tightly. The connecting ribs can be positioned using assembly tooling or using the connecting rib position lines returned by the mold when the rear beam is formed.

[0041] (2) Drill the initial hole for connecting the connecting bar and the rear beam, and expand and ream to the final hole. The drilling can be done using the drilling jig of the tooling, or by marking the hole, or the initial hole of the connecting bar can be used as a guide hole.

[0042] (3) Use standard parts to connect the connecting ribs and rear beams. The standard parts used for connection can be MBF or CR pull nails.

[0043] (4) Pre-install the rib body and use the assembly tool to adjust the position of the rib body to ensure that the rib body is tightly fitted with the web surface of the main beam and the connecting ribs. At this time, use the tool and tools (bow clamps, fish-mouth pliers) to fix the rib body.

[0044] (5) Drill the initial holes for connecting the rib body to the main beam and the rib body to the connecting rib, and expand and ream to the final holes. The holes can be drilled using the jig of the tooling, or by marking the holes, or the initial holes in the connecting rib can be used as guide holes.

[0045] (6) Use standard parts to connect the rib body and the connecting ribs. The standard parts used for connection can be high-locking bolts, self-locking bolts, ordinary bolts, etc.

[0046] (7) Use sealants (HM112, HM109, etc.) and adhesives (J-168, DG-3, etc.) to seal the mating surfaces of the connecting ribs, rib bodies, rear beams, and main beams. The standard parts are also installed using sealants and adhesives for wet assembly.

[0047] (8) The recommended installation sequence is to install the connecting ribs first and then the rib body. The installation sequence may be changed based on actual conditions.

[0048] Example 2. In the production of a certain type of aircraft aileron product, it was found that the main beam of the product had a certain degree of distortion when the support ribs were installed (the actual position of the web surface of the main beam at the support rib installation position was calculated to have an angle of 8.2° with the theoretical position), and the distance between the main beam and the rear beam was reduced by about 2mm. The traditional support rib form cannot meet the installation requirements, and the assembly process is stagnant. Using the support rib design concept of the present invention, structural simulation was carried out for the three structural forms of C-type, T-type, and L-type support rib connecting ribs. Through the constraints of strength, weight, and anti-heteroelectric corrosion, it was calculated that:

[0049] 1) All three structural forms can meet the use requirements in terms of strength, and there is no need to continue to use reinforcing ribs on the structure;

[0050] 2) In terms of weight index, the selection of L-shaped connecting ribs can reduce the total weight of the structure to the greatest extent;

[0051] 3) The use of aluminum alloy can minimize the manufacturing cycle and ensure product delivery nodes. Its anti-heteropotential corrosion can be treated by sulfuric acid anodizing, dichromate filling, and surface primer spraying.

[0052] After the above process iterations, it was finally determined that the flange surface (thickness 2mm) at the small end of the original support rib was removed, and the support rib height was further removed by about 2mm. The aluminum alloy ribs: size (25-30) mm × (25-30) mm × (40-45) mm, thickness 2mm, aluminum alloy material 7050-T7451, sulfuric acid anodized, dichromate filled, surface sprayed with QH-15 primer treatment, perfectly realized the connection between the support rib and the main beam and rear beam when the main beam is twisted and the distance between the main beam and the rear beam is shortened, ensuring the smooth assembly of the product and delivery according to the node.

[0053] Example 3. Example 2 is a solution developed after a problem was encountered during the assembly of an aircraft aileron product, which solved the problem that the original support rib could no longer be installed. This case provides a new idea for the design and installation of support ribs for subsequent product design and manufacturing.

[0054] In another type of aircraft aileron product, the support rib structure used in the present invention was directly used in the design stage for structural design, and it was determined that L-shaped composite connecting ribs were used for structural connection. During production and manufacturing, it was found that the product's secondary beam was bent and deformed, and the maximum distance between the main beam and the secondary beam increased by 3mm. Using the support ribs of the present invention, the operator was able to complete the assembly and manufacturing of 12 support ribs within 2 hours.

[0055] A comparative test was planned to solve this problem, namely the solution of the present invention, the compensation solution of grinding the symbol-shaped gasket, and the solution of increasing the grinding margin of 4mm at the small end of the support rib (reserved during the manufacturing process). The experimental results are as follows:

[0056] 1) In terms of structural strength, the above three solutions can meet the strength requirements.

[0057] 2) In terms of manufacturing cycle, compared with the solution of repeatedly grinding and repairing the shaped gasket and the solution of reserving the grinding margin of the small end edge strip of the support rib, which takes at least 1.5 days, this solution reduces the time by about 95%. At the same time, the present invention does not change the thickness of the interlayer in the connection area between the support rib and the main beam and the auxiliary beam, and does not need to change the specifications of standard parts, saving the procurement cycle caused by the change of standard parts specifications by at least weeks.

[0058] With the installation period greatly shortened, this solution has extremely significant advantages in application and promotion.

Claims

1. A supporting rib, characterized in that: The rib body (1) comprises a rib body (1) with an overall trapezoidal structure. The large end and both side edges of the rib body (1) are provided with flanges (2). The flanges (2) on both side edges make the small end of the rib body (1) present an open structure (3). The open structure (3) is connected to a connecting rib (4) via a connecting piece.

2. The support rib according to claim 1, characterized in that: The connecting ribs (4) are T-shaped ribs, C-shaped ribs, L-shaped ribs or double-sided L-shaped ribs.

3. The supporting rib according to claim 1, characterized in that: The connecting rib (4) is made of composite material, aluminum alloy and / or stainless steel.

4. A control surface for an aircraft, characterized in that: It comprises the supporting rib as claimed in any one of claims 1 to 3; the flange (2) at the large end of the rib body (1) is connected to the main beam via a connecting piece; and the connecting rib (4) is connected to the rear beam via the connecting piece.

5. The rudder surface according to claim 4, characterized in that: Use sealants and adhesives to seal the fitting surfaces of the connecting ribs, rib bodies, rear beams, and main beams.

6. The rudder surface according to claim 4, characterized in that: Each connector is wet assembled using sealants and adhesives.

7. The rudder surface according to claim 6, characterized in that: The sealant is HM112 or HM109, and the adhesive is J-168 or DG-3.

8. The rudder surface according to claim 4, characterized in that: The connecting piece is a bolt or a draw nail; the bolt includes a high-locking bolt, a self-locking bolt and / or a common bolt.

9. A method for assembling a rudder surface according to any one of claims 4 to 8, characterized in that: The steps include: S1. Position the connecting rib (4) to ensure that the connecting rib (4) and the rear beam are in the correct relative position and fit tightly; S2. Drilling the initial hole for connecting the connecting rib (4) with the rear beam, and expanding and reamed to the final hole; S3. Connect the connecting rib (4) to the rear beam by passing the connecting member through the terminal hole of step S2; S4. Pre-install the rib body (1); use the assembly tool to adjust the position of the rib body (1) to ensure that the rib body (1) fits tightly with the web surface of the main beam and the connecting rib (4), and then use the tool to fix the rib body (1); S5. Drilling the initial connection holes between the rib body (1) and the main beam, and the rib body (1) and the connecting rib (4), and expanding and reaming to the final hole; S6. Use connectors to connect the rib body and the connecting ribs; S7. Use sealants and adhesives to seal the mating surfaces of connecting ribs, rib bodies, rear beams, and main beams. Use sealants and adhesives to wet-assemble the connectors.

Images