A process method for assembling aircraft electrical components based on flexible chemical equipment

Abstract

The present invention relates to a process method for assembling aircraft electrical components based on flexible chemical equipment, wherein the electrical components installed on the tail cone frame assembly of a large aircraft are precisely formed by the flexible chemical equipment, and the lock ring position and the allowance line are marked on the steel wire of the electrical components using a marking pen. The formed electrical components are then assembled through the clamps on the bracket of the tail cone frame assembly of the large aircraft. The electrical components are long in size and rigid, and the raw materials are coiled. Direct installation is affected by the aircraft structure and has great difficulty in forming and poor precision. Therefore, a set of flexible electrical component forming tooling is designed to complete its forming process under the frame, which includes a flat platform, a locking positioning block and a forming pin rod. The present invention effectively solves the processing problems of difficult forming, low processing efficiency and poor manual forming precision when installing electrical components on the tail cone frame assembly of a large aircraft, effectively controls the installation quality and cost problems of this type of parts, and improves assembly efficiency.

Description

Technical Field

[0001] The invention belongs to the field of civil aviation electrical component assembly, and relates to a process method for assembling aircraft electrical components based on flexible chemical equipment. Background Art

[0002] In modern aerospace manufacturing, flexible assembly technology is a key enabler of intelligent assembly. It reduces manual assembly steps and improves assembly precision, ultimately enhancing the overall performance of the aircraft and enabling specialized performance in specific sections. Flexible assembly technology is a key path to improving assembly technology for large aircraft, a research direction for high-quality, high-efficiency assembly, and can effectively enhance the level of intelligent assembly and core competitiveness of large aircraft.

[0003] Traditional manufacturing methods for assembling aviation electrical components often involve first installing positioning brackets and clamps on the aircraft frame, then pre-installing the electrical components based on experience, and finally manually bending and forming them directly onto the aircraft frame. This assembly method significantly increases worker complexity, resulting in long molding times, limited working space, poor molding accuracy, low assembly technology requirements, and high operator skill. The resulting assembled product is poorly precise, prone to various defects and requiring rework and repair. Summary of the Invention

[0004] The purpose of the present invention is to provide a process method for assembling aircraft electrical components based on flexible chemical equipment, thereby increasing the degree of automation, improving manufacturing efficiency and molding accuracy, reducing the difficulty of worker operation, reducing defects generated after assembly, and increasing the manufacturing success rate.

[0005] To achieve the above object, the technical solution adopted by the present invention is:

[0006] A process method for assembling aircraft electrical components based on flexible chemical equipment. The flexible chemical equipment and structure of the process method include: a tail cone frame component, electrical components, a flat platform, a locking positioning block, a pin rod, and a clamp.

[0007] The tail cone frame assembly is a frame structure assembled from aircraft structural parts. The structure is relatively closed, and electrical components are assembled inside the tail cone frame assembly, so the molding operation space is not open.

[0008] The electrical component is composed of a slender metal wire and a surrounding locking ring. The wire has high rigidity and high forming strength. The locking ring slides along the wire, making position control difficult.

[0009] The flexible chemical equipment is composed of a flat platform, a locking positioning block, and a pin rod. The flexible function is achieved by changing the position of the threaded holes and the forming pin rods of the flat platform according to different electrical components. The flat platform is made of a Q235 steel flat plate with a thickness of 20mm, a working surface roughness of 1.6, a platform flatness of ±0.2mm, and an edge bevel or fillet of 0.5mm. An unlimited number of threaded holes are set on the working surface of the flat platform at the bending and long straight positions according to the installation shape of the electrical components, and the bending and forming are completed by the connected pin rods. The outer dimensions of the flat platform leave a 200mm margin based on the outer dimensions of the electrical components, which is used to adjust the position of the threaded holes and facilitate operation. The locking positioning block is clamped by the fixed positioning block and the pressure plate through bolts. The positioning block is not limited to the groove between the wires of the electrical components and is made of Q235 steel. The forming pin rods are used in a single piece in a quantity of 22, and the quantity is determined according to the shape of the electrical components. A single pin is a φ5mm steel cylinder with a thread at one end, a thread depth of 10mm, a total length of 30mm, and a cylindricity of 0.2mm.

[0010] The clamp is a standard part used for fixing and installing the locking ring of the electrical component, and the size of the groove is consistent with the shape of the locking ring of the electrical component.

[0011] A flexible assembly method for assembling aircraft electrical components uses flexible assembly to precisely shape the electrical components to be mounted on the tail cone frame assembly of a large aircraft. The locking ring position and allowance line are marked on the electrical component wire using a marker. The formed electrical components are then assembled to the aircraft's tail cone frame assembly using clamps corresponding to the locking ring position. The electrical component assembly process steps are as follows:

[0012] Step 1: Cut the material according to the designed length of the electrical component and the number of formed lock rings, and add a 100mm margin to the length.

[0013] Step 2: Install the formed pin at the bending position of the electrical component according to the design requirements. Install the pin at the inner R of the bend and install the end locking positioning block.

[0014] Step 3: Fix the cut silk material by locking the positioning block at one end of the flat platform.

[0015] Step 4: Starting with the locking positioning block, complete the bending and forming of the electrical components in sequence through the forming pins. When there is a locking ring between a group of adjacent forming pins, use a marking pen to mark the position of the locking ring and the allowance line to ensure that the part is straightened before each bending, and there is no bending of the electrical components between each group of adjacent forming pins.

[0016] Step 5: After the electrical components are formed, cut the wire size according to the designed size and mark it with a marking pen to ensure the length accuracy. Remove the electrical components and cut them.

[0017] Step 6: Install the clamp on the tail cone frame of the large aircraft at the lock ring position as required by the design.

[0018] Step 7: Assemble the electrical components to the clamps of the tail cone frame according to the marked positions and secure them with bolts, ensuring that the margin lines at both ends of each locking ring meet the design requirements of the drawing.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] This invention utilizes a flexible process for assembling aircraft electrical components, effectively resolving various technical issues such as significantly increased operator difficulty, long molding times, limited workspace, poor molding precision, low assembly technology requirements, poor assembled product precision, and the resulting defects and rework. This significantly increases manufacturing precision while also enhancing the degree of automation, effectively improving the assembly efficiency and quality of electrical components in large aircraft frame assemblies, and increasing the manufacturing success rate. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 Assemble schematic diagrams for electrical components.

[0022] Figure 2 This is a schematic diagram of flexible chemical equipment.

[0023] Figure 3 This is a diagram of the lock ring installation.

[0024] In the figure: 1 tail cone frame assembly, 2 electrical components, 3 flat platform, 4 locking positioning block, 5 pin rod, 6 clamp. DETAILED DESCRIPTION

[0025] The technical solution of the present invention is described clearly and completely below. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of them. All other embodiments improved or adjusted by ordinary technicians in this field based on the embodiments of the present invention are within the scope of protection of the present invention.

[0026] Example 1:

[0027] like Figure 1-3 As shown, a process method for assembling aircraft electrical components based on flexible chemical equipment includes the following steps:

[0028] 1Install the clamp on the tail cone frame assembly according to the design size requirements.

[0029] 2 Cut the material according to the designed length of the electrical components and the number of formed lock rings, and add a 100mm margin to the length.

[0030] 3. Install the formed pins at the bend position of the electrical components according to the design requirements, and install the pins at the inner R of the bend. Install the end locking positioning block.

[0031] 4. Fix the cut silk material by locking the positioning block at one end of the flat platform.

[0032] 5. Starting with the locking positioning block, complete the bending of the electrical components through the forming pins in sequence. When there is a locking ring between a group of adjacent forming pins, use a marking pen to mark the position of the locking ring and the allowance line to ensure that the part is straightened before each bending, and there is no bending of the electrical components between each group of adjacent forming pins.

[0033] 6 After the electrical components are formed, cut the wire size according to the design size and mark it with a marking pen to ensure the length accuracy, then remove the electrical components for cutting.

[0034] 7. On the large aircraft tail cone frame assembly, install the clamp at the lock ring position according to the design requirements.

[0035] 8. Assemble the electrical components to the clamps of the tail cone frame assembly according to the marked positions and secure with bolts. Ensure that the margin lines at both ends of each locking ring meet the design requirements of the drawing.

[0036] Example 2:

[0037] A process method for assembling aircraft electrical components based on flexible chemical equipment. The flexible chemical equipment and structure of the process method include: a tail cone frame assembly, electrical components (wires and locking rings) 2, a flat platform, a locking positioning block, a pin rod, and a clamp.

[0038] The tail cone frame assembly is a frame structure assembled from aircraft structural parts. The structure is relatively closed, and electrical components are assembled inside the tail cone frame assembly, so the molding operation space is not open.

[0039] The electrical component is composed of a slender metal wire and a surrounding locking ring. The wire has high rigidity and high forming strength. The locking ring slides along the wire, making position control difficult.

[0040] The flexible chemical equipment is composed of a flat platform, a locking positioning block, and a pin rod. The flexible function is achieved by changing the position of the threaded holes and the forming pin rods of the flat platform according to different electrical components. The flat platform is made of a Q235 steel flat plate with a thickness of 20mm, a working surface roughness of 1.6, a platform flatness of ±0.2mm, and an edge bevel or fillet of 0.5mm. An unlimited number of threaded holes are set on the working surface of the flat platform at the bending and long straight positions according to the installation shape of the electrical components, and the bending and forming are completed by the connected pin rods. The outer dimensions of the flat platform leave a 200mm margin based on the outer dimensions of the electrical components, which is used to adjust the position of the threaded holes and facilitate operation. The locking positioning block is clamped by the fixed positioning block and the pressure plate through bolts. The positioning block is not limited to the groove between the wires of the electrical components and is made of Q235 steel. The forming pin rods are used in a single piece in a quantity of 22, and the quantity is determined according to the shape of the electrical components. A single pin is a φ5mm steel cylinder with a thread at one end, a thread depth of 10mm, a total length of 30mm, and a cylindricity of 0.2mm.

[0041] The clamp is a standard part used for fixing and installing the locking ring of the electrical component, and the size of the groove is consistent with the shape of the locking ring of the electrical component.

[0042] Example 3:

[0043] A flexible assembly method for assembling aircraft electrical components uses flexible assembly to precisely shape the electrical components to be mounted on the tail cone frame assembly of a large aircraft. The locking ring position and allowance line are marked on the electrical component wire using a marker. The formed electrical components are then assembled to the aircraft's tail cone frame assembly using clamps corresponding to the locking ring position. The electrical component assembly process steps are as follows:

[0044] Step 1: Cut the material according to the designed length of the electrical component and the number of formed lock rings, and add a 100mm margin to the length.

[0045] Step 2: Install the formed pin at the bending position of the electrical component according to the design requirements. Install the pin at the inner R of the bend and install the end locking positioning block.

[0046] Step 3: Fix the cut silk material by locking the positioning block at one end of the flat platform.

[0047] Step 4: Starting with the locking positioning block, complete the bending and forming of the electrical components in sequence through the forming pins. When there is a locking ring between a group of adjacent forming pins, use a marking pen to mark the position of the locking ring and the allowance line to ensure that the part is straightened before each bending, and there is no bending of the electrical components between each group of adjacent forming pins.

[0048] Step 5: After the electrical components are formed, cut the wire size according to the designed size and mark it with a marking pen to ensure the length accuracy. Remove the electrical components and cut them.

[0049] Step 6: Install the clamp on the tail cone frame of the large aircraft at the lock ring position as required by the design.

[0050] Step 7: Assemble the electrical components to the clamps of the tail cone frame according to the marked positions and secure them with bolts, ensuring that the margin lines at both ends of each locking ring meet the design requirements of the drawing.

[0051] The above-described embodiments merely express the implementation methods of the present invention, but they should not be understood as limiting the scope of the patent of the present invention. It should be pointed out that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention, which all fall within the scope of protection of the present invention.

Claims

1. A process for assembling aircraft electrical components based on flexible chemical equipment, characterized by: The electrical components to be installed on the tail cone frame assembly of the large aircraft are precisely formed using flexible chemical assembly. The lock ring position and allowance line are marked on the steel wire of the electrical components using a marking pen. The formed electrical components are then assembled on the tail cone frame assembly of the large aircraft by connecting the corresponding lock ring position with the corresponding clamp. The process steps for assembling electrical components are as follows: a) Cut the material according to the designed length of the electrical components and the number of formed lock rings, and add 100mm margin to the length; b) Install the formed pins at the bend of the electrical components according to the design requirements, with the pins installed at the inner R of the bend; install the end locking positioning blocks; c) Fix the cut silk material by locking the positioning block at one end of the flat platform; d) Starting with the locking positioning block, the electrical components are bent and formed sequentially through the forming pins. When there is a locking ring between adjacent forming pins, use a marking pen to mark the position of the locking ring and the allowance line to ensure that the part is straightened before each bending, and there is no bending between each group of adjacent forming pins. e) After the electrical components are formed, the wire size is cut according to the design size and marked with a marking pen to ensure the length accuracy, and the electrical components are removed for cutting; f) Install the clamp on the tail cone frame of the large aircraft at the lock ring position as required by the design; g) Assemble the electrical components to the clamps of the tail cone frame according to the marked positions and secure with bolts; Ensure that the margin lines at both ends of each lock ring meet the design requirements of the drawing; The flexible chemical equipment and structure of the process method include: a tail cone frame assembly (1), an electrical component (2), a flat platform (3), a locking positioning block (4), a pin rod (5), and a clamp (6); The tail cone frame assembly (1) is a frame-type structure assembled from aircraft structural parts. The structure is relatively closed, and the electrical components are assembled inside the tail cone frame assembly (1). The molding operation space is not open. The flexible chemical equipment is composed of a flat platform (3), a locking positioning block (4), and a pin rod (5); the position of the threaded hole of the flat platform (3) and the forming pin rod (5) is changed according to different electrical components to achieve a flexible function; the working surface of the flat platform (3) is provided with an unlimited number of threaded holes at the bending and long straight positions according to the installation shape of the electrical components, and the bending forming is completed by the connected pin rod (5); the locking positioning block (4) is clamped by the fixed positioning block and the pressure plate through bolts, and the fixed positioning block is not limited to the groove between the wire materials of the electrical component (2) and is made of Q235 steel; the number of the forming pin rod (5) is determined according to the shape of the electrical component; The clamp (6) is a standard part and is used to fix the locking ring of the electrical component (2). The size of the groove is consistent with the shape of the locking ring of the electrical component (2).

2. The process for assembling aircraft electrical components based on flexible chemical equipment according to claim 1, characterized in that: The electrical component (2) is composed of a slender metal wire and a surrounding locking ring.

3. The process for assembling aircraft electrical components based on flexible chemical equipment according to claim 1, characterized in that: The flat platform (3) is a Q235 steel flat plate with a thickness of 20 mm, a working surface roughness of 1.6, a platform flatness of ±0.2 mm, and an edge bevel or fillet of 0.5 mm.

4. The process for assembling aircraft electrical components based on flexible chemical equipment according to claim 1, characterized in that: The single pin (5) is a φ5mm steel cylinder with a thread at one end, a thread depth of 10mm, a total length of 30mm, and a cylindricity of 0.2mm.

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