An aircraft spoiler and flap bay gap control device and method

Abstract

The present application belongs to the technical field of assembly, and relates to an aircraft spoiler and flap bay structure gap control device and method. The device comprises a scribe, the scribe is provided with a main suspension joint for connecting with an actuator cylinder base joint on a wing rear girder, and the scribe is further provided with an auxiliary suspension joint for connecting with an auxiliary front joint, an auxiliary rear joint, a front main joint and a rear main joint on the wing rear girder. The scribe comprises a scribe main body, one side of the scribe main body is provided with a scribe working surface protruding along the heading, the side of the scribe main body connected with the scribe working surface is consistent with the theoretical position of a spoiler leading edge end surface, and the protruding amount of the scribe working surface along the heading and the gap size of the aircraft spoiler and the flap bay structure are consistent. The present application solves the problem that the prior art uses a scribing method taking the wing structure rear girder of the aircraft as a reference to control the gap between the spoiler and the flap bay structure. The method is affected by error transmission, and is prone to cause the problem of gap out-of-tolerance.

Description

Technical Field

[0001] This invention belongs to the field of assembly technology and relates to the assembly and processing method of aviation system structural components, specifically to a device and method for controlling the gap between an aircraft spoiler and a flap compartment structure. Background Technology

[0002] The spoilers inside the flap nacelles of a certain type of aircraft are arranged on the upper surface of the flap nacelles of the left and right middle outer wings, such as... Figure 1 , 2 As shown in Figure 3, Figure 1 The shape of the spoiler of this certain aircraft is shown. Figure 2 The spoiler suspension joint is shown. Figure 3 The diagram shows the connection joint between the wing and the spoiler. Each spoiler consists of four pieces along its span. The spoilers are made of composite materials, and each piece is equipped with a main suspension joint and an auxiliary suspension joint. They are connected to the wing using a fork-type joint. The spoilers open upwards to an angle of not less than 60°. Each spoiler suspension joint consists of a main suspension joint, an auxiliary suspension joint, and an actuator base joint. There are requirements for the leading edge clearance between the wing and the spoiler, such as... Figure 4 As shown, during the spoiler assembly process, the assembly technical requirements are: the gap between the leading edge of the spoiler and the upper skin of the flap pod should be 18.5mm-20.5mm (e.g., ...). Figure 4 (As shown). Excessive clearance here will affect the opening and closing of the spoiler, causing it to malfunction. The previous processing method was as follows: after the wing flap nacelles were assembled, the product was removed from the assembly jig, and the composite spoiler suspension connector was aligned with the connector on the wing for connection. After adjusting the spoiler's shape, the clearance between the spoiler and flap nacelles was measured. If the clearance did not meet the requirements, a margin line was marked on the spoiler, and then the spoiler manufacturer was notified to send personnel to the site to repair the composite spoiler to meet the clearance requirements. Currently, the composite processing technology in aircraft assembly plants is not mature, requiring coordination with the composite manufacturer for on-aircraft reprocessing of the spoiler for each aircraft. This process is time-consuming and costly, severely restricting the pace of mass production. Summary of the Invention

[0003] Purpose of the invention: This invention addresses the problem that existing methods for controlling the gap between spoilers and flap nacelles, which use a scribing method based on the rear spars of the aircraft wing structure, are susceptible to error propagation and are prone to causing gap deviations.

[0004] Technical solution

[0005] A device for controlling the clearance between an aircraft spoiler and a flap compartment includes a scribing device. The scribing device is provided with a main suspension joint 1 for connecting to an actuator base joint on the rear wing spars. The scribing device is also provided with auxiliary suspension joints for connecting to auxiliary front joints, auxiliary rear joints, a front main joint, and a rear main joint on the rear wing spars. The scribing device includes a scribing device body. One side of the scribing device body is provided with a scribing working surface 3 that protrudes along the flight direction. The side of the scribing device body that connects to the scribing working surface 3 is theoretically aligned with the leading edge end face of the spoiler. The amount of protrusion of the scribing working surface 3 along the flight direction is consistent with the clearance dimension between the aircraft spoiler and the flap compartment.

[0006] Furthermore, the main suspension joint has a bent structure, which does not interfere with the scribing working surface 3. This allows the scribing device to be stably supported on the joint on the rear wing spars, avoiding surrounding structures.

[0007] Furthermore, the main body of the marking device has a hollow structure to reduce the weight of the control device. This maximizes cost savings and makes it easier for operators to use.

[0008] A method for controlling the clearance between an aircraft spoiler and a flap nacelle structure includes the following steps:

[0009] Step 1: Position and connect the aircraft spoiler and flap compartment structure clearance control device on the corresponding joint of the wing rear spars.

[0010] Step 2: Use the aircraft spoiler and flap cabin structural clearance control device to draw the allowance line on the T-shaped profile opposite the leading edge of the aircraft wing flap cabin and spoiler.

[0011] Step 3: Remove the aircraft spoiler and flap compartment structure clearance control device from the corresponding joint on the rear wing spar, and repair the T-profile along the allowance line.

[0012] Furthermore, step 1 specifically involves: during the flap pod assembly process, using pins to connect the main suspension connector 1 of the control device to the actuator base connector on the wing spars, and using pins to connect the auxiliary suspension connector 2 of the control device to the auxiliary front connector, auxiliary rear connector, front main connector, and rear main connector on the wing spars.

[0013] Furthermore, after the control device is connected to the corresponding joint of the wing's rear spars, the scribing device body simulates the state of the spoiler when it is assembled in the flap nacelle, and the protrusion of the scribing working surface 3 simulates the structural gap between the aircraft spoiler and the flap nacelle. At this time, the working surface 3 can be regarded as the theoretical rear end face of the T-shaped profile opposite the leading edge of the aircraft wing flap nacelle and the spoiler.

[0014] Furthermore, step 2 specifically involves: attaching the bottom surface of the scribing working surface 3 to the upper surface of the T-profile opposite the front edge of the spoiler, and using a scribing tool to scribing the allowance line on the T-profile along the side of the scribing working surface 3.

[0015] Furthermore, step 3 specifically involves: removing the aircraft spoiler and flap compartment structure clearance control device from the corresponding joint on the wing rear spars; repairing the T-profile along the allowance line; and then proceeding with the subsequent structural assembly work as normal. After the overall wing structure is removed from the frame, connect the spoiler to the auxiliary front joint, auxiliary rear joint, front main joint, and rear main joint on the wing rear spars. At this point, it can be ensured that the gap between the T-profile end face and the leading edge of the spoiler is 18.5mm-20.5mm, and there is no need to repair the composite spoiler again.

[0016] Beneficial effects

[0017] This invention provides a simple, convenient, accurate, reliable, efficient, and effective device and method for controlling the gap between the wing flap compartment and the spoiler. The control device is set up by simulating the spoiler's suspension on the aircraft, using the spoiler and the structure as references to draw structural allowance lines. This ensures that the gap between the spoiler and the flap compartment structure meets design requirements during subsequent spoiler installation, eliminating the need for on-site adjustments. It solves the problem of existing methods that use the rear wing spars as a reference for controlling the gap between the spoiler and flap compartment structure, which are susceptible to error propagation and prone to causing gap deviations. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the spoiler layout for this product;

[0019] Figure 2 This is a schematic diagram of the spoiler connector;

[0020] Figure 3 This is a schematic diagram of the spoiler suspension joint;

[0021] Figure 4 This is a schematic diagram showing the required gap between the spoiler and the structural profile;

[0022] Figure 5 This is a schematic diagram of the aircraft spoiler and flap cabin structure clearance control device of the present invention;

[0023] Among them, 1. main suspension joint, 2. auxiliary suspension joint, and 3. scribing work surface. Detailed Implementation

[0024] The following description, in conjunction with the accompanying drawings, further illustrates the aircraft spoiler and flap cabin structure clearance control device and method of the present invention:

[0025] like Figure 5As shown, a clearance control device between an aircraft spoiler and a flap cabin structure is provided, which mainly includes three parts: a main suspension joint 1, an auxiliary suspension joint 2, and a scribing working surface 3.

[0026] Specifically, the device includes a scribing device, on which a main suspension connector 1 is provided for connection to the actuator base connector on the rear wing spars. The scribing device is also provided with auxiliary suspension connectors for connection to the auxiliary front connector, auxiliary rear connector, front main connector, and rear main connector on the rear wing spars. The scribing device includes a scribing device body, on which a scribing working surface 3 protruding along the flight direction is provided on one side. The side of the scribing device body that connects with the scribing working surface 3 is theoretically aligned with the leading edge end face of the spoiler. The amount of protrusion of the scribing working surface 3 along the flight direction is consistent with the clearance dimension between the aircraft spoiler and the flap compartment structure.

[0027] In this embodiment, the main suspension joint is a bent structure that does not interfere with the scribing working surface 3. This allows the scribing device to be stably supported on the joint on the wing's rear spars, avoiding surrounding structures.

[0028] In this embodiment, the main body of the marking device has a hollow structure to reduce the weight of the control device. This maximizes cost savings and makes it easier for operators to use.

[0029] Another embodiment of the present invention is a method for providing a clearance control device between an aircraft spoiler and a flap nacelle structure, comprising the following steps:

[0030] Step 1: Position and connect the aircraft spoiler and flap compartment structural clearance control device on the corresponding joints of the wing rear spar; Specifically, during the flap compartment assembly process, use pins to connect the main suspension joint 1 of the control device to the actuator base joint on the wing spar, and use pins to connect the auxiliary suspension joint 2 of the control device to the auxiliary front joint, auxiliary rear joint, front main joint, and rear main joint on the wing spar.

[0031] After the control device is connected to the corresponding joint of the wing's rear spars, the scribing device body simulates the state of the spoiler when it is assembled in the flap nacelle, and the protrusion of the scribing working surface 3 simulates the structural gap between the aircraft spoiler and the flap nacelle. At this time, the working surface 3 can be regarded as the theoretical rear end face of the T-shaped profile opposite the leading edge of the aircraft wing flap nacelle and the spoiler.

[0032] Step 2: Use the aircraft spoiler and flap cabin structural clearance control device to draw the allowance line on the T-profile opposite the leading edge of the aircraft wing flap cabin and spoiler; Step 2 specifically involves: attaching the bottom surface of the scribing working surface 3 to the upper surface of the T-profile opposite the leading edge of the spoiler, and using a scribing tool to draw the allowance line on the T-profile along the side of the scribing working surface 3.

[0033] Step 3: Remove the aircraft spoiler and flap compartment structure clearance control device from the corresponding joint on the rear wing spar, and repair the T-profile along the allowance line.

[0034] Step 3 specifically involves: removing the aircraft spoiler and flap compartment structure clearance control device from the corresponding joint on the wing rear spars. Following the allowance line, the T-profile is repaired, and then the subsequent structural assembly work proceeds normally. After the overall wing structure is removed from the frame, the spoiler is connected to the auxiliary front joint, auxiliary rear joint, front main joint, and rear main joint on the wing rear spars. At this point, the clearance between the T-profile end face and the leading edge of the spoiler is guaranteed to be 18.5mm-20.5mm, eliminating the need for further repair of the composite spoiler.

[0035] The present invention also provides another embodiment of a method for controlling the gap between an aircraft spoiler and a flap nacelle structure, comprising the following steps:

[0036] Step 1, Appendix Figure 3 As shown, connect the product actuator base connector to the main connector 1 of the scribing device, and then connect the front main connector, rear main connector, auxiliary front connector, and auxiliary rear connector to the auxiliary connector 2 of the scribing fixture in sequence. After fixing with positioning pins, the allowance line can be drawn on the structural profile according to the scribing working surface 3 of the scribing device.

[0037] Step two: Adjust the structural profiles according to the allowance lines, then proceed with subsequent structural assembly work. After the subsequent positioning work is completed, attach the... Figure 2 The spoiler is installed on the structure, and the effect after installation is shown in the attached figure. Figure 1 At this point, the gap between the leading edge of the spoiler and the structural T-shaped profile can meet the requirements for attachment. Figure 4 Require.

[0038] The marking fixture in step one can also be set up by setting support connection points on the assembly jig, but this solution chooses to set up the fixture by using the product as the assembly positioning reference.

[0039] The second step of the marking method can also be to use a pencil or a drawing needle to mark the line on the product along the end face of the marking line, but this solution prefers to use a special marking tool to mark the line.

[0040] The device and method of this invention are simple, easy to operate, accurate, reliable, efficient, and of stable quality. They are convenient and effective, simulating the state of a spoiler suspended on an aircraft to set up the control device and method, using the spoiler and structure as references to draw structural allowance lines. This ensures that the clearance between the spoiler and the flap compartment structure meets design requirements during subsequent spoiler installation, eliminating the need for on-site adjustments. This solves the problem of existing methods that use the rear spar of the aircraft wing structure as a reference for drawing lines to control the clearance between the spoiler and the flap compartment structure, which are susceptible to error propagation and prone to causing clearance deviations.

Claims

1. A device for controlling the gap between an aircraft spoiler and a flap compartment structure, characterized in that, The system includes a line marking device, which is equipped with a main suspension connector for connecting to the actuator base connector on the rear wing spars. The line marking device is also equipped with auxiliary suspension connectors for connecting to auxiliary front connectors, auxiliary rear connectors, front main connectors, and rear main connectors on the rear wing spars. The line marking device includes a line marking device body, and one side of the line marking device body is provided with a line marking working surface that protrudes along the flight direction. The side of the line marking device body that connects to the line marking working surface is theoretically aligned with the leading edge end face of the spoiler. The amount of protrusion of the line marking working surface along the flight direction is consistent with the clearance dimension between the aircraft spoiler and the flap compartment structure. A method for controlling the clearance between an aircraft spoiler and a flap nacelle structure includes: Step 1: Position the aircraft spoiler and flap nacelle structural clearance control device on the corresponding joint of the wing rear spar; after the control device is connected to the corresponding joint of the wing rear spar, the scribing machine body simulates the state when the spoiler is assembled in the flap nacelle, and the protrusion of the scribing working surface simulates the structural clearance between the aircraft spoiler and the flap nacelle. Step 2: Use the aircraft spoiler and flap compartment structure clearance control device to draw the allowance line on the T-shaped profile opposite the leading edge of the aircraft wing flap compartment and spoiler; that is, put the bottom surface of the scribing working surface into contact with the upper surface of the T-shaped profile opposite the leading edge of the spoiler, and use the scribing tool to draw the allowance line on the T-shaped profile along the side of the scribing working surface. Step 3: Remove the aircraft spoiler and flap compartment structure clearance control device from the corresponding joint on the rear wing spar, and repair the T-profile along the allowance line.

2. The aircraft spoiler and flap compartment structure clearance control device according to claim 1, characterized in that, The main suspension joint has a bent structure and does not interfere with the scribing work surface.

3. The aircraft spoiler and flap compartment structure clearance control device according to claim 1, characterized in that, The main body of the scribing device is hollow, which is used to reduce the weight of the control device.

4. The aircraft spoiler and flap compartment structure clearance control device according to claim 1, characterized in that, Step 1 specifically involves using pins during the flap pod assembly process to connect the main suspension connector of the control device to the actuator base connector on the wing spars. Pins are also used to connect the auxiliary suspension connector of the control device to the auxiliary front connector, auxiliary rear connector, front main connector, and rear main connector on the wing spars.

5. The aircraft spoiler and flap compartment structure clearance control device according to claim 1, characterized in that, Step 3 specifically involves: removing the aircraft spoiler and flap compartment structure clearance control device from the corresponding joint on the rear wing spar, and repairing the T-profile along the allowance line to ensure that the clearance between the end face of the T-profile and the leading edge of the spoiler is 18.5mm-20.5mm.

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