Method of reaming a hinge joint of a movable aircraft component

Abstract

The application discloses a hinge hole drilling method for a hinge joint of an aircraft movable component, adopts a hinge joint drilling tool for assisting in hinge hole drilling work of the hinge joint connected between the aircraft movable component and an aircraft fixed component, and the hinge joint drilling tool for the aircraft movable component comprises a tool main body, at least two groups of hinge joint positioning assemblies corresponding to the hinge joint in one-to-one mode, a plurality of tool positioning pieces and a plurality of aircraft fixed component positioning pieces which are detachably fixed on the tool main body. The application effectively guarantees the coaxial degree of the hinge hole drilling on different hinge joints, and effectively improves the installation precision of the aircraft movable component. The hinge joint drilling tool for the aircraft movable component can be repeatedly used, and the hinge hole drilling is convenient to position, thereby effectively improving the assembly efficiency of the aircraft movable component while reducing the assembly cost of the aircraft movable component.

Description

Technical Field

[0001] This invention relates to the field of aircraft moving parts assembly technology, and in particular to a method for creating hinge holes in the hinge joints of aircraft moving parts. Background Technology

[0002] In aircraft manufacturing, after assembling the fuselage components, moving parts such as boarding doors, emergency exits, and access doors need to be assembled and installed onto the fixed components of the aircraft. Hinges are often used to connect these moving parts. However, due to rigidity or deformation issues with the openings of these moving parts, misalignment of the installation points can occur. When moving parts are connected to fixed components via hinges, the coaxiality of the hinged components cannot meet the high precision requirements of the design, thus affecting the installation quality of the moving parts.

[0003] Chinese patent application CN113200151A discloses a high-precision constant-force assembly method for large aircraft cabin doors. The method uses door samples and door frame samples to adjust the fit between the aircraft cabin door and the door frame. The door sample consists of a door sample base, a door hinge connector, and tension / compression sensors. The door sample base has a frame structure, and its frame shape matches the shape of the door in the overlapping area of ​​the aircraft cabin door and door frame. The door hinge connector is fixed to the outer ring of the door sample base and has the same shape and position as the cabin door hinge connector. Tension / compression sensors are installed between the hinge connector and the door sample base. The door frame sample consists of a door frame sample base, a door frame hinge connector, and tension / compression sensors. The door frame sample base has a perimeter frame structure, and its shape matches the shape of the door frame in the overlapping area of ​​the aircraft cabin door and door frame. The door frame hinge connector is fixed to the inner ring of the door frame sample base and has the same shape and position as the cabin door frame hinge connector. Tension / compression sensors are installed between the door frame hinge connector and the door frame sample base.

[0004] The technical solution disclosed in the aforementioned patent application monitors the force value by setting a pressure sensor between the hinge joint of the aircraft cabin door and the door frame sample, so as to adjust the shaft hole fit accuracy of the hinge joint. However, the technical solution of this patent requires setting a pressure sensor at the installation point of each hinge joint for real-time monitoring, which will undoubtedly increase the cost of assembly work. In addition, the installation and debugging of pressure sensors will consume a lot of manpower, which is not conducive to controlling production costs. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a method for creating a hinge hole in the hinge joint of an aircraft moving part, which can effectively improve the assembly accuracy of the aircraft moving part and reduce the assembly cost.

[0006] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is: a method for hinge hole drilling of aircraft moving parts, which uses an aircraft moving parts hinge hole drilling tooling to assist in the hinge hole drilling of the hinge joint connecting the aircraft moving parts and the aircraft fixed parts. The aircraft moving parts hinge hole drilling tooling includes a tooling body, on which at least two sets of hinge joint positioning assemblies corresponding one-to-one with the hinge joints, multiple tooling positioning parts, and multiple aircraft fixed part positioning parts are detachably fixed. The hinge joint positioning assembly includes a fixed seat and a positioning piece. The fixed seat is fixed on the tooling body, and the positioning piece is detachably connected to the fixed seat. The positioning piece is provided with a hinge hole positioning hole and multiple sets of positioning piece mounting hole groups, and the positioning piece mounting hole group includes at least one positioning piece mounting hole.

[0007] The method for drilling the hinge joint of the aircraft moving part includes the following steps:

[0008] Step 1: Place the main body of the aircraft moving part hinge joint hinge hole tooling in the installation position of the aircraft moving part in the aircraft fixed part, connect and fix the main body of the tooling to the assembly frame through the tooling positioning component, connect and fix the main body of the tooling to the aircraft fixed part through the aircraft fixed part positioning component, and fix the hinge joint positioning component on the tooling main body through the pin.

[0009] Step 2: Align the bushing of the hinge joint with the axial positioning hole of the positioning piece on the corresponding hinge joint positioning assembly. After passing through the locating hole and the bushing of the hinge joint with the initial hole positioning pin, fix the hinge joint on the fixed base.

[0010] Step 3: Remove the initial hole positioning pin and remove the pin that fixes the hinge joint positioning assembly. Select the same set of mounting positioning holes according to the misalignment of the mounting holes on the positioning plates in each set of hinge joint positioning assemblies. Then, use the pin to cooperate with the selected set of mounting positioning holes to re-fix the hinge joint positioning assembly to the tooling body.

[0011] Step 4: Through the reaming holes on the positioning plate, ream the bushing of the hinge joint and make it into a final hole. After the reaming is completed, fix the hinge joint to the aircraft fixed component.

[0012] Step 5: After completing the hinge holes for all hinge joints, remove the hinge joints from the mounting base and remove the main fixture from the aircraft mounting components.

[0013] As an improvement to the above solution: at least three sets of positioning plate mounting hole groups are provided on the positioning plate, each set of positioning plate mounting hole groups includes two positioning plate mounting holes spaced apart, so that the two positioning plate mounting holes in the same set of positioning plate mounting hole groups are spaced apart in the length direction of the positioning plate, and the three sets of positioning plate mounting hole groups are arranged parallel and equidistantly in the width direction of the positioning plate.

[0014] As an improvement to the above solution: two fixed seats and two positioning plates are provided in the hinge joint positioning assembly. The two fixed seats are spaced apart and clamp the hinge joint. The two positioning plates abut against the two fixed seats from the top and bottom respectively. The positioning plates, hinge joint and fixed seats are connected by pins.

[0015] The beneficial effects of this invention are as follows: This invention uses a hinge hole tooling for aircraft moving parts to assist in the installation of hinge joints used to connect aircraft moving parts and aircraft fixed parts, completing the hinge hole and assembly work of the hinge joint. The hinge joint is initially positioned using the hinge hole positioning hole of the positioning plate in the hinge joint positioning assembly in conjunction with the initial hole positioning pin. After the hinge joint is installed and fixed, the initial positioning pin is removed to release assembly stress. Based on the misalignment of the mounting hole groups on the positioning plates in each group of hinge joint positioning assemblies, the same group of mounting positioning holes is selected, and the positioning plate is fixed to the fixed seat. Finally, the hinge joint is machined according to the hinge hole positioning hole on the positioning plate, thereby effectively ensuring the coaxiality of the hinge holes on different hinge joints and effectively improving the installation accuracy of aircraft moving parts. The hinge hole tooling used in this invention is reusable and provides convenient hinge hole positioning, effectively improving the assembly efficiency of aircraft moving parts while reducing assembly costs. Attached Figure Description

[0016] Figure 1 A schematic diagram showing the installation of the hinge hole tooling for the hinge joint of the moving parts of an aircraft with the fixed parts of the aircraft.

[0017] Figure 2 This is an isometric view of the hinge hole tooling for the hinge joint of the moving parts of an aircraft used in this invention.

[0018] Figure 3 This is a top view of the aircraft moving component hinge joint hinge hole tooling used in this invention.

[0019] Figure 4 A schematic diagram of the hinge joint positioning assembly;

[0020] Figure 5 This is a schematic diagram showing the fit between the hinge connector and the positioning plate.

[0021] The markings in the diagram are as follows: 100-Aircraft fixed component, 200-Aircraft moving component, 300-Aircraft moving component hinge joint hinge hole tooling, 310-Tooling body, 320-Hinge joint positioning assembly, 321-Fixed seat, 322-Positioning piece, 323-Hinge hole positioning hole, 324-Positioning piece mounting hole, 330-Tooling positioning component, 340-Aircraft fixed component positioning component, 400-Hinge joint. Detailed Implementation

[0022] To facilitate understanding of the present invention, the invention will be further described below with reference to the accompanying drawings.

[0023] In the description of this invention, it should be noted that the terms "front", "rear", "left", "right", "up", "down", "inner", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of description, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0024] The method for drilling hinge joints of aircraft moving parts disclosed in this invention uses a tooling 300 for drilling hinge joints of aircraft moving parts to assist in positioning and installing the hinge joint 400.

[0025] Specifically, such as Figures 1 to 3 As shown, the aircraft moving component hinge joint reaming hole tooling 300 consists of a tooling body 310, a hinge joint positioning assembly 320, a tooling positioning component 330, and an aircraft fixed component positioning component 340. The structure of the tooling body 310 is not limited; it is mainly used to install and fix the hinge joint positioning assembly 320, the tooling positioning component 330, and the aircraft fixed component positioning component 340. To reduce the overall production cost of the aircraft moving component hinge joint reaming hole tooling 300, a frame structure tooling body 310 can be adopted to reduce the overall weight and manufacturing cost of the tooling body 310, while also facilitating its transportation. The hinge joint positioning assembly 320 is used to position the hinge joint 400 that enables the hinged connection between the aircraft fixed component 100 and the aircraft movable component 200. The number of hinge joint positioning assemblies 320 is set according to the number of hinge joints 400 required for the connection between the aircraft fixed component 100 and the aircraft movable component 200. For example, in this invention, there are two hinge joints 400, so two sets of hinge joint positioning assemblies 320 are used. The aircraft movable component 200 mentioned in this invention is mainly an openable and closable door structure in the aircraft components, while the aircraft fixed component 100 is a door frame structure fixed to the aircraft fuselage for installing the door structure. The tooling positioning component 330 is used to connect and fix the tooling body 310 to the assembly frame and to position the connection position between the tooling body 310 and the assembly frame. The aircraft fixed component positioning component 340 is used to connect and fix the tooling body 310 to the aircraft fixed component 100 and to position the connection position between the tooling body 310 and the aircraft fixed component 100. There is no limit to the number of tooling positioning parts 330 and aircraft fixing component positioning parts 340, which can be set according to the actual assembly situation. The specific implementation of tooling positioning parts 330 and aircraft fixing component positioning parts 340 can adopt mature positioning structures in the existing technology. For example, bolts, screws, pins or similar parts can be used to cooperate with positioning holes to achieve positioning and fixing.

[0026] Specifically, such as Figure 3 and Figure 4 As shown, the hinge joint positioning assembly 320 used in this invention consists of a fixed base 321 and a positioning piece 322. The fixed base 321 and the positioning piece 322 are detachably connected. The fixed base 321 is used to fix the hinge joint positioning assembly 320 as a whole on the tooling body 310, and the positioning piece 322 is used to position the hinge hole of the hinge joint 400. Multiple sets of positioning piece mounting holes are provided at the end of the positioning piece 322 connected to the fixed base 321. Each set of positioning piece mounting holes includes at least one positioning piece mounting hole 324. The sets of positioning piece mounting holes are evenly distributed at intervals on the positioning piece 322, and their arrangement direction is the width direction of the positioning piece 322.

[0027] Furthermore, the present invention provides at least three sets of positioning plate mounting hole groups on the positioning plate 322. Each set of positioning plate mounting hole groups includes two spaced-apart positioning plate mounting holes 324, such that the two positioning plate mounting holes 324 in the same set are spaced apart along the length direction of the positioning plate 322, and the three sets of positioning plate mounting hole groups are arranged parallel and equidistantly along the width direction of the positioning plate 322. The three sets of positioning plate mounting hole groups are respectively used for positioning along the theoretical axis and for positioning at a distance offset from the theoretical axis. In addition, as... Figure 1 , Figure 2 and Figure 5 As shown, two fixing seats 321 and two positioning pieces 322 can also be provided in the hinge joint positioning assembly 320. When fixing the hinge joint 400, the hinge joint 400 is clamped by the two spaced fixing seats 321. The two positioning pieces 322 are respectively attached to the two fixing seats 321 from the top and bottom sides. The positioning pieces 322, the hinge joint 400 and the fixing seats 321 are connected by pins.

[0028] The method for boring a hinge joint in an aircraft moving part disclosed in this invention involves the following steps when assembling and boring the hinge joint 400:

[0029] Step 1: Place the main body 310 of the aircraft movable component hinge joint hinge hole tooling 300 into the installation position of the aircraft movable component 200 within the aircraft fixed component 100, i.e., at the opening position of the aircraft movable component 200 on the aircraft fuselage. The main body 310 adopts a rectangular frame structure, and its shape is adapted to the opening shape of the installation position of the aircraft movable component 200. The main body 310 is connected and fixed to the assembly jig by the tooling positioning component 330, and the main body 310 is connected and fixed to the aircraft fixed component 100 by the aircraft fixed component positioning component 340. The tooling positioning component 330 and the aircraft fixed component positioning component 340... All components adopt a connection structure consisting of a support plate and reinforcing ribs, with connection holes provided on the support plate for connection and fixation; the number of tooling positioning parts 330 and aircraft fixed component positioning parts 340 is at least three; the hinge joint positioning assembly 320 is fixed to the tooling body 310 by a pin, which facilitates disassembly in subsequent steps. At this time, the positioning plate mounting hole group that cooperates with the pin to fix the hinge joint positioning assembly 320 is the positioning plate mounting hole group used for theoretical axis positioning; the hinge joint positioning assembly 320 is rotated with the product according to the assembly process to ensure accuracy, and is only removed before the installation of the aircraft moving parts 200.

[0030] Step 2: Align the bushing of the hinge connector 400 axially with the locating hole 323 of the locating piece 322 on the corresponding hinge connector positioning assembly 320. Leave a certain margin in the inner diameter of the bushing of the hinge connector 400. After the initial hole locating pin passes through the locating hole 323 and the bushing of the hinge connector 400, fix the hinge connector 400 to the fixing seat 321 with a pin. The hinge connector 400 can be directly fixed to the tooling body 310. In this invention, in order to simplify the structure, the connector 400 is directly fixed to the fixing seat 321 that is already fixedly connected to the tooling body 310. At this time, both ends of the hinge connector 400 are fixed. One end is connected and fixed to the locating piece 322 of the hinge connector positioning assembly 320 through the initial hole locating pin, and the other end is connected and fixed to the fixing seat 321 of the hinge connector positioning assembly 320 through a pin.

[0031] Step 3: Remove the initial hole positioning pin and the pin securing the hinge joint positioning assembly 320. This pin is used to secure the positioning piece 322 in the hinge joint positioning assembly 320. Specifically, remove the pin that mates with the positioning piece mounting hole group on the positioning piece 322, releasing the end of the positioning piece 322 with the positioning piece mounting hole group. After the assembly stress is released, if there is a difference between the initial positioning position and the theoretical axis positioning, the end of the positioning piece 322 with the positioning piece mounting hole group will deviate. Then, select the same set of mounting positioning hole groups based on the misalignment of the mounting hole groups on the positioning pieces 322 in each set of hinge joint positioning assemblies 320. Then, use the pin to mate with the selected same set of mounting positioning hole groups to re-secure the hinge joint positioning assembly 320 onto the tooling body 310. At this time, the mounting positioning hole group mates with the pin is the mounting positioning hole group that deviates from the theoretical axis. The specific set of deviated mounting positioning hole groups is selected based on the actual misalignment.

[0032] Step 4: The bushing of the hinge head 400 is reamed and made into a final hole through the reaming hole positioning hole 323 on the positioning plate 322. After the reaming is completed, the hinge head 400 is fixedly connected to the aircraft fixed component 100 through the final hole positioning pin. Then, the reaming work of other hinge heads 400 is carried out to ensure the coaxiality of the inner hole of the bushing of different hinge heads 400.

[0033] Step 5: After completing the hinge holes of all hinge joints 400, remove the hinge joints 400 from the fixed base 321, remove the tooling body 310 from the aircraft fixed part 100, and then connect and fix the aircraft moving part 200 to the hinge joints 400.

Claims

1. A method for creating a hinge hole in a hinge joint of an aircraft moving part, characterized in that: A hinge hole tooling (300) for aircraft moving parts is used to assist in the hinge hole work of the hinge joint (400) connecting the aircraft moving part (200) and the aircraft fixed part (100). The aircraft moving part hinge joint hinge hole tooling (300) includes a tooling body (310), on which at least two sets of hinge joint positioning assemblies (320) corresponding one-to-one with the hinge joints (400) and multiple tooling positioning parts are detachably fixed. 330) and multiple aircraft fixed component positioning parts (340); the hinge joint positioning assembly (320) includes a fixed base (321) and a positioning piece (322), the fixed base (321) is fixed on the tooling body (310), the positioning piece (322) is detachably connected to the fixed base (321), the positioning piece (322) is provided with a hinge hole positioning hole (323) and multiple sets of positioning piece mounting hole groups, the positioning piece mounting hole group includes at least one positioning piece mounting hole (324); The method for drilling the hinge joint of the aircraft moving part includes the following steps: Step 1: Place the main body (310) of the hinge hole tooling (300) of the aircraft moving part into the installation position of the aircraft moving part (200) in the aircraft fixed part (100). Connect and fix the main body (310) to the assembly frame through the tooling positioning component (330). Connect and fix the main body (310) to the aircraft fixed part (100) through the aircraft fixed part positioning component (340). Fix the hinge head positioning assembly (320) on the tooling main body (310) through the pin. Step 2: Align the bushing of the hinge head (400) with the axial position of the locating hole (323) of the locating piece (322) on the corresponding hinge head positioning assembly (320). After the initial hole locating pin passes through the locating hole (323) and the bushing of the hinge head (400), fix the hinge head (400) on the fixing seat (321). Step 3: Remove the initial hole positioning pin and remove the pin that fixes the hinge joint positioning assembly (320). Select the same set of mounting positioning holes according to the misalignment of the mounting hole group on the positioning piece (322) in each set of hinge joint positioning assemblies (320). Then, fix the hinge joint positioning assembly (320) on the tooling body (310) again by cooperating with the selected same set of mounting positioning holes using the pin. Step 4: The bushing of the hinge joint (400) is reamed and made into a final hole through the reaming hole positioning hole (323) on the positioning plate (322). After the reaming is completed, the hinge joint (400) is fixedly connected to the aircraft fixed component (100) through the final hole positioning pin. Step 5: After completing the hinge holes of all hinge joints (400), remove the hinge joints (400) from the fixed base (321), remove the tooling body (310) from the aircraft fixed part (100), and then connect and fix the aircraft moving part (200) to the hinge joints (400).

2. The method for drilling a hinge joint in an aircraft moving part as described in claim 1, characterized in that: At least three sets of positioning plate mounting holes are provided on the positioning plate (322). Each set of positioning plate mounting holes includes two positioning plate mounting holes (324) spaced apart, such that the two positioning plate mounting holes (324) in the same set of positioning plate mounting holes are spaced apart in the length direction of the positioning plate (322), and the three sets of positioning plate mounting holes are arranged parallel and equidistantly in the width direction of the positioning plate (322).

3. The method for drilling a hinge joint in an aircraft moving part as described in claim 2, characterized in that: Two fixing seats (321) and two positioning pieces (322) are provided in the hinge joint positioning assembly (320). The two fixing seats (321) are spaced apart and clamp the hinge joint (400). The two positioning pieces (322) are respectively attached to the two fixing seats (321) from the top and bottom. The positioning pieces (322), the hinge joint (400) and the fixing seats (321) are connected by pins.

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