Method for reaming hinge joint of aircraft movable part

Abstract

The invention discloses an aircraft movable part hinge joint reaming method, which adopts an aircraft movable part hinge joint reaming tool to assist in reaming a hinge joint connected between an aircraft movable part and an aircraft fixed part, and the aircraft movable part hinge joint reaming tool comprises a tool main body, and at least two groups of hinge joint positioning assemblies, a plurality of tool positioning pieces and a plurality of airplane fixing part positioning pieces which are in one-to-one correspondence with the hinge joints are detachably fixed on the tool main body. According to the invention, the coaxiality of reaming holes in different hinge joints is effectively ensured, and the mounting precision of movable parts of an aircraft is effectively improved; the reaming tool for the hinge joint of the aircraft movable part can be repeatedly used, reaming positioning is convenient and fast, the assembly cost of the aircraft movable part is reduced, and meanwhile the assembly efficiency of the aircraft movable part is effectively improved.

Description

Technical Field

[0001] The invention relates to the technical field of assembling aircraft movable parts, in particular to a method for boring a hinge joint of an aircraft movable part. Background Art

[0002] In the production and manufacturing of aircraft, after the assembly of the aircraft fuselage components is completed, it is necessary to assemble the boarding door, emergency door, access door and other movable parts, and install these movable parts on the fixed parts of the aircraft. In the assembly of these movable parts of the aircraft, hinges are often used for connection. However, due to the opening rigidity or deformation problems of the aircraft movable parts, the installation intersection of the aircraft movable parts will deviate. When the movable parts are connected to the fixed parts through hinges, the coaxiality of each hinged part cannot meet the high-precision requirements of the design, which in turn affects the installation quality of the aircraft movable parts.

[0003] A Chinese patent application with publication number CN113200151A discloses a high-precision fixed-force assembly method for large aircraft cabin doors, which 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 joint, and a tension and pressure sensor, the door sample base is a frame structure, and its frame shape is consistent with the door shape of the aircraft cabin door and the door frame overlap area, the door hinge joint is fixed to the outer circle of the door sample base and is consistent with the shape and position of the cabin door hinge joint, and a tension and pressure sensor is installed between the hinge joint and the door sample base; the door frame sample consists of a door frame sample base, a door frame hinge joint, and a tension and pressure sensor, the door frame sample base is a surrounding frame structure, the door frame sample base shape is consistent with the door frame shape of the aircraft cabin door and the door frame overlap area, the door frame hinge joint is fixed to the inner circle of the door frame sample base and is consistent with the shape and position of the cabin door frame hinge joint, and a tension and pressure sensor is installed between the door frame hinge joint and the door frame sample base.

[0004] The technical solution disclosed in the above patent application monitors the force value by setting a pressure sensor between the hinge joint and the door frame sample of the aircraft cabin door to adjust the shaft hole matching accuracy of the hinge joint. However, the technical solution of this patent requires the installation of a pressure sensor at each hinge joint for real-time monitoring, which will undoubtedly increase the cost of assembly work, and the installation and debugging of the pressure sensor 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 boring holes in hinge joints of aircraft movable parts, which can effectively improve the assembly accuracy of aircraft movable parts and reduce assembly costs.

[0006] In order to solve the above technical problems, the technical solution adopted by the present invention is: a method for reaming a hinge joint of an aircraft movable part, using a reaming tool for a hinge joint of an aircraft movable part to assist in reaming a hinge joint connected between the aircraft movable part and the aircraft fixed part, the aircraft movable part hinge joint reaming tool comprising a tool body, on which at least two groups of hinge joint positioning components, a plurality of tool positioning pieces and a plurality of aircraft fixed part positioning pieces are detachably fixed and correspond to the hinge joint one by one; the hinge joint positioning component comprises a fixing seat and a positioning piece, the fixing seat is fixed to the tool body, the positioning piece is detachably connected to the fixing seat, the positioning piece is provided with a reaming positioning hole and a plurality of positioning piece mounting hole groups, the positioning piece mounting hole group comprises at least one positioning piece mounting hole;

[0007] The method for reaming a hole in a hinge joint of an aircraft movable part comprises the following steps:

[0008] Step 1: Place the tool body of the aircraft movable part hinge joint reaming tool at the installation position of the aircraft movable part in the aircraft fixed part, connect and fix the tool body with the assembly jig through the tool positioning piece, connect and fix the tool body with the aircraft fixed part through the aircraft fixed part positioning piece, and fix the hinge joint positioning assembly on the tool body through the latch;

[0009] Step 2: Axially align the bushing of the hinge joint with the reaming hole of the locating plate on the corresponding hinge joint locating assembly, and after the initial hole locating pin penetrates the reaming hole and the bushing of the hinge joint, fix the hinge joint on the fixing seat;

[0010] Step 3: Remove the initial hole positioning pin and the pin that fixes the hinge joint positioning assembly, select the same group of installation positioning hole groups according to the staggered hole amount of the installation hole groups on the positioning pieces in each group of hinge joint positioning assemblies, and then re-fix the hinge joint positioning assembly on the tooling body by matching the pin with the selected same group of installation positioning hole groups;

[0011] Step 4: Ream the bushing of the hinge joint through the reaming positioning hole on the positioning sheet to form a final hole, and after the reaming is completed, fix the hinge joint to the aircraft fixed component;

[0012] Step 5. After completing the reaming of all hinge joints, remove the hinge joints from the fixing seats and remove the tooling body from the aircraft fixing parts.

[0013] As an improvement of the above scheme: at least three groups of positioning piece mounting hole groups are arranged on the positioning piece, each group of positioning piece mounting hole groups includes two spacing positioning piece mounting holes, so that the two positioning piece mounting holes in the same group of positioning piece mounting hole groups are spacing in the length direction of the positioning piece, and the three groups of positioning piece mounting hole groups are arranged in parallel and equidistantly in the width direction of the positioning piece.

[0014] As an improvement of the above scheme: two fixing seats and two positioning plates are set in the hinge joint positioning assembly, the two fixing seats are set at intervals and clamp the hinge joint, the two positioning plates are respectively abutted against the two fixing seats from the upper and lower sides, and the positioning plates, the hinge joint and the fixing seats are connected by pins.

[0015] The beneficial effects of the present invention are as follows: the present invention uses an aircraft movable part hinge joint reaming tool to assist in the installation of a hinge joint used to connect an aircraft movable part and an aircraft fixed part, completes the reaming and assembly work of the hinge joint, uses the reaming locating hole of the locating plate in the hinge joint positioning assembly to cooperate with the initial hole locating pin to perform preliminary positioning of the hinge joint, then removes the preliminary locating pin after the hinge joint is installed and fixed to release the assembly stress, selects the same group of installation locating hole groups according to the staggered hole amount of the installation hole groups on the locating plates in each group of hinge joint positioning assemblies, fixes the locating plate on the fixing seat, and finally performs reaming processing on the hinge joint according to the reaming locating holes on the locating plate, thereby effectively ensuring the coaxiality of the reaming holes on different hinge joints and effectively improving the installation accuracy of the aircraft movable parts; the aircraft movable part hinge joint reaming tool used in the present invention is reusable and convenient for reaming hole positioning, effectively improving the assembly efficiency of the aircraft movable parts while reducing the assembly cost of the aircraft movable parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the reaming tool for the hinge joint of the aircraft movable part after being installed with the aircraft fixed part;

[0017] Figure 2 It is a structural axonometric diagram of the hinge joint reaming tooling for the aircraft movable part used in the present invention;

[0018] Figure 3 It is a top view of the structure of the hinge joint reaming tool for the aircraft movable part used in the present invention;

[0019] Figure 4 It is a structural schematic diagram of the hinge joint positioning assembly;

[0020] Figure 5 It is a schematic diagram of the cooperation between the hinge joint and the positioning piece.

[0021] Marked in the figure: 100-aircraft fixed parts, 200-aircraft movable parts, 300-aircraft movable parts hinge joint reaming tool, 310-tool body, 320-hinge joint positioning assembly, 321-fixed seat, 322-positioning plate, 323-reaming positioning hole, 324-positioning plate mounting hole, 330-tool positioning piece, 340-aircraft fixed part positioning piece, 400-hinge joint. DETAILED DESCRIPTION

[0022] In order to facilitate the understanding of the present invention, the present invention is further described below in conjunction with the accompanying drawings.

[0023] In the description of the present invention, it should be noted that the directions or positional relationships indicated by terms such as “front”, “rear”, “left”, “right”, “up”, “down”, and “inside” are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of description. They do not indicate or imply that the device or component referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limitations on the present invention.

[0024] The method for reaming a hole in a hinge joint of an aircraft movable part disclosed in the present invention adopts a reaming tool 300 for reaming a hole in a hinge joint of an aircraft movable part to assist in positioning and installing a hinge joint 400.

[0025] Specifically, Figures 1 to 3 As shown, the aircraft movable part hinge joint reaming tool 300 is composed of a tool body 310, a hinge joint positioning assembly 320, a tool positioning piece 330 and an aircraft fixed part positioning piece 340. The structure of the tool body 310 is not limited, and it is mainly used to install and fix the hinge joint positioning assembly 320, the tool positioning piece 330 and the aircraft fixed part positioning piece 340. In order to reduce the production cost of the entire aircraft movable part hinge joint reaming tool 300, a frame structure tool body 310 can be used to reduce the overall weight and preparation cost of the tool body 310, and it is also convenient to transport the tool body 310. The hinge joint positioning assembly 320 is used to position the hinge joint 400 that realizes 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, if the number of hinge joints 400 in the present invention is two, two sets of hinge joint positioning assemblies 320 are used accordingly; the aircraft movable component 200 described in the present invention is mainly an openable and closable door structure in the aircraft component, and the aircraft fixed component 100 is a door frame structure fixed on the aircraft fuselage for installing the door structure. The tool positioning member 330 is used to connect and fix the tool main body 310 with the assembly jig, and to position the connection position of the tool main body 310 and the assembly jig; the aircraft fixed component positioning member 340 is used to connect and fix the tool main body 310 with the aircraft fixed component 100, and to position the connection position of the tool main body 310 and the aircraft fixed component 100. There is no limit to the number of tooling locating parts 330 and aircraft fixed component locating parts 340, which can be set according to actual assembly conditions. The specific implementation schemes of tooling locating parts 330 and aircraft fixed component locating parts 340 can adopt mature positioning structures in the prior art, for example, bolts, screws, pins or similar parts can be used in conjunction with positioning holes to achieve positioning and fixation.

[0026] Specifically, Figure 3 and Figure 4 As shown, the hinge joint positioning assembly 320 used in the present invention is composed of a fixing seat 321 and a positioning piece 322; the fixing seat 321 and the positioning piece 322 are detachably connected, the fixing seat 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 locate the reaming position of the hinge joint 400. A plurality of positioning piece mounting hole groups are provided at one end where the positioning piece 322 is connected to the fixing seat 321, each positioning piece mounting hole group includes at least one positioning piece mounting hole 324, and each positioning piece mounting hole group is evenly spaced on the positioning piece 322, and the arrangement direction thereof is the width direction of the positioning piece 322.

[0027] Furthermore, the present invention sets at least three groups of positioning piece mounting hole groups on the positioning piece 322, and each group of positioning piece mounting hole groups includes two positioning piece mounting holes 324 arranged at intervals, so that the two positioning piece mounting holes 324 in the same group of positioning piece mounting hole groups are arranged at intervals in the length direction of the positioning piece 322, and the three groups of positioning piece mounting hole groups are arranged in parallel and equidistantly in the width direction of the positioning piece 322. The three groups of positioning piece mounting hole groups are respectively used for theoretical axis positioning and for positioning at an equidistant distance outside the theoretical axis. In addition, if Figure 1 , Figure 2 and Figure 5 As shown, two fixing seats 321 and two positioning plates 322 can also be set in the hinge joint positioning assembly 320. When fixing the hinge joint 400, the hinge joint 400 is clamped by the two fixing seats 321 arranged at intervals, and the two positioning plates 322 are respectively abutted against the two fixing seats 321 from the upper and lower sides, and the positioning plates 322, the hinge joint 400 and the fixing seats 321 are connected by pins.

[0028] The method for reaming a hole in a hinge joint of an aircraft movable part disclosed in the present invention is performed according to the following steps when assembling and reaming a hole in a hinge joint 400:

[0029] Step 1: Place the tool body 310 of the aircraft movable component hinge joint reaming tool 300 at the installation position of the aircraft movable component 200 in the aircraft fixed component 100, that is, at the opening position of the aircraft movable component 200 on the aircraft fuselage. The tool 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; connect and fix the tool body 310 to the assembly jig through the tool positioning piece 330, connect and fix the tool body 310 to the aircraft fixed component 100 through the aircraft fixed component positioning piece 340, and the tool positioning piece 330 and the aircraft fixed component positioning piece 340 are connected and fixed. 0 both adopt a connection structure composed of a support plate and a reinforcing rib, and a connection hole is set on the support plate for connection and fixation; the number of tooling locating pieces 330 and aircraft fixed component locating pieces 340 is at least three; the hinge joint positioning assembly 320 is fixed to the tooling body 310 by a latch, which is convenient for disassembly in subsequent steps. At this time, the positioning piece mounting hole group that cooperates with the latch to fix the hinge joint positioning assembly 320 is the positioning piece mounting hole group for theoretical axis positioning; the hinge joint positioning assembly 320 is circulated with the product according to the assembly process to ensure accuracy, and it is not removed until the aircraft movable component 200 is installed.

[0030] Step 2, axially align the bushing of the hinge joint 400 with the reaming positioning hole 323 of the positioning plate 322 on the corresponding hinge joint positioning assembly 320, reserve a certain margin for the inner diameter of the bushing of the hinge joint 400, use the initial hole positioning pin to penetrate the reaming positioning hole 323 and the bushing of the hinge joint 400, and then fix the hinge joint 400 on the fixing seat 321 by the same pin. The hinge joint 400 can be directly fixed on the tooling body 310. In order to simplify the structure in the present invention, the connecting joint 400 is directly fixed on the fixing seat 321 that has been fixedly connected to the tooling body 310; at this time, both ends of the hinge joint 400 are fixed, one end is connected and fixed to the positioning plate 322 of the hinge joint positioning assembly 320 by the initial hole positioning pin, and the other end is connected and fixed to the fixing seat 321 of the hinge joint positioning assembly 320 by the pin.

[0031] The third step is to remove the initial hole positioning pin and the plug for fixing the hinge joint positioning assembly 320. The plug here is the pin for fixing the positioning piece 322 in the hinge joint positioning assembly 320, that is, to remove the plug that matches the positioning piece mounting hole group on the positioning piece 322, so that one end of the positioning piece mounting hole group set in the positioning piece 322 is released. 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 mounting hole group set in the positioning piece 322 will deviate; then, according to the amount of misalignment of the mounting hole group on the positioning piece 322 in each group of hinge joint positioning assemblies 320, the same group of mounting positioning hole groups is selected, and then the hinge joint positioning assembly 320 is re-fixed on the tooling body 310 through the pin and the same group of selected mounting positioning hole groups. At this time, the mounting positioning hole group matched with the plug is the mounting positioning hole group that deviates from the theoretical axis. The specific selection of which group of deviated mounting positioning hole groups is based on the actual amount of misalignment.

[0032] Step 4: The bushing of the hinge joint 400 is reamed through the ream positioning hole 323 on the positioning plate 322 to form a final hole. After the ream is completed, the hinge joint 400 is fixedly connected to the aircraft fixed component 100 through the final hole positioning pin, and then other hinge joints 400 are reamed to ensure the coaxiality of the inner holes of the bushings of different hinge joints 400.

[0033] Step 5: After all the hinge joints 400 are reamed, the hinge joints 400 are removed from the fixing base 321 , the tooling body 310 is removed from the aircraft fixed component 100 , and then the aircraft movable component 200 is connected and fixed to the hinge joint 400 .

Claims

1. A method for reaming holes in hinge joints of aircraft movable parts, characterized in that: An aircraft movable part hinge joint reaming tool (300) is used to assist in reaming a hinge joint (400) connected between an aircraft movable part (200) and an aircraft fixed part (100). The aircraft movable part hinge joint reaming tool (300) comprises a tool body (310) on which at least two groups of hinge joint positioning components (320) corresponding to the hinge joints (400) are detachably fixed, and a plurality of tool positioning members ( 330) and a plurality of aircraft fixed component positioning members (340); the hinge joint positioning assembly (320) comprises a fixing seat (321) and a positioning piece (322), the fixing seat (321) is fixed on the tooling body (310), the positioning piece (322) is detachably connected to the fixing seat (321), the positioning piece (322) is provided with a reaming positioning hole (323) and a plurality of positioning piece mounting hole groups, the positioning piece mounting hole group comprising at least one positioning piece mounting hole (324); The method for reaming a hole in a hinge joint of an aircraft movable part comprises the following steps: Step 1: placing a tool body (310) of a hinge joint reaming tool (300) for an aircraft movable part at an installation position of the aircraft movable part (200) in an aircraft fixed part (100), connecting and fixing the tool body (310) to an assembly jig through a tool positioning piece (330), connecting and fixing the tool body (310) to an aircraft fixed part (100) through an aircraft fixed part positioning piece (340), and fixing a hinge joint positioning assembly (320) to the tool body (310) through a latch; Step 2: Axially align the bushing of the hinge joint (400) with the reaming positioning hole (323) of the positioning sheet (322) on the corresponding hinge joint positioning assembly (320), and after the initial hole positioning pin is passed through the reaming positioning hole (323) and the bushing of the hinge joint (400), the hinge joint (400) is fixed 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 group of installation positioning hole groups according to the amount of staggered holes of the installation hole groups on the positioning pieces (322) in each group of hinge joint positioning assemblies (320), and then re-fix the hinge joint positioning assembly (320) on the tooling body (310) by matching the pin with the selected same group of installation positioning hole groups; Step 4: The bushing of the hinge joint (400) is reamed through the reaming positioning hole (323) on the positioning plate (322) to form a final hole. After the reaming is completed, the hinge joint (400) is fixedly connected to the aircraft fixing component (100) through the final hole positioning pin; Step 5: After all the hinge joints (400) are reamed, the hinge joints (400) are removed from the fixing seat (321), the tooling body (310) is removed from the aircraft fixed component (100), and then the aircraft movable component (200) is connected and fixed to the hinge joint (400).

2. The method for boring a hole in a hinge joint of an aircraft movable part according to claim 1, characterized in that: At least three groups of positioning piece mounting hole groups are arranged on the positioning piece (322), each group of positioning piece mounting hole groups includes two positioning piece mounting holes (324) arranged at intervals, so that the two positioning piece mounting holes (324) in the same group of positioning piece mounting hole groups are arranged at intervals in the length direction of the positioning piece (322), and the three groups of positioning piece mounting hole groups are arranged in parallel and equidistantly in the width direction of the positioning piece (322).

3. The method for boring a hole in a hinge joint of an aircraft movable part according to claim 2, characterized in that: Two fixing seats (321) and two positioning pieces (322) are arranged in the hinge joint positioning assembly (320); the two fixing seats (321) are arranged at intervals and clamp the hinge joint (400); the two positioning pieces (322) are respectively abutted against the two fixing seats (321) from upper and lower sides; the positioning pieces (322), the hinge joint (400) and the fixing seats (321) are connected by means of a latch.

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