Aircraft cabin door interchangeability detection tool and detection method

Abstract

The invention discloses an aircraft cabin door interchangeability detection tool and detection method, and relates to the technical field of aircraft assembly. The aircraft cabin door interchangeability detection tool comprises a tool frame, and a cabin door appearance comparison assembly and a hinge arm matching mechanism are fixedly arranged on the tool frame; the cabin door appearance comparison assembly is of a frame-shaped structure matched with the outer contour edge of an aircraft cabin door, and the hinge arm matching mechanism is used for being connected with a hinge arm on the aircraft cabin door in a matched mode. The groove-shaped connecting rail position detection block is fixed to the tool frame and located behind the cabin door appearance comparison assembly, and the retainer detection identification point positions are fixed to the back face of the cabin door appearance comparison assembly. According to the invention, analysis and evaluation of the attitude of the aircraft cabin door can be rapidly completed, the aircraft cabin door can be directly debugged based on the tool, and the interchangeability of the aircraft cabin door can be efficiently detected while the interchangeability detection accuracy and repeatability are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of testing or inspection of aircraft components, and in particular to an aircraft door interchangeability detection tooling and an aircraft door interchangeability detection method. Background Art

[0002] Aircraft manufacturing is a complex systems engineering. The assembly accuracy of the final product determines whether the aircraft can meet the design requirements. Therefore, the measurement and inspection work during and after the aircraft assembly process is particularly important. The aircraft door is an important part of the aircraft structure. As a movable component, the aircraft door has more stringent requirements for assembly production.

[0003] Interchangeability detection is an important detection link in aircraft production. When performing interchangeability detection, usually a component of one aircraft is selected as the reference part for interchange detection, and then the corresponding assembled component of another aircraft is taken as the interchange part for interchange detection. If both meet the detection technical conditions, it is determined that the component has interchangeability; interchangeability detection can ensure the accuracy and stability of aircraft component assembly. In the existing aircraft door interchangeability detection, all components for interchangeability inspection and the nose component need to be completed and inspected qualified before performing the interchange inspection. However, due to differences in production rhythms, the completion and matching status of each component are inconsistent, resulting in a large number of assembly work stagnations waiting; and due to the large uncertainty in the coordination and cooperation between the aircraft door component and the nose component, there are many interchangeability detection features, resulting in a cumbersome interchangeability detection process, a large amount of adjustment work, and a long time-consuming; in addition, since the interchangeability detection work is directly carried out on the aircraft using the product, there is a risk of damaging the product during the debugging process due to a large initial adjustment stroke.

[0004] The patent application document of the invention patent with the publication number of CN117163315A discloses a method and tooling for realizing interchangeability in the assembly of double-allowance parts. Its technical solution can solve the problem of realizing the interchangeability function in the assembly of double-allowance parts, and the states of the cylindrical skin and the detachable cover that should be affected by the part processing accuracy and product positioning accuracy are fixed by the tooling so that the cylindrical skin is fixed at the theoretical position, the appearance of the detachable cover is kept consistent, and the theoretical hole positions are made on the detachable cover. Through this method, the positions, shapes, and hole positions of the above two parts can be kept consistent on each product, realizing the interchangeability function of the detachable cover. The technical solution of this patent application is mainly used for the interchange assembly between the detachable cover and the cylindrical skin, and cannot be used for the interchangeability detection of aircraft doors. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide an aircraft door interchangeability detection tooling that can effectively improve the interchangeability detection efficiency.

[0006] The technical solution adopted by the present invention to solve the above technical problems is as follows: An aircraft door interchangeability detection tooling, including a tooling frame, on which a door outer shape comparison component and a hinge arm matching mechanism are fixedly arranged; the door outer shape comparison component is a frame structure adapted to the outer contour edge of the aircraft door, and the hinge arm matching mechanism is used for mating connection with the hinge arm on the aircraft door; it also includes a groove-shaped track position detection block fixed on the tooling frame and located behind the door outer shape comparison component, and a plurality of stop piece detection marking points fixed on the back of the door outer shape comparison component.

[0007] As an improvement of the above solution: The door outer shape comparison component is composed of a front door side outer shape comparison template, a rear door side outer shape comparison template, an upper door outer shape comparison template, and a lower door outer shape comparison template; the front door side outer shape comparison template and the rear door side outer shape comparison template are respectively located on both sides of the tooling frame, and the upper door outer shape comparison template and the lower door outer shape comparison template are respectively located on the upper and lower parts of the tooling frame.

[0008] As an improvement of the above solution: The hinge arm matching mechanism is composed of a hinge arm upper matching component and a hinge arm lower matching component arranged at intervals in the vertical direction; the hinge arm upper matching component includes an upper connecting rod and an upper matching bearing, one end of the upper connecting rod is fixedly connected to the tooling frame, and the upper matching bearing is fixed at the other end of the upper connecting rod; the hinge arm lower matching component includes a lower connecting rod and a lower matching bearing, one end of the lower connecting rod is fixedly connected to the tooling frame, and the lower matching bearing is fixed at the other end of the lower connecting rod; the upper matching bearing and the lower matching bearing are coaxially arranged.

[0009] As an improvement of the above solution: The hinge arm matching mechanism is arranged on one side of the tooling frame where the front door side outer shape comparison template is installed, and part of the front door side outer shape comparison template is fixedly connected to the tooling frame through a support; the rear door side outer shape comparison template is integrally fixedly connected to the tooling frame.

[0010] As an improvement of the above solution: The groove-shaped track position detection block is composed of a support rod and a guide wheel; one end of the support rod is fixedly connected to one side of the tooling frame where the front door side outer shape comparison template is installed, the other end of the support rod horizontally extends from the rear of the front door side outer shape comparison template to the inside of the frame structure of the door outer shape comparison component, and the guide wheel is installed at the end of the support rod that is not connected to the tooling frame.

[0011] As an improvement of the above solution: It also includes a tooling base fixedly connected to the bottom of the tooling frame.

[0012] The present invention also discloses an aircraft door interchangeability detection method, which uses the aircraft door interchangeability detection tooling as described above and is carried out according to the following steps: Step 1: Install the aircraft door on the door profile comparison component of the aircraft door interchangeability detection tooling, and make the outer contour edge of the aircraft door abut against the door profile comparison component; Step 2: Cooperatively connect the hinge arm on the aircraft door with the hinge arm mating mechanism, and check and evaluate the attitude performance of the aircraft door on the aircraft door interchangeability detection tooling when the aircraft door is in the open state; Step 3: Confirm the position of the grooved rail joint on the aircraft door, and judge whether the position of the grooved rail joint can correspond to the position of the grooved rail joint position detection block. If it is judged that there is a deviation in the position of the grooved rail joint, debug the movable components on the aircraft door to make the grooved rail joint position detection block able to connect with the grooved rail joint; Step 4: Use a general measuring tool to measure the step difference and clearance value between the door profile comparison component and the aircraft door, and debug the movable components on the aircraft door to make the clearance value not less than 2 mm, and use the door profile comparison component as auto-collimation, with the step difference within the following required ranges: the front side required range is 0 - 9 mm, the rear side required range is 0 - 6 mm, the upper part required range is 0 - 12 mm, and the lower part required range is 0 - 9 mm; Step 5: Compare and check the installed stop on the aircraft door with the stop detection marking point on the door profile comparison component, and use a general measuring tool to measure the distance dimension between the stop and the door profile comparison component, and debug the movable components on the aircraft door to make the distance between the stop and the door profile comparison component not less than 10 mm; Step 6: Rotate the aircraft door and check whether the mating position of the hinge arm on the aircraft door and the hinge arm mating mechanism rotates flexibly; Step 7: Summarize the relative relationship between the debugged aircraft door and the aircraft door interchangeability detection tooling to form the result of the detection record report. Finally, install the aircraft door and the aircraft nose reference part, and perform directional fine-tuning according to the result of the detection record report to complete the interchangeability detection work.

[0013] The beneficial effects of the present invention are as follows: By using the interchangeability detection tooling for aircraft cabin doors to replace the reference parts required in the interchangeability detection of aircraft cabin doors, it is not necessary to use the corresponding parts on the aircraft as reference parts. Therefore, the interchangeability detection of aircraft cabin doors can be carried out before the corresponding parts are completed, directly saving the waiting time before the reference parts are completed, and thus effectively improving the efficiency of the interchangeability detection of aircraft cabin doors; The tooling disclosed in the present invention is convenient for installing aircraft cabin doors. It only needs to use the hinge arm matching mechanism on the tooling to cooperate and connect with the hinge arm of the aircraft cabin door, and while limiting the aircraft through the cabin door contour comparison component, the contour of the aircraft cabin door is compared and detected. It can quickly complete the analysis and evaluation of the attitude of the aircraft cabin door, directly judge the fine-tuning direction and position of the aircraft cabin door, and can directly debug the aircraft cabin door based on the tooling to ensure that it is qualified in one-time debugging later. While improving the accuracy and repeatability of the interchangeability detection, the efficient detection of the interchangeability of aircraft cabin doors is realized; At the same time, since the present invention does not directly carry out the interchangeability detection on the aircraft components, it effectively avoids the risk of damage to the aircraft components caused by the debugging work. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 is an axonometric view of the interchangeability detection tooling for aircraft cabin doors; Figure 2 is a front view of the interchangeability detection tooling for aircraft cabin doors; Figure 3 is a side view of the interchangeability detection tooling for aircraft cabin doors; Figure 4 is a top view of the interchangeability detection tooling for aircraft cabin doors.

[0015] The markings in the figure are: 100 - tooling frame, 200 - cabin door contour comparison component, 210 - front side contour comparison template of the door, 220 - rear side contour comparison template of the door, 230 - upper part contour comparison template of the door, 240 - lower part contour comparison template of the door, 300 - hinge arm matching mechanism, 310 - upper part matching component of the hinge arm, 320 - lower part matching component of the hinge arm, 400 - tooling base. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0016] For the convenience of understanding the present invention, the present invention will be further described below with reference to the accompanying drawings.

[0017] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "front", "rear", "left", "right", "upper", "lower", "inner", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of description, rather than indicating or implying that the device or component referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0018] AsFigures 1 to 4 As shown in the figure, the aircraft door interchangeability detection tooling disclosed by the present invention includes a tooling frame 100, a door profile comparison assembly 200, and a hinge arm matching mechanism 300; the tooling frame 100 serves as the basic structure of the entire aircraft door interchangeability detection tooling, and both the door profile comparison assembly 200 and the hinge arm matching mechanism 300 are installed on the tooling frame 100; the door profile comparison assembly 200 is used to perform a comparison detection on the profile of the aircraft door to be detected; the hinge arm matching mechanism 300 is used to be cooperatively connected with the hinge arm on the aircraft door, and the entire aircraft door is fixed on the tooling frame 100 by fixing the hinge arm on the aircraft door through the hinge arm matching mechanism 300, and the working condition of the hinge arm can be detected while the aircraft door is being fixed, so as to detect the rotation state of the aircraft door. In addition, for the aircraft door interchangeability detection work in the present invention, a channel rail position detection block and a stop part detection marking point are also provided. The channel rail position detection block is used to detect the position of the channel rail on the aircraft door, and the stop part detection marking point is used to detect the position of the stop part on the aircraft door; since the channel rail on the aircraft door is located on the back of the aircraft door, the channel rail position detection block is arranged behind the door profile comparison assembly 200; since there are multiple stop parts on the aircraft door, the same number of stop part detection marking points as the stop parts are set, and the stop part detection marking points are arranged on the back of the door profile comparison assembly 200 in a one-to-one correspondence with the stop parts. The stop part detection marking points correspond to the stop parts on the back of the aircraft door from the side of the aircraft door. If the stop part detection marking point can be aligned with the corresponding stop part, it indicates that the position of the stop part is accurate, and adjustment is made if there is a deviation. The present invention can replace the reference part in the aircraft door interchangeability detection with the aircraft door interchangeability detection tooling, cooperate with the aircraft door to be detected, complete the preliminary analysis and evaluation of the aircraft door attitude, and adjust the attitude of the aircraft door to the best position that matches the reference part in the theoretical state. After the interchangeability detection is completed, the aircraft door is cooperatively installed with the actually selected reference part, and appropriate fine-tuning can complete the accurate assembly work.

[0019] Specifically, as Figures 1 to 4As shown, the specific structure of the tooling frame 100 in the present invention is not limited. It is mainly used to fix the hatch door contour comparison assembly 200 and the hinge arm matching mechanism 300. The tooling frame 100 can adopt a frame structure assembled by welding pipes. On the premise of ensuring stability, the use of pipes is minimized to reduce costs, and a space for the rotation of the aircraft hatch door needs to be left in the middle part. Further, in order to improve the stability of the entire aircraft hatch door interchangeability detection tooling, a tooling base 400 can also be added to the bottom of the tooling frame 100. The tooling base 400 can also adopt a frame structure assembled by welding pipes. The horizontal projection area of the tooling base 400 should be larger than the horizontal projection area of the tooling frame 100. The contact area between the entire aircraft hatch door interchangeability detection tooling and the ground is increased through the tooling base 400, and the tooling base 400 provides a stable support foundation for the entire aircraft hatch door interchangeability detection. The materials of the tooling frame 100 and the tooling base 400 are selected as die steel and are surface-treated by quenching and passivation.

[0020] As Figures 1 to 4 shown, the hatch door contour comparison assembly 200 adopted in the present invention is composed of multiple comparison templates, and each comparison template corresponds to different parts of the aircraft hatch door respectively. Specifically, the hatch door contour comparison assembly 200 is composed of a front side contour comparison template 210, a rear side contour comparison template 220, an upper part contour comparison template 230, and a lower part contour comparison template 240. Taking the front view of the aircraft hatch door interchangeability detection tooling as shown Figure 2 as a reference benchmark, the front side contour comparison template 210 is located on the left side of the tooling frame 100, the rear side contour comparison template 220 is located on the right side of the tooling frame 100, the upper part contour comparison template 230 is located on the upper part of the tooling frame 100, and the lower part contour comparison template 240 is located on the lower part of the tooling frame 100. The front side contour comparison template 210 is adapted to the left side edge of the aircraft hatch door, the rear side contour comparison template 220 is adapted to the right side edge of the aircraft hatch door, the upper part contour comparison template 230 is adapted to the top edge of the aircraft hatch door, and the lower part contour comparison template 240 is adapted to the bottom edge of the aircraft hatch door. Each template in the hatch door contour comparison assembly 200 is made of die steel material and is surface-treated by quenching and passivation. The entire hatch door contour comparison assembly 200 is fixed on the tooling frame 100. The overall shape of the hatch door contour comparison assembly 200 is a frame structure. The inner contour shape of the hatch door contour comparison assembly 200 is adapted to the outer contour shape of the aircraft hatch door. When performing detection, the hatch door contour comparison assembly 200 surrounds the aircraft hatch door from the outside. By observing and measuring the clearance fit state, deviation or offset state between the inner frame of the hatch door contour comparison assembly 200 and the outer contour of the aircraft hatch door, the overall attitude of the aircraft hatch door is analyzed and evaluated, the contour state of the aircraft hatch door is confirmed, and the orientation and displacement amount to be adjusted are measured.

[0021] Specifically, as Figures 1 to 4 shown, the hinge arm mating mechanism 300 adopted in the present invention is composed of an upper hinge arm mating component 310 and a lower hinge arm mating component 320; the upper hinge arm mating component 310 is used to form a mating connection with the upper part of the upper hinge arm of the aircraft cabin door, and the lower hinge arm mating component 320 is used to form a mating connection with the lower part of the upper hinge arm of the aircraft cabin door. The entire aircraft cabin door is fixed on the tooling frame 100 through the mating connection between the hinge arm mating mechanism 300 and the upper hinge arm of the aircraft cabin door. The upper hinge arm mating component 310 includes an upper connecting rod and an upper mating bearing. One end of the upper connecting rod is fixedly connected to the tooling frame 100, and the upper mating bearing is fixed to the other end of the upper connecting rod; the lower hinge arm mating component 320 includes a lower connecting rod and a lower mating bearing. One end of the lower connecting rod is fixedly connected to the tooling frame 100, and the lower mating bearing is fixed to the other end of the lower connecting rod; the upper mating bearing and the lower mating bearing are coaxially arranged. Through the upper hinge arm mating component 310 and the lower hinge arm mating component 320 in the hinge arm mating mechanism 300, a rotatable mating connection relationship is respectively formed with the upper and lower parts of the upper hinge arm of the aircraft cabin door. While fixing the aircraft cabin door on the tooling frame 100, the rotation of the aircraft cabin door can be realized, and further, the rotation state of the aircraft cabin door can be detected to detect the flexibility of the rotation of the aircraft cabin door.

[0022] Furthermore, as Figures 1 to 4 shown, considering the corresponding state of the door profile comparison component 200 and the aircraft cabin door and the rotation state of the aircraft cabin door on the tooling frame 100, in the present invention, the hinge arm mating mechanism 300 is arranged on one side of the front door profile comparison template 210 installed on the tooling frame 100. Through at least two support members, part of the front door profile comparison template 210 is fixedly connected to the tooling frame 100, that is, the connection relationship between the front door profile comparison template 210 and the tooling frame 100 is a non-integral connection, and there is a gap space between the front door profile comparison template 210 and the tooling frame 100; at the same time, the rear door profile comparison template 220 is integrally fixedly connected to the tooling frame 100, that is, the connection between the rear door profile comparison template 220 and the tooling frame 100 is complete, and there is no gap space between the two; the rear door profile comparison template 220 and the tooling frame 100 are connected and fixed through support member mating bolts and are stably positioned through positioning pins. Through the above structural limitations, sufficient space can be left for the side of the aircraft cabin door where the hinge arm is installed when the aircraft cabin door rotates, without affecting the cooperation between the hinge arm mating mechanism 300 and the hinge arm, and the integral fixed connection of the rear door profile comparison template 220 to the tooling frame 100 can improve the fixing strength of the entire door profile comparison component 200 on the tooling frame 100.

[0023] In the present invention, a grooved joint position detection block is used to detect the position of the grooved joint on the aircraft cabin door. The grooved joint position detection block consists of a support rod and a guide wheel. One end of the support rod is fixedly connected to one side of the front door side contour comparison template 210 installed on the tooling frame 100. The other end of the support rod horizontally extends from the rear of the front door side contour comparison template 210 to the inside of the frame structure of the cabin door contour comparison assembly 200, and the guide wheel is installed at the end of the support rod that is not connected to the tooling frame 100. When detecting the position of the grooved joint on the aircraft cabin door, observe whether the position of the guide wheel on the grooved joint position detection block can fit with the position of the grooved joint on the aircraft cabin door. Both the support rod and the guide wheel of the grooved joint position detection block are made of die steel material, and the surface is quenched and passivated.

[0024] The design of the interchangeability detection tooling for aircraft cabin doors first establishes a derivative data model related to the characteristics of the aircraft cabin door through CATIA software, extracts the characteristics involved in the interchangeability detection of the aircraft cabin door, determines the measurement point layout plan for the interchangeability detection, obtains the tooling mold as a substitute for the reference part in the interchangeability detection of the aircraft cabin door, and finally manufactures the interchangeability detection tooling for the aircraft cabin door according to the mold.

[0025] The present invention also discloses an aircraft cabin door interchangeability detection method implemented by using the above-mentioned aircraft cabin door interchangeability detection tooling. When performing the interchangeability detection on the aircraft cabin door, the following steps are carried out: Step 1: Install the aircraft cabin door on the cabin door contour comparison assembly 200 of the aircraft cabin door interchangeability detection tooling, and make the outer contour edge of the aircraft cabin door abut against the cabin door contour comparison assembly 200. Step 2: Cooperatively connect the hinge arm on the aircraft cabin door with the hinge arm cooperation mechanism 300, and check and evaluate the attitude performance of the aircraft cabin door on the aircraft cabin door interchangeability detection tooling when the aircraft cabin door is in the open state. Step 3: Confirm the position of the grooved joint on the aircraft cabin door, and judge whether the position of the grooved joint can correspond to the position of the grooved joint position detection block. If it is judged that there is a deviation in the position of the grooved joint, then adjust the movable parts on the aircraft cabin door to make the grooved joint position detection block able to connect with the grooved joint. Step 4: Use a general measuring tool to measure the step difference and clearance value between the cabin door contour comparison assembly 200 and the aircraft cabin door, and adjust the movable parts on the aircraft cabin door to make the clearance value not less than 2 mm, and use the cabin door contour comparison assembly 200 as an autocollimator, with the step difference within the following required ranges: the front side required range is 0 - 9 mm, the rear side required range is 0 - 6 mm, the upper part required range is 0 - 12 mm, and the lower part required range is 0 - 9 mm. Step 5: Compare the installed stop on the aircraft cabin door with the stop detection marking points on the cabin door profile comparison assembly 200, and use general measuring tools to measure the distance between the stop and the cabin door profile comparison assembly 200. Adjust the moving parts on the aircraft cabin door so that the distance between the stop and the cabin door profile comparison assembly 200 is not less than 10 mm; Step 6: Rotate the aircraft cabin door and check whether the mating position of the hinge arms on the aircraft cabin door with the hinge arm mating mechanism 300 rotates flexibly; Step 7: Summarize the relative relationship between the adjusted aircraft cabin door and the aircraft cabin door interchangeability detection tooling to form the result of the detection record report. Finally, install the aircraft cabin door and the aircraft nose reference part, and perform directional fine-tuning according to the result of the detection record report to complete the interchangeability detection work.

Claims

1. Aircraft door interchangeability detection tooling, characterized by: It includes a tooling frame (100), on which a cabin door contour comparison component (200) and a hinge arm mating mechanism (300) are fixedly arranged; the cabin door contour comparison component (200) is a frame-shaped structure adapted to the outer contour edge of the aircraft cabin door, and the hinge arm mating mechanism (300) is used to mate and connect with the hinge arm on the aircraft cabin door; it also includes a grooved rail position detection block fixed on the tooling frame (100) and located behind the cabin door contour comparison component (200), and a plurality of stop piece detection marking points fixed on the back of the cabin door contour comparison component (200).

2. The aircraft door interchangeability detection tooling according to claim 1, characterized in that: The cabin door contour comparison component (200) is composed of a front side contour comparison template (210), a rear side contour comparison template (220), an upper part contour comparison template (230) and a lower part contour comparison template (240); the front side contour comparison template (210) and the rear side contour comparison template (220) are respectively located on both sides of the tooling frame (100), and the upper part contour comparison template (230) and the lower part contour comparison template (240) are respectively located on the upper and lower parts of the tooling frame (100).

3. The aircraft door interchangeability detection tooling according to claim 2, characterized in that: The hinge arm mating mechanism (300) is composed of an upper hinge arm mating component (310) and a lower hinge arm mating component (320) spaced apart in the vertical direction; the upper hinge arm mating component (310) includes an upper connecting rod and an upper mating bearing, one end of the upper connecting rod is fixedly connected to the tooling frame (100), and the upper mating bearing is fixed to the other end of the upper connecting rod; the lower hinge arm mating component (320) includes a lower connecting rod and a lower mating bearing, one end of the lower connecting rod is fixedly connected to the tooling frame (100), and the lower mating bearing is fixed to the other end of the lower connecting rod; the upper mating bearing and the lower mating bearing are coaxially arranged.

4. The aircraft door interchangeability detection tooling according to claim 3, wherein: The hinge arm mating mechanism (300) is arranged on one side of the tooling frame (100) where the front side contour comparison template (210) is installed, and part of the front side contour comparison template (210) is fixedly connected to the tooling frame (100) through a support; the rear side contour comparison template (220) is integrally fixedly connected to the tooling frame (100).

5. The aircraft door interchangeability detection tooling according to claim 1, characterized in that: The grooved rail position detection block is composed of a support rod and a guide wheel; one end of the support rod is fixedly connected to one side of the tooling frame (100) where the front side contour comparison template (210) is installed, the other end of the support rod horizontally extends from the rear of the front side contour comparison template (210) to the inside of the frame-shaped structure of the cabin door contour comparison component (200), and the guide wheel is installed at the end of the support rod that is not connected to the tooling frame (100).

6. The aircraft cabin door interchangeability detection tooling according to claim 1, characterized in that: It also includes a tooling base (400) fixedly connected to the bottom of the tooling frame (100).

7. Detection method for interchangeability of aircraft cabin doors, characterized in that: Using the aircraft cabin door interchangeability detection tooling according to any one of claims 1 to 6, the following steps are carried out: Step 1: Install the aircraft cabin door on the cabin door contour comparison component (200) of the aircraft cabin door interchangeability detection tooling, and make the outer contour edge of the aircraft cabin door abut against the cabin door contour comparison component (200). Step 2: Cooperate and connect the hinge arm on the aircraft cabin door with the hinge arm cooperation mechanism (300), and check and evaluate the attitude performance of the aircraft cabin door on the aircraft cabin door interchangeability detection tooling when the aircraft cabin door is in the open state; Step 3: Confirm the position of the grooved rail joint on the aircraft cabin door, and judge whether the position of the grooved rail joint can correspond to the position of the grooved rail joint position detection block. If it is judged that there is a deviation in the position of the grooved rail joint, debug the moving parts on the aircraft cabin door so that the grooved rail joint position detection block can be connected with the grooved rail joint; Step 4: Use a general measuring tool to measure the step difference and clearance value between the cabin door outer shape comparison component (200) and the aircraft cabin door, and debug the moving parts on the aircraft cabin door so that the clearance value is not less than 2 mm, and take the cabin door outer shape comparison component (200) as the auto-collimation, with the step difference within the following required ranges: the front side required range is 0 - 9 mm, the rear side required range is 0 - 6 mm, the upper part required range is 0 - 12 mm, and the lower part required range is 0 - 9 mm; Step 5: Compare and check the installed stop on the aircraft cabin door with the stop detection marking points on the cabin door outer shape comparison component (200), and use a general measuring tool to measure the distance dimension between the stop and the cabin door outer shape comparison component (200), and debug the moving parts on the aircraft cabin door so that the distance between the stop and the cabin door outer shape comparison component (200) is not less than 10 mm; Step 6: Rotate the aircraft cabin door and check whether the cooperation position between the hinge arm on the aircraft cabin door and the hinge arm cooperation mechanism (300) rotates flexibly; Step 7: Summarize the relative relationship between the debugged aircraft cabin door and the aircraft cabin door interchangeability detection tooling to form the result of the detection record report. Finally, install the aircraft cabin door and the aircraft nose reference part, and perform directional fine-tuning according to the result of the detection record report to complete the interchangeability detection work.

Images