Large aircraft door positioning device

Abstract

This application relates to a large aircraft cabin door positioning device, belonging to the technical field of aircraft assembly. It includes two sets of annular inner retaining frames, an auxiliary support assembly disposed between the two sets of inner retaining frames, and a positioning fixture disposed on the inner retaining frames. Each inner retaining frame includes a cabin door support portion and a wall panel support portion. The large aircraft cabin door is located at the cabin door support portion. Both the auxiliary support assembly and the positioning fixture are disposed at the cabin door support portion. The auxiliary support assembly includes a support seat disposed between the two sets of inner retaining frames, a support component slidably connected to the support seat along the diameter of the annular inner retaining frame, and a drive component for driving the support component to slide. This application has the advantages of facilitating cabin door positioning during aircraft assembly and providing a high level of support.

Description

Technical Field

[0001] This application relates to the technical field of aircraft assembly technology, and in particular to a large aircraft cabin door positioning device. Background Technology

[0002] Aircraft assembly has strict process requirements. The assembly components used, which require positioning, are simply called positioning assembly devices or positioning tooling devices. Their main purpose is to ensure the precise positioning and installation of various aircraft parts, coordinate the positional relationships between the parts, improve aircraft production efficiency, and reduce costs. Because aircraft parts are weak in rigidity, numerous, and have complex coordination relationships, aircraft assembly differs from general mechanical product assembly and requires the use of specialized assembly jigs to shape and position aircraft parts.

[0003] Aircraft assembly tooling extensively uses truss-type welded frames, with locators and frames fixedly connected. The assembly method for aircraft fuselage structures involves shaping and positioning over 90% of the aircraft fuselage parts using fuselage assembly jigs. Most components in the fuselage structure require jig positioning and assembly, so assembly jigs are usually specialized. The most difficult position to position and assemble is the cabin door.

[0004] Regarding the aforementioned technologies, the inventors believe that there is a deficiency in the lack of tooling structures for rapid assembly of hatches. Summary of the Invention

[0005] To solve the above-mentioned technical problems, this application provides a large aircraft cabin door positioning device.

[0006] This application provides a large aircraft cabin door positioning device, which adopts the following technical solution:

[0007] A large aircraft cabin door positioning device includes two sets of annular inner retaining frames, an auxiliary support assembly disposed between the two sets of inner retaining frames, and a positioning fixture disposed on the inner retaining frames. The inner retaining frames include a cabin door support portion and a wall panel support portion. The large aircraft cabin door is located at the cabin door support portion. The auxiliary support assembly and the positioning fixture are both disposed at the cabin door support portion. The auxiliary support assembly includes a support seat disposed between the two sets of inner retaining frames, a support assembly slidably connected to the support seat along the diameter direction of the annular inner retaining frames, and a drive assembly for driving the support assembly to slide.

[0008] By adopting the above technical solution, the aircraft's bulkhead is stably supported by the bulkhead support on the inner frame, and the aircraft's door is positioned and supported by the door support. An auxiliary support component is set up to support the door. The length of the support component is adjusted by the drive component so that the support component can abut against the inner wall of the door. At this time, the aircraft's bulkhead and door can be stably supported, which facilitates the assembly of the door by the operator.

[0009] Preferably, the support assembly includes a support rod, and a support connection hole is provided on the support base at the position corresponding to the support rod. The support rod is slidably connected in the support connection hole. The drive assembly includes a turntable, which is rotatably connected to the support base. The turntable is sleeved on the support rod and threadedly connected to the support rod. The top end of the support rod is detachably connected to a tray adapted to the shape of the large aircraft cabin door.

[0010] Preferably, an expansion assembly is provided on the inner retaining frame at the location of the hatch support. The expansion assembly includes a mounting bracket detachably connected to the inner retaining frame and a telescopic cylinder detachably connected to the mounting bracket. The piston rod of the telescopic cylinder faces away from the hatch support, and an expansion mounting hole is provided on the piston rod of the telescopic cylinder.

[0011] By adopting the above technical solution, the piston rod of the telescopic cylinder can be extended through the external expansion component to assist in the installation of aircraft panels and cabin doors, and other devices can be installed at the outer end of the piston rod.

[0012] Preferably, a contact-type early warning sensor is provided on the inner retaining frame next to the outer expansion component, and the sensing end of the contact-type early warning sensor is slightly lower than the support plate.

[0013] By adopting the above technical solution and setting up contact-type early warning sensors, it is easy to detect when aircraft panels or other devices are touched and issue early warning signals, thereby improving safety performance during construction.

[0014] Preferably, a buffer assembly is provided on the inner retaining frame ring surface between the two sets of door support parts. The buffer assembly includes a connecting seat detachably connected to the side of the inner retaining frame, a connecting arm rotatably connected to the connecting seat, and a buffer part detachably connected to the upper end of the connecting arm. The upper end of the connecting arm has an insertion port, and the buffer part is inserted into the insertion port.

[0015] By adopting the above technical solution, setting up a buffer component and inserting it into the socket, the buffer component can be installed according to the actual situation of the aircraft panel, which is simple and convenient to operate.

[0016] Preferably, a support sleeve is provided between the support rod and the support base. The side of the support sleeve has a support hole that penetrates the support base. A support pin is inserted into the support hole. A through hole is provided on the support rod at the position corresponding to the support pin. A linkage component is provided on the support pin to control its insertion into or release from the through hole on the support rod. The linkage component includes an inductive sensor. The inductive sensor is disposed on the buffer component and controls the support pin to be inserted into the through hole when the aircraft panel contacts the buffer component.

[0017] By adopting the above technical solution, the linkage component allows the support pin to be inserted into the through hole when the buffer component begins buffering, thus achieving stable fixation between the two and making the assembly of aircraft panels and large aircraft doors safer.

[0018] Preferably, a transition section is provided between the hatch support and the wall panel support, and the hatch support, the wall panel support, and the transition section together form a Z-shaped structure; the arc height of the hatch support is lower than the arc height of the wall panel support.

[0019] By adopting the above technical solution and setting a Z-shaped transition section, the door support and the wall panel support are relatively more stable, which can effectively improve the safety performance during the assembly process.

[0020] Preferably, a first positioning plate is detachably connected to the wall panel support next to the transition section, and the first positioning plate has multiple slots adapted to the aircraft wall panel.

[0021] By adopting the above technical solution, setting a first positioning plate, and supplementing it with a door support, the aircraft panel can be stably supported, which facilitates the assembly of the aircraft panel.

[0022] Preferably, multiple sets of guide rail sliders are installed on the wall panel support. The fixed part of the guide rail slider is detachably connected to the wall panel support. The sliding part of the guide rail slider is detachably connected to a second positioning plate. A locking assembly is provided between the second positioning plate and the wall panel support to lock and fix the two together.

[0023] Preferably, the wall panel support portion is provided with a plurality of positioning holes along its radial direction, and the locking assembly includes a positioning pin mounted on the second positioning plate, the positioning pin being able to be inserted into the positioning hole to realize the positioning of the second positioning plate.

[0024] By adopting the above technical solution, the second positioning plate can be raised or lowered by the locking components and corresponding guide rail sliders, so that the support effect can be adjusted at any time, thereby improving the assembly quality of aircraft panels and large aircraft doors.

[0025] In summary, this application includes at least one of the following beneficial technical effects:

[0026] The aircraft's bulkhead is stably supported by the bulkhead support on the inner frame, and the aircraft's door is positioned and supported by the door support. An auxiliary support assembly is set up to support the door position. The length of the support assembly is adjusted by the drive assembly so that the support assembly can abut against the inner wall of the door. At this time, the bulkhead and door of the aircraft can be stably supported, which facilitates the assembly of the door by the operator.

[0027] The linkage component allows the support pin to be inserted into the through hole when the buffer component begins buffering, achieving stable fixation between the two and making the assembly of aircraft panels and large aircraft doors safer. The first positioning plate, supplemented by the door support, enables the aircraft panel to be stably supported, facilitating the assembly of the aircraft panel. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the overall structure of the embodiment.

[0029] Figure 2 This is a schematic diagram of the support components in the embodiment.

[0030] Figure 3 This is a schematic diagram of one side of the internal retaining frame in the embodiment.

[0031] Figure 4 yes Figure 3 Enlarged view of section A.

[0032] Figure 5 This is a schematic diagram of the other side of the internal retaining frame in the embodiment.

[0033] Figure 6 This is a schematic diagram of the air pressure compensation unit in the embodiment.

[0034] Figure 7 This is a schematic diagram of the structure of the rubber ring in the embodiment.

[0035] Explanation of reference numerals in the attached drawings: 1. Inner retaining frame; 11. Door support; 12. Wall panel support; 13. Transition section; 2. Auxiliary support assembly; 21. Support seat; 22. Support assembly; 221. Support rod; 223. Support plate; 2231. Air hole; 224. Support sleeve; 226. Support pin; 23. Drive assembly; 231. Turntable; 27. First positioning plate; 271. Groove; 28. Guide rail slider; 281. Second positioning plate; 282. Locking assembly; 2821. Positioning hole; 2822. Positioning pin; 3. Rubber ring; 31. Compensation gap; 4. Air pressure compensation unit; 41. Air supply source; 42. Air pipe; 5. Adjustment seat; 51. Air passage; 511. Slot; 6. Temperature sensor; 7. Heater. Detailed Implementation

[0036] The following is in conjunction with the appendix Figure 1-7 This application will be described in further detail.

[0037] This application discloses a large aircraft cabin door positioning device, referring to... Figure 1-5 The system includes two sets of annular inner conformal frames 1, an auxiliary support assembly disposed between the two sets of inner conformal frames 1, and a positioning fixture disposed on the inner conformal frames 1. The inner conformal frame 1 includes a door support part 11 and a wall panel support part 12. The large aircraft door is located at the door support part 11. The auxiliary support assembly and the positioning fixture are both disposed at the door support part 11. The auxiliary support assembly includes a support seat 21 disposed between the two sets of inner conformal frames 1, a support component 22 slidably connected to the support seat 21 along the diameter direction of the annular inner conformal frame 1, and a drive component 23 for driving the support component 22 to slide. A transition section 13 is provided between the door support part 11 and the wall panel support part 12. The door support part 11, the wall panel support part 12, and the transition section 13 together form a Z-shaped structure. The arc height of the door support part 11 is lower than the arc height of the wall panel support part 12.

[0038] By setting a Z-shaped transition section 13, the door support 11 and the wall panel support 12 are relatively more stable. The wall panel support 12 on the inner conformal frame 1 provides stable support for the aircraft wall panel, and the door support 11 provides positioning support for the aircraft door position. An auxiliary support component is set to support the door position. The length of the support component 22 is adjusted by the drive component 23 so that the support component 22 can abut against the inner wall of the door. At this time, the aircraft wall panel and door can be stably supported, which facilitates the assembly of the door by the operator.

[0039] The support assembly 22 includes a support rod 221. A support connection hole is provided on the support base 21 corresponding to the position of the support rod 221. The support rod 221 is slidably connected within the support connection hole. The drive assembly 23 includes a turntable 231, which is rotatably connected to the support base 21 and sleeved on the support rod 221, threadedly connected to it. A tray 223 adapted to the shape of a large aircraft door is detachably connected to the top of the support rod 221. A groove is formed in the middle of the tray 223, and airflow channels are provided at the protrusions on the tray 223. A rubber ring 3 is provided on the outer side of the airflow channel, and an airflow detection assembly is provided inside the airflow channel. The airflow detection assembly is used to detect the gap between the rubber ring 3 and the large aircraft door. Because the aircraft panels and doors are curved, if the gap between the large aircraft door and the rubber ring 3 is large, other devices can be adjusted to make the tray more flexible. It fits tightly against the cabin door position; a buffer assembly is provided on the inner conformal frame 1 ring surface between the two sets of cabin door support parts 11. The buffer assembly includes a connecting seat detachably connected to the side of the inner conformal frame 1, a connecting arm rotatably connected to the connecting seat, and a buffer part detachably connected to the upper end of the connecting arm; the upper end of the connecting arm has an insertion port, and the buffer part is inserted into the insertion port. A support sleeve 224 is provided between the support rod 221 and the support seat 21. A support hole penetrating the support seat 21 is provided on the side of the support sleeve 224. A support pin 226 is inserted into the support hole. A through hole is provided on the support rod 221 at the position corresponding to the support pin 226. A linkage assembly is provided on the support pin 226 to control its extension into or detachment from the through hole on the support rod 221. The linkage assembly includes an inductive sensor. The inductive sensor is provided on the buffer assembly and controls the support pin 226 to be inserted into the through hole when the aircraft panel contacts the buffer assembly.

[0040] An expansion assembly is provided on the inner retaining frame 1 at the location corresponding to the hatch support 11. The expansion assembly includes a mounting bracket detachably connected to the inner retaining frame 1 and a telescopic cylinder detachably connected to the mounting bracket. The piston rod of the telescopic cylinder faces away from the hatch support 11, and an expansion mounting hole is provided on the piston rod of the telescopic cylinder. A contact-type warning sensor is provided on the inner retaining frame 1 next to the expansion assembly. The sensing end of the contact-type warning sensor is slightly lower than the support plate 223.

[0041] A first positioning plate 27 is detachably connected to the wall panel support 12 next to the transition section 13. The first positioning plate has multiple slots 271 adapted to the aircraft wall panel. Multiple sets of guide rail sliders 28 are installed on the wall panel support 12. The fixed part of the guide rail slider 28 is detachably connected to the wall panel support 12, and the sliding part of the guide rail slider 28 is detachably connected to a second positioning plate 281. A locking assembly 282 is provided between the second positioning plate 281 and the wall panel support 12 to lock and fix the two. Multiple sets of positioning holes 2821 are provided on the wall panel support 12 along its radial direction. The locking assembly 282 includes a positioning pin 2822 installed on the second positioning plate 281. The positioning pin 2822 can be inserted into the positioning hole 2821 to realize the positioning of the second positioning plate 281.

[0042] The working principle of the large aircraft cabin door positioning device in this application is as follows:

[0043] The aircraft's bulkhead is stably supported by the bulkhead support 12 on the inner frame 1, and the aircraft's door is positioned and supported by the door support 11. An auxiliary support assembly is provided for support at the door position. The length of the support assembly 22 is adjusted by the drive assembly 23 so that the support assembly 22 can abut against the inner wall of the door. This provides stable support for the aircraft's bulkhead and door, facilitating door assembly by operators. An external expansion assembly is used for auxiliary installation of the aircraft's bulkhead and door. The piston rod of the telescopic cylinder can extend... The piston rod is long, and other devices are installed at the outer end. A buffer assembly is set and inserted into the socket. The buffer assembly can be installed according to the actual situation of the aircraft panel. The linkage assembly can insert the support pin 226 into the through hole when the buffer assembly starts to perform buffering treatment, so as to achieve stable fixation between the two. The locking assembly 282 and the corresponding guide rail slider 28 can control the second positioning plate 281 to rise or fall, so that the support effect can be adjusted at any time, improving the assembly quality of the aircraft panel and the large aircraft door.

[0044] Reference Figure 6 and Figure 7As a new embodiment, when the temperature drops during the assembly of the large aircraft cabin door, the rubber ring 3 shrinks due to the cold and becomes brittle. At this time, there is a gap between the large aircraft cabin door and the rubber ring 3, causing the large aircraft cabin door to wobble slightly. Furthermore, the large aircraft cabin door is prone to damaging the brittle rubber ring 3 when it is squeezed. Therefore, a compensation gap 31 is provided on the rubber ring. The compensation gap 31 has a width of 1 mm. An air hole 2231 communicating with the compensation gap 31 is provided on the support plate 223. An air pressure compensation unit 4 is provided on the support base 21. The air pressure compensation unit 4 includes an air supply source 41 and an air pipe 42. The air supply source 41 is provided on the support base 21. It contains high-pressure gas; an adjusting seat 5 is provided on the gas supply source 41; an air passage 51 communicating with the inside of the gas supply source 41 is opened in the adjusting seat 5; one end of the air pipe 42 is connected to the air passage 51, and the other end is connected to the air hole 2231 after passing through the heater 7; a slot 511 is opened on the side wall of the air passage 51; a temperature sensor 6 is provided in the adjusting seat 5; one end of the temperature sensor 6 is fixedly connected to the inner wall of the air passage 51, and the other end is inserted into the slot 511; in the initial state, the temperature sensor 6 closes the air passage 51; the end of the temperature sensor 6 inserted into the slot 511 is in close contact with the inner wall of the slot 511 to prevent the air pressure in the gas supply source 41 from squeezing the end of the temperature sensor 6 out of the slot 511.

[0045] When the workshop temperature drops too much, the temperature sensor 6 shrinks due to the cold, reducing the friction between the end of the temperature sensor 6 inserted into the slot 511 and the slot 511. At this time, the air pressure in the air supply source 41 pushes the temperature sensor 6 and causes it to disengage from the slot 511, thereby connecting the air supply source 41 with the air pipe 42. A temperature sensor can be installed on the support base. When the temperature drops to the preset temperature value, the heater 7 is activated, heating the gas in the air pipe 42. After heating, the gas is rushed into the compensation gap 31, which on the one hand heats the rubber ring 3, restoring its elasticity; on the other hand, the high-pressure gas in the compensation gap 31 provides temporary support, ensuring the stable support of the large aircraft door.

[0046] After the rubber ring 3 shrinks due to cold, the width of the compensation gap 31 increases, which facilitates a wider contact area between the high-pressure gas and the large aircraft door, thereby improving the support effect of the large aircraft door.

[0047] The temperature sensing element 6 includes a natural rubber layer and a vulcanized rubber layer; the natural rubber layer shrinks significantly when cooled, while the vulcanized rubber layer enhances the structural strength of the temperature sensing element 6, enabling it to withstand the high-pressure gas in the gas supply source 41.

[0048] The above are all preferred embodiments of this application and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A large aircraft cabin door positioning device, characterized in that: The system includes two sets of annular inner retaining frames (1), an auxiliary support assembly (2) disposed between the two sets of inner retaining frames (1), and a positioning fixture disposed on the inner retaining frames (1). The inner retaining frame (1) includes a door support part (11) and a wall panel support part (12). The large aircraft door is located at the door support part (11). The auxiliary support assembly (2) and the positioning fixture are both disposed at the door support part (11). The auxiliary support assembly (2) includes a support seat (21) disposed between the two sets of inner retaining frames (1), a support assembly (22) slidably connected to the support seat (21) along the diameter direction of the annular inner retaining frame (1), and a drive assembly (23) for driving the support assembly (22) to slide. The support assembly (22) includes a support rod (221); the top end of the support rod (221) is detachably connected to a tray (223) adapted to the shape of a large aircraft door; A buffer assembly is provided on the inner retaining frame (1) ring surface between the two sets of door support parts (11). The buffer assembly includes a connecting seat detachably connected to the side of the inner retaining frame (1), a connecting arm rotatably connected to the connecting seat, and a buffer part detachably connected to the upper end of the connecting arm. The upper end of the connecting arm is provided with a socket, and the buffer part is inserted into the socket. A support sleeve (224) is provided between the support rod (221) and the support base (21). The side of the support sleeve (224) is provided with a support hole that penetrates the support base (21). A support pin (226) is inserted into the support hole. A through hole is provided on the support rod (221) at the position corresponding to the support pin (226). A linkage component is provided on the support pin (226) to control its insertion into or removal from the through hole on the support rod (221). The linkage component includes an inductive sensor. The inductive sensor is provided on the buffer component and controls the support pin (226) to be inserted into the through hole when the aircraft panel contacts the buffer component.

2. The large aircraft cabin door positioning device according to claim 1, characterized in that: The support base (21) has a support connection hole at the position corresponding to the support rod (221). The support rod (221) is slidably connected in the support connection hole. The drive assembly (23) includes a turntable (231). The turntable (231) is rotatably connected to the support base (21), and the turntable (231) is sleeved on the support rod (221) and threadedly connected to the support rod (221).

3. The large aircraft cabin door positioning device according to claim 1, characterized in that: An expansion assembly is provided on the inner retaining frame (1) at the location corresponding to the hatch support (11). The expansion assembly includes a mounting bracket detachably connected to the inner retaining frame (1) and a telescopic cylinder detachably connected to the mounting bracket. The piston rod of the telescopic cylinder faces away from the hatch support (11), and an expansion mounting hole is provided on the piston rod of the telescopic cylinder.

4. The large aircraft cabin door positioning device according to claim 3, characterized in that: A contact-type early warning sensor is provided on the inner protective frame (1) next to the outer expansion component, and the sensing end of the contact-type early warning sensor is slightly lower than the tray (223).

5. A large aircraft cabin door positioning device according to claim 1, characterized in that: A transition section (13) is provided between the hatch support (11) and the wall panel support (12), and the hatch support (11), the wall panel support (12) and the transition section (13) together form a Z-shaped structure; the arc height of the hatch support (11) is lower than the arc height of the wall panel support (12).

6. A large aircraft cabin door positioning device according to claim 5, characterized in that: A first positioning plate (27) is detachably connected to the wall panel support (12) next to the transition section (13), and the first positioning plate (27) has multiple slots (271) adapted to the aircraft wall panel.

7. A large aircraft cabin door positioning device according to claim 1, characterized in that: Multiple sets of guide rail sliders (28) are installed on the wall panel support (12). The fixed part of the guide rail slider (28) is detachably connected to the wall panel support (12), and the sliding part of the guide rail slider (28) is detachably connected to a second positioning plate (281). A locking assembly (282) is provided between the second positioning plate (281) and the wall panel support (12) to lock and fix the two together.

8. A large aircraft cabin door positioning device according to claim 7, characterized in that: The wall panel support (12) is provided with a plurality of positioning holes (2821) along its radial direction. The locking assembly (282) includes a positioning pin (2822) installed on the second positioning plate (281). The positioning pin (2822) can be inserted into the positioning hole (2821) to realize the positioning of the second positioning plate (281).

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