Device and method for installing omega-shaped sealing ring of aircraft canopy control actuator cylinder

Abstract

The invention discloses a mounting device and method for an omega-shaped sealing ring of an aircraft canopy control actuator cylinder, and relates to the technical field of aviation product repair, the device comprises a support, a screw and a pull claw, and a threaded hole is formed in the center of the support; the screw is connected with the threaded hole, one end of the screw is provided with a handle, the other end of the screw is rotationally connected with a check ring, and a plurality of radial notches are formed in the edge of the check ring. The pull claws are arranged around the support, one end of each pull claw is hinged to the support, and the other end of each pull claw penetrates through the corresponding notch. During installation, the omega-shaped sealing ring is installed on the non-metal expansion ring, the omega-shaped sealing ring and the non-metal expansion ring are pressed into the cover together, then the metal expansion ring is placed into the cover, the device is adopted for installation, the metal expansion ring is pressed tightly, the metal expansion ring and the cover are assembled to the outer cylinder together to be screwed and assembled, and then the piston rod is installed. The omega-shaped sealing ring can be rapidly, safely and accurately installed, it is guaranteed that the omega-shaped sealing ring is not damaged during assembly, and the sealing work performance of the canopy control actuator cylinder is guaranteed.

Description

Technical Field

[0001] The invention relates to the technical field of aviation product repair, and is used for installing an omega-shaped sealing ring of an aircraft canopy operating cylinder, and more specifically to an installation device and method for an omega-shaped sealing ring of an aircraft canopy operating cylinder. Background Art

[0002] The canopy operating actuator is composed of a hydraulic chamber, a pneumatic chamber, and an elastic lock. It is an accessory of the aircraft canopy pneumatic system and is used to operate the canopy to open, close, or reach any stroke. The Ω-shaped sealing ring is prone to mechanical scratches at the root of the outer corner of the fixed edge during the tightening and assembly process, and then overload tearing occurs.

[0003] When assembling, Figure 1 As shown, first install the Ω-shaped sealing ring on the non-metallic expansion ring, and distribute the Ω-shaped sealing ring evenly; press the Ω-shaped sealing ring and the non-metallic expansion ring into the cover together, ensure that the fixed edge of one side of the Ω-shaped sealing ring is embedded in the installation groove of the cover and evenly distributed; finally, put the metal expansion ring into the cover and assemble it to the outer cylinder together with the cover. In actual assembly, it is difficult to observe the state that the fixed edge is completely embedded in the metal expansion ring groove or unevenly distributed in the metal expansion ring groove. It may also cause the fixed edge of the Ω-shaped sealing ring to not be completely embedded in the metal expansion ring groove, or unevenly distributed in the metal expansion ring groove. The fixed edge of the Ω-shaped sealing ring contacts and presses with the convex shoulder of the metal expansion ring groove. In the subsequent process of tightening the cover, when the friction between the metal expansion ring and the cylinder is greater than the friction between the metal expansion ring and the cover, the metal expansion ring rotates with the cylinder. When the cover and the metal expansion ring undergo relative rotation displacement, the Ω-shaped sealing ring may be crushed and cut.

[0004] In order to solve this problem, the Ω-shaped sealing ring and the non-metallic expansion ring need to be soaked in 7650 lubricant for 15 to 18 hours before assembly. After soaking, the diameter of the Ω-shaped sealing ring should be 48.5mm to 49.5mm. However, in the actual assembly process, the Ω-shaped sealing ring expands too much after being soaked in lubricant. After being constrained by the non-metallic expansion ring, it is installed in the cover. The fixed side of one side of the Ω-shaped sealing ring is constrained by the cover, and the other side is in an unconstrained state. The outer diameter of the fixed surface in the unconstrained state exceeds the outer diameter of the metal expansion ring installation groove by a large amount. It cannot enter the installation groove by itself under the extrusion of the metal expansion ring cover, and the Ω-shaped sealing ring is squeezed and deformed. The groove convex shoulder of the additional metal expansion ring causes relative displacement between the metal expansion ring and the Ω-shaped sealing ring as the outer cylinder rotates during assembly and disassembly. The Ω-shaped sealing ring is scratched by the convex shoulder of the metal expansion ring groove, resulting in overload cracking.

[0005] It can be seen that the existing installation method is difficult to ensure that the size of the Ω-shaped sealing ring is in a qualified state, it is difficult to observe the state of the fixed edge of the Ω-shaped sealing ring embedded in the metal expansion ring groove, and it is difficult to ensure that it is completely embedded in the metal expansion ring groove and evenly distributed in the metal expansion ring groove, and it is difficult to avoid the metal expansion ring from rotating with the barrel. The installation process depends on the experience and state of the personnel, the operation is inconvenient, and the stability and accuracy of the installation process cannot be guaranteed.

[0006] Therefore, it is necessary to design a device that can reliably install the Ω-shaped sealing ring, and correspondingly propose a method that can reliably install the Ω-shaped sealing ring, so as to improve installation efficiency, reduce installation risks, reduce personnel operation errors, and solve production safety hazards. Summary of the invention

[0007] In view of this, the present invention provides an Ω-shaped sealing ring installation device and method for an aircraft canopy control actuator, which can quickly, safely and accurately install the Ω-shaped sealing ring. The assembly process, tooling and method are formulated to ensure that the Ω-shaped sealing ring is not damaged during assembly and to ensure the sealing performance of the canopy control actuator.

[0008] In order to achieve the above object, the present invention adopts the following technical solution:

[0009] An Ω-shaped sealing ring installation device for an aircraft canopy operating cylinder comprises:

[0010] A support, wherein a threaded hole is provided at the center of the support;

[0011] A screw rod, the screw rod is connected to the threaded hole, one end of the screw rod is provided with a handle, the other end of the screw rod is rotatably connected with a retaining ring, and the edge of the retaining ring is provided with a plurality of radial notches;

[0012] A pulling claw, the number of which is the same as the number of the notches, a plurality of the pulling claws are arranged around the support, one end of the pulling claw is hinged to the support, and the other end of the pulling claw passes through the corresponding notch.

[0013] Through the above technical scheme, the present invention adopts structures such as a handle, a screw, a support, a retaining ring and a claw to solve the problem that it is difficult to observe the state of the fixed edge of the Ω-shaped sealing ring embedded in the groove of the metal expansion ring during assembly, avoids the metal expansion ring from rotating together with the barrel, and avoids the Ω-shaped sealing ring from being crushed and cut. It can reduce the assembly error caused by the difficulty in observing the assembly state, and at the same time avoid relative displacement between the metal expansion ring and the cover. At the same time, it reduces the difficulty of manual installation, improves the efficiency of installation, and reduces production safety risks. It has certain innovation and practical application value, and can provide a certain reference for the installation of sealing structures of similar products.

[0014] Preferably, in the above-mentioned aircraft canopy operating cylinder Ω-shaped sealing ring installation device, the end of the screw rod away from the retaining ring has a handle plug, the handle plug has a socket, and the handle is inserted into the socket. The spiral handle can quickly and accurately adjust the position and opening angle of the pull claw, which is convenient for operators to use and improves work efficiency.

[0015] Preferably, in the above-mentioned aircraft canopy operating cylinder Ω-shaped sealing ring installation device, the end of the screw rod away from the handle plug has a connecting section with a reduced diameter, and the connecting section is inserted into a rotating hole opened in the middle of the retaining ring, and a thrust ball bearing is sleeved on the connecting section, and the thrust ball bearing is located between the retaining ring and the stepped surface of the connecting section, and a washer corresponding to the rotating hole is provided on the surface of the retaining ring on the side facing away from the screw rod, and the screw passes through the washer and is threadedly connected to the connecting section.

[0016] Preferably, in the above-mentioned aircraft canopy operating cylinder Ω-shaped sealing ring installation device, the edge of the support has a U-shaped notch, the end of the pull claw away from the retaining ring is arranged in the U-shaped notch, and the pull claw is hinged to the U-shaped notch by a cylindrical pin.

[0017] Preferably, in the above-mentioned aircraft canopy operating cylinder Ω-shaped sealing ring installation device, the spacing between the plurality of pull claws from one end of the cylindrical pin to the other end is gradually reduced, and the end of the pull claw away from the retaining ring is radially turned outward, and a fixing sleeve is provided on the turned-out part. The three pull claws adopt a variable cross-sectional area structure, which can accurately adjust the opening angle of the three pull claws and control the diameter near the free end so as to pass through or fit the inner diameter of the metal expansion ring.

[0018] Preferably, in the above-mentioned aircraft canopy operating cylinder Ω-shaped sealing ring installation device, the fixing sleeve is a rubber sleeve. The end of the pull claw adopts a fixing sleeve structure, which can reliably press and fix the metal expansion ring without damaging the metal expansion ring.

[0019] The present invention also provides a method for installing an Ω-shaped sealing ring of an aircraft canopy operating cylinder, which comprises the following steps: firstly installing the Ω-shaped sealing ring on a non-metallic expansion ring, pressing the Ω-shaped sealing ring and the non-metallic expansion ring together into the cover, then placing the metal expansion ring into the cover, and using the above-mentioned Ω-shaped sealing ring installation device for an aircraft canopy operating cylinder to install the metal expansion ring, the metal expansion ring is pressed, assembled together with the cover onto an outer cylinder and tightened, and then the piston rod is installed.

[0020] Preferably, in the above-mentioned method for installing the Ω-shaped sealing ring of the aircraft canopy operating cylinder, when using the device, the handle is rotated to adjust the position of the support so that the free ends of the three pulling claws are gathered together, the free ends of the three pulling claws are passed through the end cover of the canopy operating cylinder, the non-metallic expansion ring and the inner ring of the metal expansion ring, and the retaining ring is pressed against the outer side of the end cover of the canopy operating cylinder, the handle is rotated to make the free ends of the three pulling claws move away from each other, the fixing sleeve presses the metal expansion ring, and the handle is continued to be rotated so that the metal expansion ring is stably pressed.

[0021] Preferably, in the above-mentioned method for installing an Ω-shaped sealing ring of an aircraft canopy operating cylinder, during the installation of the Ω-shaped sealing ring and the non-metallic expansion ring, the Ω-shaped sealing ring is ensured to be evenly distributed.

[0022] Preferably, in the above-mentioned aircraft canopy operating cylinder Ω-shaped sealing ring installation method, during the process of pressing the Ω-shaped sealing ring and the non-metallic expansion ring into the cover together, ensure that one side fixed edge of the Ω-shaped sealing ring is embedded in the installation groove of the cover and evenly distributed.

[0023] It can be seen from the above technical solutions that, compared with the prior art, the present invention discloses a device and method for installing an Ω-shaped sealing ring of an aircraft canopy operating cylinder, which has the following beneficial effects:

[0024] 1. The present invention can improve installation efficiency: through the coordination of structures such as the handle, screw, support, retaining ring and claw, the position and opening angle of the claw can be quickly and accurately adjusted by rotating the handle, so that the free end of the claw can quickly pass through the end cover of the canopy operating cylinder, the non-metallic expansion ring and the inner ring of the metal expansion ring, and the retaining ring is pressed against the outer side of the end cover of the canopy operating cylinder, thereby realizing the rapid compression and fixation of the metal expansion ring, greatly shortening the adjustment time before installation and improving the overall efficiency of installation. Compared with the traditional installation method, the device and method of the present invention simplifies multiple steps in the assembly process, avoids repeated adjustments and inspections caused by insufficient experience or improper operation, makes the entire installation process smoother and more convenient, and further improves the installation efficiency.

[0025] 2. The present invention can reduce installation risks: during the installation process, it can effectively prevent the Ω-shaped sealing ring from being crushed and cut due to the rotation of the metal expansion ring and the tube. The stable pressing effect of the pull claw and the fixed sleeve ensures that the metal expansion ring will not undergo relative rotational displacement with the cockpit cover during the assembly process, thereby protecting the Ω-shaped sealing ring from damage, ensuring the integrity and sealing performance of the sealing ring, and reducing the potential risks caused by damage to the sealing ring. The structural design and operation method of the device are simple and clear, easy to master, reducing the dependence on the operator's experience and skill level, reducing assembly errors and safety hazards caused by improper operation or mistakes, and improving the stability and reliability of the installation process.

[0026] 3. The present invention can improve the installation quality: by precisely controlling the immersion time of the Ω-shaped sealing ring and using an optical automatic image measuring instrument to measure the size, the dimensional change of the sealing ring can be accurately grasped to ensure that it matches the size of the metal expansion ring slot during installation, so that the Ω-shaped sealing ring can be completely embedded in the metal expansion ring slot and evenly distributed in the slot, thereby improving the installation quality and enhancing the sealing performance of the cockpit cover control actuator. The surface quality inspection of the metal expansion ring, the cleaning of the Ω-shaped sealing ring after immersion, the detailed requirements for the matching assembly of the piston rod and the end cover, and the assembly inspection and pre-assembly of the Ω-shaped sealing ring and expansion ring assembly are added, and the assembly process is strictly controlled from multiple aspects, further ensuring the reliability and safety of the assembly and improving the overall quality of the product. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0028] Figure 1 The accompanying drawing is a schematic diagram of the installation of an Ω-shaped sealing ring in the prior art;

[0029] Figure 2 The accompanying drawing is a schematic structural diagram of an Ω-shaped sealing ring installation device for an aircraft canopy operating cylinder provided by the present invention;

[0030] Figure 3 The accompanying drawing is a schematic diagram of the structure of the aircraft canopy operating cylinder Ω-shaped sealing ring installation device provided by the present invention from an upward angle;

[0031] Figure 4 The accompanying drawing is a schematic diagram of the structure of the screw provided by the present invention;

[0032] Figure 5 The accompanying drawing is a schematic structural diagram of the connection between the support and the claw provided by the present invention;

[0033] Figure 6 The accompanying drawing is a schematic structural diagram of the retaining ring provided by the present invention;

[0034] Figure 7 The accompanying drawing is a schematic diagram of the use of the aircraft canopy operating cylinder Ω-shaped sealing ring installation device provided by the present invention;

[0035] Figure 8 The accompanying drawing is a relationship diagram between the inner diameter of the Ω-shaped sealing ring provided by the present invention and the total immersion time.

[0036] in:

[0037] 1-fixing sleeve; 2-pulling claw; 3-retaining ring; 4-washer; 5-screw; 6-thrust ball bearing; 7-cylindrical pin; 8-support; 9-screw; 10-handle; 11-threaded hole; 12-slot; 13-handle plug; 14-jack; 15-connecting section; 16-rotating hole; 17-U-shaped slot; 18-Ω-shaped sealing ring; 19-non-metallic expansion ring; 20-metal expansion ring. DETAILED DESCRIPTION

[0038] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0039] The present embodiment provides an Ω-shaped sealing ring installation device and installation method for an aircraft canopy control actuator, which mainly include designing and manufacturing installation fixing tooling, determining the installation method, adding a record of the actual immersion time of the Ω-shaped sealing ring, measuring the size of the Ω-shaped sealing ring with an optical automatic image measuring instrument, adding a fault inspection requirement for the metal expansion ring, adding a cleaning requirement for the Ω-shaped sealing ring after immersion, refining the matching assembly requirements of the piston rod and the end cover, adding an assembly inspection and pre-assembly of the Ω-shaped sealing ring and the expansion ring assembly, so as to ensure the final assembly quality of the Ω-shaped sealing ring.

[0040] It mainly includes product failure statistical analysis, theoretical calculation of sealing ring installation dimensions, verification of sealing ring dimension variation, design and application of installation device, improvement of assembly process and assembly method, ensuring structural application, and ensuring the final assembly quality of Ω-shaped sealing ring.

[0041] Step 1: Fault Statistics Analysis

[0042] Comparative analysis found that the damaged position of the canopy control actuator was the matching position of the air pressure chamber end cover and the metal expansion ring, and the size of the sealing ring after the original aircraft was disassembled in the factory was smaller than the size requirement after immersion during assembly (which is the normal size change of rubber parts after long-term work). The inner diameter of the damaged sealing ring after disassembly in the factory was larger than the inner diameter of the undamaged sealing ring.

[0043] The main cause of the failure is the mismatch between the installation groove and the seal size, which results in the inability of the fixed edge of the Ω-shaped sealing ring to be completely embedded in the groove of the metal expansion ring or uneven distribution in the groove of the metal expansion ring. The fixed edge of the Ω-shaped sealing ring is in contact and pressed with the convex shoulder of the metal expansion ring groove. In the subsequent process of tightening the cover, when the friction between the metal expansion ring and the cylinder is greater than the friction with the cover, the metal expansion ring rotates with the cylinder. When the cover and the metal expansion ring undergo relative rotational displacement, the Ω-shaped sealing ring is likely to be crushed and cut.

[0044] Step 2: Theoretical calculation of sealing ring installation dimensions

[0045] The outer diameter of the sealing ring after oil immersion is calculated by enlarging the size in proportion to the size. The outer diameter of the sealing ring in the free state has exceeded the outer diameter of the metal expansion ring installation groove.

[0046] After the seal ring passes through the constraint of the non-metallic expansion ring, the outer diameter size change mainly occurs in the non-constrained part. The non-constrained part (single side 2.5mm~2.8mm) is proportionally enlarged and calculated, and the outer diameter size of the seal ring changes by (2.66~3.08)mm. The diameter changes by (0.32~1.16)mm, that is, the outer diameter range is: (52.07~53.96)mm. Compared with the design size of the outer diameter of the installation groove Φ53 + 0 0.46 mm does not match exactly.

[0047] Comparing the installation dimensions of the metal expansion ring installation groove and the sealing ring, when the outer diameter of the metal expansion ring installation groove is the lower limit of the size drawing (Φ53), the installation dimension overlap rate is 49%, and the outer diameter of the sealing ring has a 51% probability of exceeding the outer diameter of the metal expansion ring installation groove; when the outer diameter of the metal expansion ring installation groove is the upper limit of the size drawing (Φ53.46), the installation dimension overlap rate is 74%, and the outer diameter of the sealing ring has a 26% probability of exceeding the outer diameter of the metal expansion ring installation groove. That is, the dimension overlap rate when the sealing ring is installed is 49% to 74%. There is a 26% to 51% probability that the outer diameter exceeds the size of the metal expansion ring installation groove.

[0048] Step 3: Verify the change pattern of sealing ring size

[0049] 1. Verification of the size change of the sealing ring after soaking in 7650 grease

[0050] Combination Figure 8 We selected 5 seals to verify the dimensional change law after immersion. The verification results show that the dimensional change of the seal after immersion is mainly related to the immersion time. At the same time, other liquid media, the use status of lubricants, and the residual media on the surface of the seal also have a certain influence on the dimensional change of the seal. Generally, the dimensional range will not exceed the specified range if the immersion does not exceed 24 hours.

[0051] 2. Different immersion methods of sealing rings affect verification

[0052] Table 1 Seal ring change trend results

[0053]

[0054]

[0055] The diameter of part ① is basically unchanged, which means that the diameter of the sealing ring remains basically unchanged when placed in the air;

[0056] The diameter of part ② increases slowly over time, indicating that the sealing ring coated with 132-25 precision instrument oil will slowly increase when placed in the air;

[0057] The diameter of part ③ decreases significantly over time, indicating that the seal ring will shrink significantly when immersed in 132-25 precision instrument oil;

[0058] The diameter of part ④ increased after being placed for 24 hours, and remained basically unchanged afterwards. The reason is that the residual 7650 lubricant was basically completely absorbed by the sealing ring. At this time, part ④ is in the same state as part ①, and the sealing ring no longer continues to increase.

[0059] Verification by different immersion and cleaning methods shows that the change in the diameter of the sealing ring is related to the medium in contact with the surface. After the product is immersed in a qualified size, it needs to be cleaned and dried to avoid the influence of residual medium on the sealing ring.

[0060] When soaking the sealing ring, the soaking time should be controlled to avoid the size deviation and scrapping due to soaking time too long. At the same time, avoid contact with other non-working media.

[0061] Step 4: Installation design and use

[0062] See attached Figure 2 To Attachment Figure 6 This embodiment discloses an Ω-shaped sealing ring installation device for an aircraft canopy operating cylinder, comprising:

[0063] A support 8, wherein a threaded hole 11 is provided at the center of the support 8;

[0064] A screw rod 9, the screw rod 9 is connected to a threaded hole 11, and one end of the screw rod 9 is provided with a handle 10, and the other end of the screw rod 9 is rotatably connected with a retaining ring 3, and the edge of the retaining ring 3 is provided with a plurality of radial notches 12;

[0065] The pulling claws 2 , the number of the pulling claws 2 is the same as the number of the slots 12 , the multiple pulling claws 2 are arranged around the support 8 , and one end of the pulling claw 2 is hinged to the support 8 , and the other end of the pulling claw 2 passes through the corresponding slot 12 .

[0066] In order to further optimize the above technical solution, the end of the screw rod 9 away from the retaining ring 3 has a handle plug 13, and the handle plug 13 has a socket 14, and the handle 10 is inserted into the socket 14. The handle 10 is fixed by a movable shaft connection, and the arm length of the handle 10 can be changed at any time.

[0067] In order to further optimize the above technical solution, the end of the screw 9 away from the handle plug 13 has a connecting section 15 with a reduced diameter. The connecting section 15 is inserted into a rotating hole 16 opened in the middle of the retaining ring 3. A thrust ball bearing 6 is sleeved on the connecting section 15. The thrust ball bearing 6 is located between the step surface of the retaining ring 3 and the connecting section 15. A washer 4 corresponding to the rotating hole 16 is provided on the surface of the retaining ring 3 facing away from the screw 9. The screw 5 passes through the washer 4 and is threadedly connected to the connecting section 15.

[0068] In order to further optimize the above technical solution, the support 8 has a U-shaped notch 17 on its edge, the end of the claw 2 away from the retaining ring 3 is arranged in the U-shaped notch 17, and the claw 2 is hinged to the U-shaped notch 17 through the cylindrical pin 7.

[0069] In order to further optimize the above technical solution, the spacing between the multiple claws 2 from one end of the cylindrical pin 7 to the other end is gradually reduced, and the end of the claw 2 away from the retaining ring 3 is radially turned outward, and the turned-out part is sleeved with a fixing sleeve 1.

[0070] In order to further optimize the above technical solution, the fixing sleeve 1 is a rubber sleeve.

[0071] Step 5: Improve assembly process and assembly method

[0072] 1. During the assembly process, use the cockpit cover to operate the actuator Ω-shaped sealing ring installation device to press and fix the metal expansion ring:

[0073] See attached Figure 7 During assembly, first install the Ω-shaped sealing ring 18 with qualified size on the non-metallic expansion ring 19, and evenly distribute the Ω-shaped sealing ring 18; press the Ω-shaped sealing ring 18 and the non-metallic expansion ring 19 into the cover together, ensure that the fixed edge of one side of the Ω-shaped sealing ring 18 is embedded in the installation groove of the cover and evenly distributed, and then put the metal expansion ring 20 into the cover. Rotate the rotating handle 10 of the installation device to adjust the position of the support 8 so that the free ends of the three claws 2 are gathered together, and the free ends of the three claws 2 pass through the end cover of the cockpit cover operating cylinder, the non-metallic expansion ring 19 and the inner ring of the metal expansion ring 20, and place the retaining ring 3 against the outer side of the end cover, rotate the handle 10 to make the free ends of the three claws 2 away from each other, let the fixed sleeve 1 press the metal expansion ring 20, and continue to rotate the handle 10 to make the metal expansion ring 20 stably pressed. At this time, the metal expansion ring 20 is reliably pressed, and the end cover and the metal expansion ring 20 will not rotate relative to each other. Assemble it together with the cover to the outer cylinder and tighten it, and then install the piston rod.

[0074] 2. Add the actual immersion time record of the Ω-shaped sealing ring to ensure the qualified size:

[0075] Add the actual soaking time record of Ω-shaped sealing ring and expansion ring to ensure the accuracy of soaking time to control the size of rubber ring.

[0076] 3. Use an optical automatic image measuring instrument to measure the size of the Ω-shaped sealing ring and unify the measurement standards:

[0077] Use automatic image measuring instrument to measure the size of Ω-shaped sealing ring and expansion ring after immersion to ensure the accuracy of size measurement.

[0078] 4. Increase the inspection requirements for metal expansion rings and refine the surface quality inspection requirements:

[0079] Add surface quality inspection on the shoulder R0.1mm of the expansion ring to avoid assembly damage of the Ω-shaped sealing ring caused by sharp burrs on the shoulder.

[0080] 5. Add cleaning requirements for Ω-shaped sealing rings after soaking to prevent the rubber ring from continuing to expand after soaking:

[0081] Added cleaning requirements for Ω-shaped sealing rings after soaking in 7650 lubricant. They should be cleaned with anhydrous ethanol, and no residual 7650 lubricant is allowed. Avoid the rubber ring from continuing to expand under the influence of residual lubricant after soaking.

[0082] 6. Refine the assembly requirements of the piston rod and the end cover to ensure assembly safety:

[0083] Clarify the installation direction and improve it to use a clamp to fix the outer tube vertically.

[0084] Screw on the cover until it reaches the stop pin position (if a large torque change occurs during the process of screwing it to the stop pin position, it is not allowed to be screwed in forcefully and it should be disassembled and checked for any abnormalities).

[0085] 7. Add assembly inspection and pre-assembly of Ω-shaped sealing ring and expansion ring assembly to ensure assembly reliability:

[0086] Install an Ω-shaped sealing ring of qualified size on the expansion ring. Press it by hand to screw the side claws of the Ω-shaped sealing ring into the installation groove of the expansion ring.

[0087] Install the expansion ring, Ω-shaped sealing ring with expansion ring, shaft ring, Ω-shaped sealing ring in the cover, screw the cover to the stop pin position, and then disassemble the cover. After tightening and loosening three times, check that the Ω-shaped sealing ring is not damaged before assembling.

[0088] The method provided by the present invention includes using a cockpit cover operating cylinder Ω-shaped sealing ring installation device during assembly, adding a record of the actual immersion time of the Ω-shaped sealing ring, adding a failure inspection requirement for the metal expansion ring, measuring the size of the Ω-shaped sealing ring with an optical automatic image measuring instrument, adding a cleaning requirement for the Ω-shaped sealing ring after immersion, adding a failure inspection requirement for the metal expansion ring, and refining the assembly requirements for the piston rod and the end cover. It can effectively control the size of the Ω-shaped sealing ring to be in a qualified state, unify the measurement standard, refine the surface quality, ensure assembly reliability and safety, and provide a certain reference for improving the installation method of the sealing structure of similar products.

[0089] In this specification, each embodiment is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant parts can be referred to the method part.

[0090] The above description of the disclosed embodiments enables one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An Ω-shaped sealing ring installation device for an aircraft canopy operating cylinder, characterized in that: include: A support (8), wherein a threaded hole (11) is provided at the center of the support (8); A screw rod (9), the screw rod (9) being connected to the threaded hole (11), and having a handle (10) at one end, and a retaining ring (3) being rotatably connected at the other end of the screw rod (9), and having a plurality of radial notches (12) formed on the edge of the retaining ring (3); A pulling claw (2), the number of the pulling claws (2) is the same as the number of the slots (12), a plurality of the pulling claws (2) are arranged around the support (8), one end of the pulling claw (2) is hinged to the support (8), and the other end of the pulling claw (2) passes through the corresponding slot (12).

2. The aircraft canopy operating cylinder Ω-shaped sealing ring installation device according to claim 1, characterized in that: The end of the screw rod (9) away from the retaining ring (3) is provided with a handle plug (13), the handle plug (13) is provided with a socket (14), and the handle (10) is inserted into the socket (14).

3. The aircraft canopy operating cylinder Ω-shaped sealing ring installation device according to claim 2, characterized in that: The end of the screw rod (9) away from the handle plug (13) is provided with a connecting section (15) with a reduced diameter. The connecting section (15) is inserted into a rotating hole (16) opened in the middle of the retaining ring (3). A thrust ball bearing (6) is sleeved on the connecting section (15). The thrust ball bearing (6) is located between the stepped surface of the retaining ring (3) and the connecting section (15). A washer (4) corresponding to the rotating hole (16) is provided on the surface of the retaining ring (3) on one side away from the screw rod (9). The screw (5) passes through the washer (4) and is threadedly connected to the connecting section (15).

4. The aircraft canopy operating cylinder Ω-shaped sealing ring installation device according to claim 1, characterized in that: The support (8) has a U-shaped notch (17) on its edge, and one end of the pull claw (2) away from the retaining ring (3) is arranged in the U-shaped notch (17), and the pull claw (2) is hinged to the U-shaped notch (17) via a cylindrical pin (7).

5. The aircraft canopy operating cylinder Ω-shaped sealing ring installation device according to claim 4, characterized in that: The spacing between the plurality of pulling claws (2) gradually decreases from one end of the cylindrical pin (7) to the other end, and the end of the pulling claw (2) away from the retaining ring (3) is radially turned outward, and the turned-out part is sleeved with a fixing sleeve (1).

6. The aircraft canopy operating cylinder Ω-shaped sealing ring installation device according to claim 5, characterized in that: The fixing sleeve (1) is a rubber sleeve.

7. A method for installing an Ω-shaped sealing ring of an aircraft canopy operating cylinder, characterized in that: First, install the Ω-shaped sealing ring (18) on the non-metallic expansion ring (19), press the Ω-shaped sealing ring (18) and the non-metallic expansion ring (19) into the cover together, then put the metal expansion ring (20) into the cover, and use the aircraft cockpit cover operating cylinder Ω-shaped sealing ring installation device described in any one of claims 1 to 6 for installation, the metal expansion ring (20) is pressed, assembled together with the cover to the outer cylinder and tightened, and then the piston rod is installed.

8. The method for installing an Ω-shaped sealing ring of an aircraft canopy operating cylinder according to claim 7, characterized in that: When using the device, the handle (10) is rotated to adjust the position of the support (8) so that the free ends of the three pulling claws (2) are gathered together, and the free ends of the three pulling claws (2) are passed through the inner rings of the end cover of the cockpit cover operating cylinder, the non-metallic expansion ring (19) and the metal expansion ring (20), and the retaining ring (3) is pressed against the outer side of the end cover of the cockpit cover operating cylinder. The handle (10) is rotated to make the free ends of the three pulling claws (2) move away from each other, and the free ends of the pulling claws (2) press the metal expansion ring (20), and the handle (10) is continued to be rotated so that the metal expansion ring (20) is stably pressed.

9. The method for installing an Ω-shaped sealing ring of an aircraft canopy operating cylinder according to claim 7, characterized in that: During the installation of the Ω-shaped sealing ring (18) and the non-metallic expansion ring (19), it is ensured that the Ω-shaped sealing ring (18) is evenly distributed.

10. The method for installing an Ω-shaped sealing ring of an aircraft canopy operating cylinder according to claim 7, characterized in that: When the Ω-shaped sealing ring (18) and the non-metallic expansion ring (19) are pressed into the cover together, it is ensured that the fixed edge on one side of the Ω-shaped sealing ring (18) is embedded in the installation groove of the cover and is evenly distributed.

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