An aircraft canopy operating cylinder Ω-shaped sealing ring installation device and method

Abstract

This invention discloses an Ω-shaped sealing ring installation device and method for an aircraft cockpit canopy control actuator, relating to the field of aviation product repair technology. The device includes a support, a screw, and pull claws. The support has a threaded hole at its center. The screw connects to the threaded hole, and one end of the screw has a handle. The other end of the screw is rotatably connected to a retaining ring, which has multiple radial slots along its edge. Multiple pull claws are arranged around the support, with one end of each pull claw hinged to the support and the other end passing through a corresponding slot. First, the Ω-shaped sealing ring is installed on a non-metallic expansion ring. The Ω-shaped sealing ring and the non-metallic expansion ring are then pressed together into an end cap. Next, a metallic expansion ring is placed into the end cap, and the installation is performed using the aforementioned device. The metallic expansion ring is compressed and assembled with the end cap onto the outer cylinder, then tightened. Finally, the piston rod is installed. This invention enables quick, safe, and accurate installation of the Ω-shaped sealing ring, ensuring no assembly damage and guaranteeing the sealing performance of the cockpit canopy control actuator.

Description

Technical Field

[0001] This invention relates to the field of aviation product repair technology, and is used for the installation of Ω-shaped seals on aircraft cockpit canopy control actuator cylinders, and more specifically to an installation device and method for Ω-shaped seals on aircraft cockpit canopy control actuator cylinders. Background Technology

[0002] The cockpit canopy control actuator consists of a hydraulic chamber, a pneumatic chamber, and an elastic locking mechanism. It is an accessory of the aircraft cockpit canopy pneumatic system, used to operate the canopy's opening, closing, or any stroke. During the tightening and assembly process, the Ω-shaped sealing ring is prone to mechanical scratches at the root of the outer corner, which can then tear under overload.

[0003] During assembly, such as Figure 1 As shown, first, the Ω-shaped sealing ring is installed on the non-metallic expansion ring, and the Ω-shaped sealing ring is evenly distributed. Then, the Ω-shaped sealing ring and the non-metallic expansion ring are pressed into the end cap together, ensuring that one fixed edge of the Ω-shaped sealing ring is embedded in the mounting groove of the end cap and evenly distributed. Finally, the metal expansion ring is placed into the end cap and assembled onto the outer cylinder together with the end cap. In actual assembly, it is difficult to observe whether the Ω-shaped sealing ring is fully embedded in the groove of the metal expansion ring or whether the fixed edge is unevenly distributed in the groove. This may result in the fixed edge of the Ω-shaped sealing ring not being fully embedded in the groove of the metal expansion ring, or being unevenly distributed in the groove. The fixed edge of the Ω-shaped sealing ring contacts and presses against the shoulder of the groove of the metal expansion ring. During the subsequent tightening of the end cap, when the friction between the metal expansion ring and the cylinder is greater than the friction with the end cap, the metal expansion ring and the cylinder rotate together. When the end cap and the metal expansion ring undergo relative rotational displacement, the Ω-shaped sealing ring may be damaged or cut.

[0004] To address this issue, the Ω-shaped sealing ring and non-metallic expansion ring should be soaked in 7650 lubricant for 15–18 hours before assembly. After soaking, the diameter of the Ω-shaped sealing ring should be measured to be 48.5 mm–49.5 mm. However, during actual assembly, the Ω-shaped sealing ring expands excessively after soaking in lubricant. When installed into the end cap after being constrained by the non-metallic expansion ring, one fixed side of the Ω-shaped sealing ring is constrained by the end cap, while the other side is unconstrained. The outer diameter of the unconstrained fixed side exceeds the outer diameter of the metal expansion ring's mounting groove by a significant amount, preventing it from naturally entering the mounting groove under the pressure of the metal expansion ring and the end cap. Consequently, the Ω-shaped sealing ring is deformed. Furthermore, the shoulder of the metal expansion ring's groove causes relative displacement between the metal expansion ring and the Ω-shaped sealing ring during assembly and disassembly, resulting in scratches on the Ω-shaped sealing ring and overload cracking.

[0005] It is evident that the existing installation method cannot guarantee that the Ω-shaped sealing ring is sized correctly, cannot observe the state of the Ω-shaped sealing ring's fixed edge embedded in the metal expansion ring groove, and therefore cannot guarantee that it is fully embedded in the metal expansion ring groove and evenly distributed within it. It also makes it difficult to prevent the metal expansion ring from rotating with the cylinder. The installation process relies heavily on the experience and condition of the personnel, is inconvenient to operate, and cannot guarantee the stability and accuracy of the installation process.

[0006] Therefore, it is necessary to design a device that can reliably install Ω-shaped sealing rings, and correspondingly propose a method for reliably installing Ω-shaped sealing rings, so as to improve installation efficiency, reduce installation risks, reduce human operation errors, and solve potential 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 aircraft canopy control actuators, which enables rapid, safe, and accurate installation of the Ω-shaped sealing ring. The assembly process, tooling, and methods are formulated to ensure that the Ω-shaped sealing ring is not damaged during assembly, thus guaranteeing the sealing performance of the canopy control actuator.

[0008] To achieve the above objectives, the present invention adopts the following technical solution:

[0009] An Ω-shaped sealing ring mounting device for an aircraft cockpit canopy control actuator includes:

[0010] The support has a threaded hole at its center;

[0011] A screw rod is connected to the threaded hole, and one end of the screw rod has a handle. A retaining ring is rotatably connected to the other end of the screw rod, and the retaining ring has multiple radial slots along its edge.

[0012] Pull claws, the number of which is the same as the number of slots, are arranged around the support, one end of each pull claw is hinged to the support, and the other end of each pull claw passes through the corresponding slot.

[0013] Through the above technical solution, this invention adopts a structure including a handle, screw, support, retaining ring, and pull claw to solve the problem of difficulty in observing the state of the Ω-shaped sealing ring's fixed edge embedded in the metal expansion ring groove during assembly. This avoids the metal expansion ring rotating with the cylinder, prevents the Ω-shaped sealing ring from being crushed or cut, reduces assembly errors caused by difficulty in observing the assembly state, and avoids relative displacement between the metal expansion ring and the end cap. It also reduces the difficulty of manual installation, improves installation efficiency, and reduces production safety risks. It has certain innovative and practical application value and can provide some reference for the installation of sealing structures in similar products.

[0014] Preferably, in the above-mentioned aircraft cockpit canopy control actuator Ω-shaped sealing ring installation device, the end of the screw away from the retaining ring has a handle plug, the handle plug has a socket, and the handle is inserted into the socket. The use of a spiral handle allows for quick and accurate adjustment of the position and opening angle of the pull claw, facilitating operation and improving work efficiency.

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

[0016] Preferably, in the above-mentioned aircraft cockpit canopy control actuator Ω-shaped sealing ring installation device, the support edge has a U-shaped groove, the end of the pull claw away from the retaining ring is disposed in the U-shaped groove, and the pull claw and the U-shaped groove are hinged by a cylindrical pin.

[0017] Preferably, in the above-mentioned aircraft cockpit canopy operating actuator Ω-shaped sealing ring installation device, the spacing between the plurality of pull claws gradually decreases from one end of the cylindrical pin to the other end, and the end of the pull claw away from the retaining ring is radially outward, and the outwardly outward portion is fitted with a fixing sleeve. 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 cockpit canopy operating actuator Ω-shaped sealing ring mounting device, the fixing sleeve is a rubber sleeve. The fixing sleeve structure at the end of the pull claw can reliably press and fix the metal expansion ring without damaging it.

[0019] The present invention also provides a method for installing an Ω-shaped sealing ring on an aircraft cockpit canopy control actuator cylinder. First, the Ω-shaped sealing ring is installed on a non-metallic expansion ring. The Ω-shaped sealing ring and the non-metallic expansion ring are pressed together into the end cover. Then, a metallic expansion ring is placed into the end cover. The above-mentioned aircraft cockpit canopy control actuator cylinder Ω-shaped sealing ring installation device is used for installation. The metallic expansion ring is pressed tightly and assembled with the end cover onto the outer cylinder and tightened. Finally, the piston rod is installed.

[0020] Preferably, in the above-mentioned method for installing the Ω-shaped sealing ring of the aircraft canopy operating actuator, when using the device, the position of the support is adjusted by rotating the handle so that the free ends of the three claws meet, allowing the free ends of the three claws to pass through the inner ring of the canopy operating actuator end cover, the non-metallic expansion ring, and the metal expansion ring, and the retaining ring is pressed against the outside of the canopy operating actuator end cover. The handle is rotated so that the free ends of the three claws move away from each other, allowing the fixing sleeve to press against 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 the Ω-shaped seal ring of the aircraft cockpit canopy control actuator, the Ω-shaped seal ring is evenly distributed during the installation process of the non-metallic expansion ring.

[0022] Preferably, in the above-mentioned method for installing the Ω-shaped sealing ring of the aircraft cockpit canopy operating actuator, during the process of pressing the Ω-shaped sealing ring and the non-metallic expansion ring into the end cover, it is ensured that one fixed edge of the Ω-shaped sealing ring is embedded in the mounting groove of the end cover and is evenly distributed.

[0023] As can be seen from the above technical solution, compared with the prior art, the present invention discloses an Ω-shaped sealing ring installation device and method for aircraft cockpit canopy operating actuator cylinder, which has the following beneficial effects:

[0024] This invention improves installation efficiency: through the cooperation of the handle, screw, support, retaining ring, and pull claw, rotating the handle allows for quick and accurate adjustment of the position and opening angle of the pull claw. This enables the free end of the pull claw to rapidly pass through the cockpit canopy actuator end cap, the inner ring of the non-metallic expansion ring, and the metal expansion ring, while the retaining ring abuts against the outer side of the cockpit canopy actuator end cap, thus achieving rapid clamping and fixing of the metal expansion ring. This significantly shortens the adjustment time before installation and improves the overall installation efficiency. Compared with traditional installation methods, the device and method of this invention simplify multiple steps in the assembly process, avoiding repeated adjustments and checks due to insufficient personnel experience or improper operation, making the entire installation process smoother and more convenient, further improving installation efficiency.

[0025] This invention reduces installation risks: during installation, it effectively prevents the Ω-shaped sealing ring from being damaged or cut due to the metal expansion ring rotating with the cylinder. The stable clamping action of the pull claw and the fixing sleeve ensures that the metal expansion ring does not rotate relative to the end cap during assembly, thus protecting the Ω-shaped sealing ring from damage, guaranteeing its integrity and sealing performance, and reducing potential risks caused by seal ring damage. The device's structural design and operation method are simple and easy to master, reducing reliance on operator experience and skill levels, lowering assembly errors and safety hazards caused by improper operation or mistakes, and improving the stability and reliability of the installation process.

[0026] This invention improves installation quality by precisely controlling the soaking time of the Ω-shaped sealing ring and using an optical automatic image measuring instrument for dimensional measurement. This allows for accurate monitoring of the sealing ring's dimensional changes, ensuring it matches the dimensions of the metal expansion ring groove during installation. This ensures the Ω-shaped sealing ring is fully embedded in the groove and evenly distributed within it, thus improving installation quality and enhancing the sealing performance of the cockpit canopy control actuator. The invention also incorporates additional steps, including surface quality inspection of the metal expansion ring, cleaning the Ω-shaped sealing ring after soaking, refined requirements for the assembly of the piston rod and end cap, and assembly inspection and pre-assembly of the Ω-shaped sealing ring assembly. These multiple aspects of rigorous control over the assembly process further guarantee reliability and safety, improving the overall product quality. Attached Figure Description

[0027] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

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

[0029] Figure 2 The attached figure is a structural schematic diagram of the Ω-shaped sealing ring mounting device for the aircraft cockpit canopy control actuator provided by the present invention;

[0030] Figure 3 The attached figure is a structural schematic diagram of the Ω-shaped sealing ring mounting device for the aircraft cockpit canopy control actuator provided by the present invention, viewed from below.

[0031] Figure 4 The attached figure is a schematic diagram of the screw provided by the present invention;

[0032] Figure 5 The attached figure is a schematic diagram of the connection between the support and the pull claw provided by the present invention;

[0033] Figure 6 The attached figure is a schematic diagram of the retaining ring provided by the present invention;

[0034] Figure 7 The attached figure is a schematic diagram of the use of the Ω-shaped sealing ring installation device for the aircraft cockpit canopy control actuator provided by the present invention;

[0035] Figure 8 The attached figure shows the relationship between the inner diameter of the Ω-shaped sealing ring provided by the present invention and the total soaking time.

[0036] in:

[0037] 1-Fixing sleeve; 2-Pull 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-Socket; 15-Connecting section; 16-Rotating hole; 17-U-shaped slot; 18-Ω-shaped sealing ring; 19-Non-metallic expansion ring; 20-Metallic expansion ring. Detailed Implementation

[0038] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. 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 making creative efforts are within the scope of protection of the present invention.

[0039] This embodiment provides an Ω-shaped sealing ring installation device and method for aircraft cockpit canopy control actuators. The main components include designing and manufacturing installation and fixing fixtures, determining the installation method, adding actual immersion time recording for the Ω-shaped sealing ring, measuring the Ω-shaped sealing ring dimensions using an optical automatic image measuring instrument, adding fault inspection requirements for the metal expansion ring, adding cleaning requirements after immersion of the Ω-shaped sealing ring, refining the assembly requirements for the piston rod and end cap, and adding assembly inspection and pre-assembly of the Ω-shaped sealing ring and expansion ring assembly to ensure the final assembly quality of the Ω-shaped sealing ring.

[0040] This mainly includes statistical analysis of product failures, theoretical calculation of sealing ring installation dimensions, verification of sealing ring dimension variation gauges, design and application of installation devices, improvement of assembly processes and methods, ensuring structural application, and guaranteeing the final assembly quality of the Ω-shaped sealing ring.

[0041] Step 1: Fault Statistical Analysis

[0042] Comparative analysis revealed that the damage to the cockpit canopy control actuator was located at the mating point between the pneumatic chamber end cap and the metal expansion ring. The size of the sealing ring after the original machine was disassembled at the factory was smaller than the size requirement after immersion during assembly (which is a normal dimensional change of rubber parts after long-term operation). The inner diameter of the damaged sealing ring after disassembly at the factory was relatively larger than the inner diameter of the undamaged sealing ring.

[0043] The main cause of the malfunction is the mismatch between the mounting groove and the sealing size, which results in the Ω-shaped sealing ring's fixing edge not being fully embedded in the metal expansion ring groove or being unevenly distributed within the metal expansion ring groove. The fixing edge of the Ω-shaped sealing ring contacts and presses against the shoulder of the metal expansion ring groove. During the subsequent tightening of the end cap, when the friction between the metal expansion ring and the cylinder is greater than the friction with the end cap, the metal expansion ring and the cylinder rotate together. When the end cap and the metal expansion ring undergo relative rotational displacement, the Ω-shaped sealing ring may be damaged or cut.

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

[0045] The outer diameter of the sealing ring, after being enlarged proportionally and immersed in oil, is approximately (55.16~58.14) mm. In its free state, the outer diameter of the sealing ring exceeds the outer diameter of the metal expansion ring mounting groove.

[0046] After the sealing ring is constrained by the non-metallic expansion ring, the change in outer diameter mainly occurs in the unconstrained areas. Proportionally scaling up the calculations for the unconstrained areas (2.5 mm to 2.8 mm on each side), the change in the outer diameter of the sealing ring on each side is (2.66 to 3.08) mm. The diameter change is (0.32 to 1.16) mm, meaning the outer diameter range is (52.07 to 53.96) mm. This does not perfectly match the designed outer diameter of the mounting groove, Φ53 + 0.46 mm.

[0047] Comparing the installation dimensions of the metal expansion ring mounting groove and the sealing ring, when the outer diameter of the metal expansion ring mounting groove is at the lower limit of the dimension drawing (Φ53): the installation dimension overlap rate is 49%, and there is a 51% probability that the outer diameter of the sealing ring exceeds the outer diameter of the metal expansion ring mounting groove; when the outer diameter of the metal expansion ring mounting groove is at the upper limit of the dimension drawing (Φ53.46): the installation dimension overlap rate is 74%, and there is a 26% probability that the outer diameter of the sealing ring exceeds the outer diameter of the metal expansion ring mounting groove. In other words, the dimension overlap rate during sealing ring installation is 49%–74%, and there is a 26%–51% probability that the outer diameter will exceed the size of the metal expansion ring mounting groove.

[0048] Step 3: Verification of the sealing ring size variation pattern

[0049] 1. Verification of dimensional changes in sealing rings after soaking in 7650 grease

[0050] Combination Figure 8 Five sealing rings were selected for immersion dimensional change analysis. The results showed that the dimensional changes of the sealing rings after immersion were mainly related to the immersion time. Other liquid media, the state of the lubricant, and residual media on the surface of the sealing rings also had some influence on the dimensional changes. Generally, immersion of no more than 24 hours will not exceed the specified dimensional range.

[0051] Different immersion methods for sealing rings affect verification

[0052] Table 1 Results of the trend of seal ring changes

[0053]

[0054] The diameter of component ① remained basically unchanged, indicating that the diameter of the sealing ring remained basically unchanged when placed in the air.

[0055] The fact that the diameter of part ② increases slowly over time indicates that the sealing ring coated with 132-25 precision instrument oil will slowly increase in size when placed in the air.

[0056] ③ The diameter of part number 3 decreased significantly over time, indicating that the sealing ring would shrink significantly when immersed in 132-25 precision instrument oil;

[0057] The diameter of part ④ increased after being placed for 24 hours, and remained basically unchanged thereafter. This is because the residual 7650 lubricant was basically absorbed by the sealing ring. At this time, part ④ was in the same state as part ①, and the sealing ring no longer increased in size.

[0058] Verification through different soaking 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 soaked and the size is qualified, it needs to be cleaned and dried to avoid the influence of residual medium on the sealing ring.

[0059] The soaking time for the sealing rings needs to be carefully controlled to avoid dimensional errors and scrap due to excessive soaking time. Contact with other non-working media should also be avoided.

[0060] Step Four: Installation Device Design and Application

[0061] See appendix Figure 2 To be continued Figure 6 This embodiment discloses an Ω-shaped sealing ring mounting device for an aircraft cockpit canopy control actuator, comprising:

[0062] Support 8, with a threaded hole 11 at its center;

[0063] The screw 9 is connected to the threaded hole 11, and one end of the screw 9 has a handle 10. The other end of the screw 9 is rotatably connected to a retaining ring 3, and the retaining ring 3 has multiple radial slots 12 on its edge.

[0064] Pull claw 2, the number of pull claw 2 is the same as the number of slots 12, multiple pull claw 2 are arranged around the support 8, one end of pull claw 2 is hinged to the support 8, and the other end of pull claw 2 passes through the corresponding slot 12.

[0065] To further optimize the above technical solution, the end of the screw 9 away from the retaining ring 3 has a handle plug 13, and the handle plug 13 has a socket 14. The handle 10 is inserted into the socket 14. It is fixed by a movable shaft connection, which allows the lever arm length of the handle 10 to be changed at any time.

[0066] 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 the rotating hole 16 opened in the middle of the retaining ring 3. A thrust ball bearing 6 is fitted 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 side surface of the retaining ring 3 away from the screw 9. The screw 5 passes through the washer 4 and is threadedly connected to the connecting section 15.

[0067] To further optimize the above technical solution, the support 8 has a U-shaped groove 17 on its edge, and the end of the pull claw 2 away from the retaining ring 3 is located in the U-shaped groove 17. The pull claw 2 and the U-shaped groove 17 are hinged by a cylindrical pin 7.

[0068] To further optimize the above technical solution, the spacing between the multiple pull claws 2 gradually decreases from one end of the cylindrical pin 7 to the other end, and the end of the pull claw 2 away from the retaining ring 3 is radially outward, and the outward part is fitted with a fixing sleeve 1.

[0069] To further optimize the above technical solution, the fixing sleeve 1 is a rubber sleeve.

[0070] Step 5: Improve assembly processes and methods

[0071] 1. During assembly, use the cockpit canopy operating actuator Ω-shaped seal ring installation device to tighten and fix the metal expansion ring:

[0072] See appendix Figure 7 During assembly, first, install the Ω-shaped sealing ring 18 of the correct size onto the non-metallic expansion ring 19, and distribute the Ω-shaped sealing ring 18 evenly. Press the Ω-shaped sealing ring 18 and the non-metallic expansion ring 19 together into the end cover, ensuring that one fixed edge of the Ω-shaped sealing ring 18 is embedded in the mounting groove of the end cover and evenly distributed. Then, place the metal expansion ring 20 into the end cover. Rotate the rotating handle 10 of the mounting device to adjust the position of the support 8 so that the free ends of the three pull claws 2 converge, allowing the free ends of the three pull claws 2 to pass through the inner rings of the cockpit cover operating actuator cylinder end cover, the non-metallic expansion ring 19, and the metal expansion ring 20, and place the retaining ring 3 against the outside of the end cover. Rotate the handle 10 to move the free ends of the three pull claws 2 away from each other, allowing the fixing sleeve 1 to press against the metal expansion ring 20. Continue to rotate the handle 10 to stably press the metal expansion ring 20. 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 end cover onto the outer cylinder and tighten the assembly, and then install the piston rod.

[0073] 2. Add a record of the actual soaking time of the Ω-shaped sealing ring to ensure qualified dimensions:

[0074] Record the actual soaking time of the Ω-shaped sealing ring and expansion ring. Ensure the accuracy of the soaking time to control the ring size.

[0075] 3. Use an optical automatic image measuring instrument to measure the size of the Ω-shaped sealing ring, and standardize the measurement:

[0076] The Ω-shaped sealing rings and expansion rings were measured after immersion using an automatic image measuring instrument to ensure the accuracy of the dimensional measurements.

[0077] 4. Increase the failure inspection requirements for metal expansion rings and refine the surface quality inspection requirements:

[0078] Increase the surface quality inspection of the shoulder R0.1mm of the expansion ring to avoid damage to the Ω-shaped seal ring assembly caused by sharp burrs on the shoulder.

[0079] 5. Increase the cleaning requirements after soaking the Ω-shaped sealing ring to prevent the ring from continuing to expand after soaking stops:

[0080] The cleaning requirements for Ω-shaped sealing rings after soaking in 7650 lubricant have been increased. They should be thoroughly cleaned with anhydrous ethanol, and no 7650 lubricant residue is allowed. This is to prevent the sealing ring from continuing to expand due to residual lubricant after soaking has stopped.

[0081] 6. Refine the assembly requirements for the piston rod and end cap to ensure assembly safety:

[0082] The installation direction was clarified, and the method was improved by using clamps to vertically fix the outer cylinder for installation.

[0083] Tighten the end cap to the stop pin position (if a large torque change occurs during the tightening process, do not force it in; disassemble and check for any abnormalities).

[0084] 7. Increase assembly inspection and pre-assembly of the Ω-shaped sealing ring and expansion ring assembly to ensure assembly reliability:

[0085] Add a properly sized Ω-shaped sealing ring to the expansion ring, and press it by hand to screw the side claws of the Ω-shaped sealing ring into the mounting groove of the expansion ring.

[0086] Install the expansion ring, the Ω-shaped seal with the expansion ring, the shaft ring, and the Ω-shaped seal inside the end cover. Tighten the end cover to the position of the stop pin, and then disassemble the end cover. After tightening and loosening three times, check that the Ω-shaped seal is undamaged before reassembling.

[0087] The method provided by this invention includes using an Ω-shaped sealing ring installation device for the cockpit canopy operating actuator during assembly, adding recording of the actual immersion time of the Ω-shaped sealing ring, adding fault inspection requirements for the metal expansion ring, measuring the size of the Ω-shaped sealing ring with an optical automatic image measuring instrument, adding cleaning requirements after immersion of the Ω-shaped sealing ring, adding fault inspection requirements for the metal expansion ring, and refining the assembly requirements for the piston rod and end cap. This method can effectively control the size of the Ω-shaped sealing ring to be within acceptable limits, standardize measurement, refine surface quality, and ensure assembly reliability and safety. It can provide a reference for improving the sealing structure installation method of similar products.

[0088] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to the method section.

[0089] The above description of the disclosed embodiments is intended to enable one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily 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 is not limited to the embodiments shown herein but is intended to conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A method for installing an Ω-shaped sealing ring on an aircraft cockpit canopy control actuator, 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) together into the end cover, then put the metal expansion ring (20) into the end cover, and install it using the aircraft cockpit canopy operating actuator Ω-shaped sealing ring installation device. The metal expansion ring (20) is pressed tight and assembled with the end cover onto the outer cylinder and tightened. Through the stable pressing action of the aircraft cockpit canopy operating actuator Ω-shaped sealing ring installation device, it is ensured that the metal expansion ring (20) will not rotate relative to the end cover during the assembly process, and then install the piston rod. The aircraft cockpit canopy control actuator Ω-shaped sealing ring mounting device includes: Support (8), the support (8) has a threaded hole (11) at its center; A screw (9) is connected to the threaded hole (11), and one end of the screw (9) has a handle (10), and the other end of the screw (9) is rotatably connected to a retaining ring (3), and the retaining ring (3) has multiple radial slots (12) on its edge. Pull claws (2), the number of pull claws (2) is the same as the number of slots (12), multiple pull claws (2) are arranged around the support (8), and one end of the pull claws (2) is hinged to the support (8), and the other end of the pull claws (2) passes through the corresponding slots (12). The screw (9) has a handle plug (13) at one end away from the retaining ring (3), and the handle plug (13) has a socket (14), into which the handle (10) is inserted. The screw (9) has a connecting section (15) with a reduced diameter at one end away from the handle plug (13). The connecting section (15) is inserted into the rotating hole (16) in the middle of the retaining ring (3). A thrust ball bearing (6) is fitted on the connecting section (15). The thrust ball bearing (6) is located between the stepped surfaces of the retaining ring (3) and the connecting section (15). A washer (4) corresponding to the rotating hole (16) is provided on the side surface of the retaining ring (3) away from the screw (9). The screw (5) passes through the washer (4) and is threaded to the connecting section (15). The support (8) has a U-shaped groove (17) on its edge. The end of the pull claw (2) away from the retaining ring (3) is located in the U-shaped groove (17). The pull claw (2) and the U-shaped groove (17) are hinged by a cylindrical pin (7). The distance between the multiple pull claws (2) gradually decreases from one end of the cylindrical pin (7) to the other end, and the pull claws (2) are radially outward at the end away from the retaining ring (3), and the outwardly outward part is fitted with a fixing sleeve (1).

2. The method for installing an Ω-shaped sealing ring on an aircraft cockpit canopy control actuator according to claim 1, characterized in that, When using the device, rotate the handle (10) to adjust the position of the support (8) so that the free ends of the three claws (2) come together, and let the free ends of the three claws (2) pass through the inner ring of the canopy control actuator end cap, the non-metallic expansion ring (19) and the metal expansion ring (20), and put the retaining ring (3) against the outside of the canopy control actuator end cap. Rotate the handle (10) so that the free ends of the three claws (2) move away from each other, and let the free ends of the claws (2) press against the metal expansion ring (20). Continue to rotate the handle (10) so that the metal expansion ring (20) is stably pressed.

3. The method for installing an Ω-shaped sealing ring on an aircraft cockpit canopy control actuator according to claim 1, characterized in that, During the installation of the Ω-shaped sealing ring (18) and the non-metallic expansion ring (19), ensure that the Ω-shaped sealing ring (18) is evenly distributed.

4. The method for installing an Ω-shaped sealing ring on an aircraft cockpit canopy control actuator according to claim 1, characterized in that, During the process of pressing the Ω-shaped sealing ring (18) and the non-metallic expansion ring (19) into the end cap, it is ensured that one fixed edge of the Ω-shaped sealing ring (18) is embedded in the mounting groove of the end cap and is evenly distributed.

5. The method for installing an Ω-shaped sealing ring on an aircraft cockpit canopy control actuator according to claim 1, characterized in that, The fixing sleeve (1) is a rubber sleeve.

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