Air pressure unlocking device and unlocking method for spaceflight hydraulic damper

Abstract

The embodiment of the invention discloses an air pressure unlocking device and unlocking method for a spaceflight hydraulic damper, in the device, a locking claw of an air pressure lock mechanism arranged in the spaceflight hydraulic damper is fixedly installed at the end of a piston rod, and under pulling of stretching movement of the piston rod, the end of the claw is clamped at the stop end of a spring lock seat assembly to achieve locking; an unlocking cavity is formed between the spring lock seat assembly and the outer cylinder; in the air pressure unlocking assembly, an air pump, an air storage tank and a valve block assembly are sequentially connected, the valve block assembly is connected to an unlocking cavity of the outer cylinder through an air pipe, a pressure regulating valve assembly, a pressure gauge and a pressure relief assembly are installed on the valve block assembly, and the pressure regulating valve assembly is used for regulating air supply pressure supplied to the spaceflight hydraulic damper and closing air supply. The air supply pressure supplied to the spaceflight hydraulic damper is measured through the pressure gauge, air is supplied to the unlocking cavity of the spaceflight hydraulic damper to unlock the lock mechanism, and then the pressure in the valve block assembly is discharged through the pressure relief assembly.

Description

Technical Field

[0001] This invention relates to, but is not limited to, the field of pneumatic unlocking technology for aerospace hydraulic dampers, and particularly to a pneumatic unlocking device and unlocking method for aerospace hydraulic dampers. Background Technology

[0002] The aerospace hydraulic dampers are part of the escape and rescue system in the Shenzhou series manned spacecraft. In the event of an emergency, the escape and rescue system activates, requiring all aerospace hydraulic dampers to engage simultaneously to support the deceleration system and lock in place, ensuring the spacecraft's deceleration requirements during descent. After the mission, the locked aerospace hydraulic dampers must be unlocked promptly to allow for reuse. Furthermore, the aerospace hydraulic dampers undergo repeated locking and unlocking tests at the factory to verify that their performance meets the required specifications.

[0003] Currently, unlocking devices for actuators used in other technological fields typically employ mechanical structures for unlocking. These are manual unlocking methods, involving mechanical disassembly for unlocking, which is complex and requires the removal of numerous parts, making them prone to loss or damage. Furthermore, the need for repeated assembly in existing unlocking devices leads to wear and tear on parts, resulting in decreased overall device accuracy, poor sealing, and failure to meet intended functional requirements. Summary of the Invention

[0004] The purpose of this invention is to solve the above-mentioned technical problems. This invention provides a pneumatic unlocking device and unlocking method for aerospace hydraulic dampers. This solves the problems of existing actuator unlocking devices having complex mechanical unlocking methods and requiring the disassembly of many parts, which can easily lead to the loss or damage of parts. It also solves the problems of existing devices having reduced overall device accuracy and poor sealing due to repeated assembly causing wear of parts.

[0005] The technical solution of the present invention: In a first aspect, the present invention provides a pneumatic unlocking device for an aerospace hydraulic damper, comprising: a pneumatic lock mechanism disposed inside the aerospace hydraulic damper, and a pneumatic unlocking assembly communicating with the unlocking chamber of the outer cylinder 19 of the aerospace hydraulic damper; In the pneumatic lock mechanism of the aerospace hydraulic damper, the locking claw 17 is fixedly installed in the annular groove formed by the piston rod 18 and the end face piston 15. Under the pull of the piston rod 18 extending, the claw end of the locking claw 17 engages with the stop end of the spring lock seat assembly installed at the end of the damper in the position, so that the claw end and the outer cylinder 19 of the damper form a limiting structure in the engaged state; and an unlocking cavity is formed between the spring lock seat assembly and the outer cylinder 19 of the aerospace hydraulic damper, and an unlocking port for connecting the unlocking cavity and the pneumatic unlocking assembly is provided on the outer cylinder 19; The pneumatic unlocking assembly includes: The air pump 1, air tank 3, and valve block assembly are connected in sequence through the air pipe 8. The valve block assembly is connected to the unlocking port of the outer cylinder 19 of the aerospace hydraulic damper through the air pipe 8. The valve block assembly is equipped with a pressure regulating valve assembly 11, a pressure gauge 10, and a pressure relief assembly. The pressure regulating valve assembly 11 is used to regulate the air supply pressure to the aerospace hydraulic damper and to shut off the air supply. The pressure gauge 10 is used to measure the air supply pressure to the aerospace hydraulic damper. After the locking mechanism is unlocked by supplying air to the unlocking chamber of the aerospace hydraulic damper, the pressure inside the valve block assembly is discharged through the pressure relief assembly.

[0006] Optionally, the pneumatic unlocking device in the above-described pneumatic unlocking device for aerospace hydraulic dampers is used to provide gas at a preset pressure to the unlocking chamber of the aerospace hydraulic damper through the pneumatic unlocking assembly, so as to push the spring lock seat assembly to move away from the lock claw 17 through the gas pressure in the unlocking chamber, and disengage from the lock claw 17 through the movement of the spring lock seat assembly, thereby realizing the pneumatic unlocking of the locking mechanism.

[0007] Optionally, in the pneumatic unlocking device for an aerospace hydraulic damper as described above, the pneumatic locking mechanism inside the aerospace hydraulic damper includes: an end nut 14, a piston 15, a locking claw 17, a piston rod 18, an outer cylinder 19, an end cap nut 23, and a spring lock seat assembly. The outer cylinder 19 has a spring lock seat assembly installed in the end cavity. The piston rod 18 passes through the central hole of the spring lock seat assembly and can move relative to it along the axial direction of the spring lock seat assembly. The spring lock seat assembly in the outer cylinder 19 is fixedly installed by the end cap nut 23. The piston rod 18 is fitted with a piston 15 at the end inside the outer cylinder 19. An annular groove is formed between the piston 15 and the shoulder at the front of the piston rod 18. The locking claw 17 is fixedly installed on the annular groove by its fixed end, so that the claw end of the locking claw 17 is located on the side facing the protruding end of the spring lock seat assembly. The piston 15 and the locking claw 17 are locked and fixed by the end nut 14 screwed to the end of the piston rod 18. The inner wall of the outer cylinder 19 is provided with an annular limiting boss, which is used to axially limit the stop piston 20 passing through the annular limiting boss in the spring lock seat assembly. This allows the stop piston 20 to abut against the limiting boss under the action of the spring 21 inside the spring lock seat assembly, and the stop end of the stop piston 20 to be limited to a position for locking with the claw end of the lock claw 17 after passing through the limiting boss.

[0008] Optionally, in the pneumatic unlocking device for an aerospace hydraulic damper as described above, the spring lock seat assembly includes: a stop piston 20, a spring 21, an oil scraper ring 22, and a retaining ring 24. The stop piston 20, the oil scraper ring 22 and the retaining ring 24 are sequentially sleeved on the piston rod 18, and the end cap nut 23 screwed onto the outer cylinder 19 abuts against and fixes the axial position of the oil scraper ring 22. The stop piston 20 is sleeved on the oil scraper ring 22 through the sleeve facing the end of the stop piston 20, and a spring 21 is sleeved between the stop piston 20 and the oil scraper ring 22. Under the action of the spring force of the spring 21, the stop piston 20 has its stop end facing the lock claw 17 pass through and extend inward into the annular limiting boss of the outer cylinder 19, and presses against the annular limiting boss through its stepped end face. An unlocking cavity acting on the pneumatic lock mechanism is formed between the stop piston 20 and the annular limiting boss of the outer cylinder 19.

[0009] Optionally, in the pneumatic unlocking device for an aerospace hydraulic damper as described above, the valve block assembly includes: a valve block 5 and a plurality of screw plugs 13; The valve block 5 is provided with a pressure regulating valve assembly interface, an air tank interface, a pressure pipe interface, an air pipe interface, and a pressure relief interface; multiple valve body pipelines are provided inside the valve block 5, which are used to connect the pressure regulating valve assembly interface with the air tank interface, the pressure pipe interface, the air pipe interface, and the pressure relief interface respectively; the valve block 5 is also provided with multiple process holes for forming the internal pipeline connection structure, and each process hole is sealed by a screw plug 13.

[0010] Optionally, in the pneumatic unlocking device for aerospace hydraulic dampers as described above, the pneumatic unlocking assembly further includes: an air pump adapter 2, an air tank adapter 4, an adapter 6, a pipeline ball valve 7a, an unlocking port adapter 9, and a pressure gauge adapter 12; the pressure relief assembly is configured as a pressure relief ball valve 7b. The output pipeline of the air pump 1 is connected to the input interface of the air tank 3 through the air pump adapter 2. The output interface of the air tank 3 is connected to the air tank interface on the valve block 5 through the air tank adapter 4. The valve block 5 is equipped with the pressure regulating valve assembly 11 through the pressure regulating valve assembly interface and the pressure gauge 10 through the pressure pipe interface. The pressure relief interface of the valve block 5 is connected to the pressure relief ball valve 7b through an adapter 6. Its air pipe interface is connected to the rear air pipe 8 through another adapter 6. The end of the rear air pipe 8 is connected to the front end of the pipeline ball valve 7a. The rear end of the pipeline ball valve 7a is connected to the unlocking port of the aerospace hydraulic damper through the unlocking port adapter 9, thereby connecting to the unlocking chamber of the pneumatic lock mechanism set inside the aerospace hydraulic damper.

[0011] Optionally, in the pneumatic unlocking device for aerospace hydraulic dampers as described above, the pressure regulating valve assembly 11 includes: a nylon washer 11.1, a valve core sealing ring 11.2, a valve core 11.3, a nut 11.4, a handle 11.5, a fixing screw 11.6, and a valve sleeve 11.7. The nylon gasket 11.1 is fixedly installed at the front end of the valve sleeve 11.7, and the valve core 11.3 is screwed into the valve sleeve 11.7 with its central thread structure. The front part of the valve core 11.3 is configured as a combination structure of a sealing column and a cone front end. Two valve core sealing rings 11.2 are installed between the outer wall of the sealing column at the front of the valve core 11.3 and the valve sleeve 11.7. The cone front end of the valve core 11.3 is embedded in the nylon gasket 11.1 at the front end of the valve sleeve 11.7, thereby achieving end sealing. The handle 11.5 is fixedly installed at the end of the valve core 11.3 by a fixing screw 11.6, and is used to control the axial movement of the valve core 11.3 inside the valve sleeve 11.7 by rotating the handle 11.5; a nut 11.4 is installed on the rod of the valve core 11.3 located between the handle and the valve sleeve 11.7, and is used to fix and lock the valve core 11.3 after adjusting the relative position of the valve core 11.3 and the valve sleeve 11.7 by the handle 11.5.

[0012] Optionally, in the pneumatic unlocking device for aerospace hydraulic dampers as described above, the pressure regulating valve assembly 11 further includes: a valve sleeve sealing ring 11.8 and a locking nut 11.9; The valve sleeve 11.7 is embedded in the valve block 5 with its external thread structure and is fixed by a locking nut 11.9 fitted on the valve sleeve 11.7. The locking nut 11.9 is screwed into the valve block 5 with its external thread structure and presses the valve sleeve 11.7 into the valve body 5 with its inner end face, so as to ensure that the valve sleeve 11.7 is always fixed inside the valve body 5 when adjusting the relative position of the valve core 11.3 and the valve sleeve 11.7. The pressure regulating valve assembly 11 is provided with multiple sealing structures, namely: The first sealing structure is formed by tightening the nylon gasket 11.1 at the front end of the valve sleeve 11.7; a valve sleeve sealing ring 11.8 is installed on the outer periphery of the valve sleeve 11.7 to form the second sealing structure; the first sealing structure and the second sealing structure are used to prevent gas in the gas storage tank 3 from entering the valve block 5 and then leaking from the outside of the valve sleeve 11.7.

[0013] Secondly, embodiments of the present invention also provide a pneumatic unlocking method for an aerospace hydraulic damper, wherein the aerospace hydraulic damper is equipped with a pneumatic unlocking device for an aerospace hydraulic damper as described in any of the above claims, and the pneumatic unlocking method implemented by the pneumatic unlocking device includes: Step 1: Place the locked aerospace hydraulic damper horizontally, install the unlocking port adapter 9 onto the unlocking port of the outer cylinder 19 of the aerospace hydraulic damper, and connect the air pipe 8 at the rear end of the pneumatic unlocking component through the lock port adapter 9 to connect the pneumatic unlocking component with the unlocking chamber of the pneumatic lock mechanism inside the aerospace hydraulic damper. Step 2: For the assembled pneumatic unlocking assembly, close the pipeline ball valve 7a and the pressure relief ball valve 7b on the pneumatic unlocking assembly, turn on the air pump 1, and the air pump 1 inputs gas into the valve block 5 through the air storage tank 3. After the gas pressure in the valve block 5 reaches the unlocking pressure of the pneumatic lock mechanism in the aerospace hydraulic damper, open the pipeline ball valve 7a connected to the unlocking port of the aerospace hydraulic damper. Step 3, supplying unlocking gas to the aerospace hydraulic damper through the pressure regulating valve assembly 11, includes: opening and closing the pressure regulating valve assembly 11, so that after the valve core 11.3 moves under the turning of the handle 11.5, the gas flows through the air hole between the valve core 11.3 and the valve sleeve 11.7 to the pressure gauge 10, and is supplied to the unlocking chamber of the aerospace hydraulic damper through the air pipe 8 and the pipeline ball valve 7a; under the action of gas pressure, the locking claw 17 inside the aerospace hydraulic damper is opened, thereby unlocking.

[0014] Optionally, the pneumatic unlocking method for an aerospace hydraulic damper described above further includes: Step 4: When the piston rod 18 of the aerospace hydraulic damper begins to retract slowly, close the pressure regulating valve assembly 11 so that the pneumatic unlocking assembly stops supplying air to the pneumatic lock mechanism. Read the pressure value displayed on the pressure gauge 10 on the valve block 5. The read pressure value is the unlocking pressure value set by the aerospace hydraulic damper. Step 5: After the aerospace hydraulic damper is successfully unlocked, open the pressure relief ball valve 7b on valve block 5 to release the high-pressure gas inside the aerospace hydraulic damper through the pressure relief ball valve 7b on valve block 5; and continue to manually compress the piston rod 18 of the aerospace hydraulic damper until the piston rod 18 is completely retracted.

[0015] The beneficial effects of the present invention: The embodiments of the present invention provide a pneumatic unlocking device and unlocking method for aerospace hydraulic dampers. The pneumatic unlocking device has two parts: one part is a pneumatic lock mechanism installed inside the aerospace hydraulic damper; the other part is a pneumatic unlocking assembly communicating with the unlocking cavity of the outer cylinder 19 of the aerospace hydraulic damper. In the pneumatic lock mechanism, the claw end of the locking claw 17, which is limited and installed at the end of the piston rod 18, engages with the stop end of the spring lock seat assembly installed at the end of the damper in the positioned position, so that the claw end and the outer cylinder 19 of the damper form a limiting structure in the engaged state; and an unlocking cavity is formed between the spring lock seat assembly and the outer cylinder 19 of the aerospace hydraulic damper; in the pneumatic unlocking assembly, the air pump 1, the air tank 3 and the valve block assembly are connected in sequence, and the valve block assembly is connected to the unlocking cavity of the outer cylinder 19 of the aerospace hydraulic damper through the air pipe 8; the valve block assembly is equipped with a pressure regulating valve assembly 11, a pressure gauge 10 and a pressure relief assembly. By using this pneumatic unlocking device, a preset pressure of gas can be supplied to the unlocking chamber of the aerospace hydraulic damper through the pneumatic unlocking component. The gas pressure in the unlocking chamber will push the spring lock seat assembly to move away from the lock claw 17. The movement of the spring lock seat assembly will disengage from the lock claw 17, thereby realizing the pneumatic unlocking of the lock mechanism.

[0016] The pneumatic unlocking device provided in this invention has a simple structure, is easy to install and operate; it unlocks the internal pneumatic lock mechanism of the aerospace hydraulic damper without disassembling its parts, avoiding damage to the original structure caused by repeated disassembly, and meeting the usage requirements of various series of aerospace hydraulic dampers. The pressure regulating valve assembly used in this pneumatic unlocking device adopts a conical seal and a double combination seal, resulting in better sealing performance; the unlocking gas used in this device is low-pressure air, which is low-cost, low-risk, and readily available; the air pump 1 used is a portable air pump, easy to carry, and can be repeatedly charged and discharged, meeting the needs of aerospace field working environments. During use, users can monitor the performance changes of the springs and other structures in the aerospace hydraulic damper by comparing the unlocking pressure value with the factory pressure value, facilitating timely replacement. This device has been manufactured and assembled and put into verification tests on aerospace hydraulic dampers. Verification has shown that it can effectively unlock without disassembling the aerospace hydraulic damper. Attached Figure Description

[0017] The accompanying drawings are provided to further understand the technical solutions of the present invention and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of the present invention and do not constitute a limitation on the technical solutions of the present invention.

[0018] Figure 1 This is a schematic diagram of the overall structure of a pneumatic unlocking device for an aerospace hydraulic damper, provided by an embodiment of the present invention. Figure 2 for Figure 1 The illustrated embodiment provides a three-dimensional structural schematic diagram of a pneumatic unlocking device for aerospace hydraulic dampers. Figure 3 for Figure 1 The illustrated embodiment provides a schematic diagram of the structure in which the pneumatic lock mechanism is installed inside the aerospace hydraulic damper in a pneumatic unlocking device for aerospace hydraulic dampers. Figure 4 for Figure 3 An enlarged schematic diagram of the pneumatic lock mechanism disposed inside the aerospace hydraulic damper in the embodiment shown; Figure 5 for Figure 1 The illustrated embodiment provides a schematic diagram of the pressure regulating valve assembly in a pneumatic unlocking device for aerospace hydraulic dampers. Figure 6 for Figure 5 A schematic diagram of the gas flow direction at the front end of the pressure regulating valve assembly in the illustrated embodiment; Figure 7 for Figure 1 The illustrated embodiment provides a schematic diagram of the valve block assembly in a pneumatic unlocking device for aerospace hydraulic dampers. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

[0020] As explained in the background section, existing unlocking devices and unlocking methods for actuators used in other technical fields have limitations and cannot achieve unlocking without disassembling parts.

[0021] To address the shortcomings of existing devices and unlocking methods, this invention proposes a pneumatic unlocking device and method for aerospace hydraulic dampers. The device can achieve the following functions: after the aerospace hydraulic damper is locked, without disassembling the internal elastic locking claw structure, compressed air is supplied to the interior of the aerospace hydraulic damper using the pneumatic unlocking device. Under the action of gas pressure, the elastic locking claw inside the aerospace hydraulic damper is popped open, thereby achieving automatic unlocking.

[0022] The present invention provides the following specific embodiments, which can be combined with each other. For the same or similar concepts or processes, they may not be described again in some embodiments.

[0023] Figure 1 This is a schematic diagram of the overall structure of a pneumatic unlocking device for an aerospace hydraulic damper, provided by an embodiment of the present invention. Figure 2 for Figure 1 The illustrated embodiment provides a three-dimensional structural schematic diagram of a pneumatic unlocking device for aerospace hydraulic dampers. Figure 3 for Figure 1 The illustrated embodiment provides a schematic diagram of the structure in which the pneumatic lock mechanism is installed inside the aerospace hydraulic damper in a pneumatic unlocking device. Figure 4 for Figure 3 An enlarged schematic diagram of the pneumatic lock mechanism disposed inside the aerospace hydraulic damper in the illustrated embodiment. (Refer to...) Figures 1 to 4 As shown, the pneumatic unlocking device for aerospace hydraulic dampers provided in this embodiment of the invention comprises two parts: one part is a pneumatic lock mechanism disposed inside the aerospace hydraulic damper, such as... Figure 3 and Figure 4 As shown, the other part is a pneumatic unlocking assembly that is connected to the unlocking chamber of the outer cylinder 19 of the aerospace hydraulic damper.

[0024] like Figure 3 and Figure 4As shown, in the pneumatic lock mechanism of the aerospace hydraulic damper in this embodiment of the invention, the locking claw 17 is limited and installed in the annular groove formed by the piston rod 18 and the end face piston 15 through its fixed end. Under the pull of the piston rod 18 extending, the claw end of the locking claw 17 engages with the stop end of the spring lock seat assembly installed at the end of the damper in the position, so that the claw end and the outer cylinder 19 of the damper form a limiting structure in the engaged state; and an unlocking cavity is formed between the spring lock seat assembly and the outer cylinder 19 of the aerospace hydraulic damper, and an unlocking port for connecting the unlocking cavity and the pneumatic unlocking assembly is provided on the outer cylinder 19.

[0025] like Figure 1 and Figure 2 As shown, the pneumatic unlocking assembly in this embodiment of the invention includes: The air pump 1, air tank 3, and valve block assembly are connected in sequence through the air pipe 8. The valve block assembly is connected to the unlocking port of the outer cylinder 19 of the aerospace hydraulic damper through the air pipe 8. The valve block assembly is equipped with a pressure regulating valve assembly 11, a pressure gauge 10, and a pressure relief assembly. The pressure regulating valve assembly 11 is used to regulate the air supply pressure to the aerospace hydraulic damper and to shut off the air supply. The pressure gauge 10 is used to measure the air supply pressure to the aerospace hydraulic damper. After the locking mechanism is unlocked by supplying air to the unlocking chamber of the aerospace hydraulic damper, the pressure inside the valve block assembly is discharged through the pressure relief assembly.

[0026] Based on the above-mentioned structure of the pneumatic unlocking device, the working mode of the pneumatic unlocking device provided in this embodiment of the invention is as follows: the pneumatic unlocking component provides gas with a preset pressure to the unlocking chamber of the aerospace hydraulic damper, and the gas pressure in the unlocking chamber pushes the spring lock seat assembly to move away from the lock claw 17. The movement of the spring lock seat assembly disengages from the lock claw 17, thereby realizing the pneumatic unlocking of the lock mechanism.

[0027] In one implementation of this invention, an embodiment of a pneumatic lock mechanism inside an aerospace hydraulic damper is provided, such as... Figure 3 and Figure 4 As shown, the pneumatic lock mechanism includes: end nut 14, piston 15, locking claw 17, piston rod 18, outer cylinder 19, end cap nut 23, and spring lock seat assembly.

[0028] In this implementation, a spring lock seat assembly is installed in the mounting cavity at the end of the outer cylinder 19. The piston rod 18 passes through the central hole of the spring lock seat assembly and can move relative to it along the axial direction of the spring lock seat assembly. The spring lock seat assembly inside the outer cylinder 19 is fixedly installed by the end cap nut 23. A piston 15 is sleeved on the end of the piston rod 18 located inside the outer cylinder 19. An annular groove is formed between the piston 15 and the shoulder at the front of the piston rod 18, which is used to limit the locking claw 17 to be installed on the annular groove through its fixed end, so that the claw end of the locking claw 17 is located on the side facing the protruding end of the spring lock seat assembly. The piston 15 and the locking claw 17 are locked and fixed by the end nut 14 screwed to the end of the piston rod 18.

[0029] In this implementation, an annular limiting boss is provided on the inner wall of the outer cylinder 19 to axially limit the stop piston 20 passing through the annular limiting boss in the spring lock seat assembly. This allows the stop piston 20 to abut against the limiting boss under the action of the spring 21 inside the spring lock seat assembly, and the stop end of the stop piston 20 to be limited to a position for locking with the claw end of the lock claw 17 after passing through the limiting boss.

[0030] Furthermore, such as Figure 3 and Figure 4 As shown, the spring lock seat assembly in this implementation includes: a stop piston 20, a spring 21, an oil scraper ring 22, and a retaining ring 24.

[0031] The stop piston 20, the oil scraper ring 22 and the retaining ring 24 are sequentially sleeved on the piston rod 18, and the end cap nut 23 screwed onto the outer cylinder 19 abuts against and fixes the axial position of the oil scraper ring 22. The stop piston 20 is sleeved on the oil scraper ring 22 through the sleeve facing the end of the stop piston 20, and a spring 21 is sleeved between the stop piston 20 and the oil scraper ring 22.

[0032] In this implementation, the stop piston 20, under the action of the spring force of the spring 21, has its stop end facing the lock claw 17 pass through and extend inward into the annular limiting boss of the outer cylinder 19, and presses against the annular limiting boss through its stepped end face. An unlocking cavity acting on the pneumatic lock mechanism is formed between the stop piston 20 and the annular limiting boss of the outer cylinder 19.

[0033] In specific implementation, such as Figure 4 As shown, the pneumatic lock mechanism also includes: an outer piston sealing ring 16 disposed between the piston 15 and the outer cylinder 19; an inner piston sealing ring 25 disposed between the piston 15 and the piston rod 18; a stop piston stop end sealing ring 26 disposed between the annular limiting boss of the outer cylinder 19 and the stop piston 20; an outer stop piston sealing ring 27 disposed between the stop piston 20 and the outer cylinder 19; and an inner stop piston sealing ring 28 disposed between the stop piston 20 and the piston rod 18.

[0034] In one implementation of this invention, an embodiment of the valve block assembly in a pneumatic unlocking assembly is provided, such as... Figure 1 , Figure 2 and Figure 7 As shown, the valve block assembly includes: valve block 5 and multiple screw plugs 13. Figure 7 for Figure 1 The illustrated embodiment provides a schematic diagram of the valve block assembly in a pneumatic unlocking device for aerospace hydraulic dampers.

[0035] In this implementation, valve block 5 has a pressure regulating valve assembly interface, a gas tank interface, a pressure pipe interface, a gas pipe interface, and a pressure relief interface. The valve block 5 has multiple valve body pipelines inside, which are used to connect the pressure regulating valve assembly interface with the gas tank interface, the pressure pipe interface, the gas pipe interface, and the pressure relief interface respectively. The valve block 5 also has multiple process holes for forming the internal pipeline connection structure, and each process hole is sealed by a screw plug 13.

[0036] The pneumatic unlocking component in this implementation also includes: air pump adapter 2, air tank adapter 4, adapter 6, pipeline ball valve 7a and unlocking port adapter 9; the pressure relief component is set as pressure relief ball valve 7b.

[0037] In this implementation, the output pipeline of the air pump 1 is connected to the input interface of the air tank 3 via the air pump adapter 2, and the output interface of the air tank 3 is connected to the air tank interface on the valve block 5 via the air tank adapter 4. The valve block 5 is equipped with the pressure regulating valve assembly 11 via the pressure regulating valve assembly interface and the pressure gauge 10 via the pressure pipe interface. The pressure relief interface of the valve block 5 is connected to the pressure relief ball valve 7b via an adapter 6, and its air pipe interface is connected to the rear air pipe 8 via another adapter 6. The end of the rear air pipe 8 is connected to the front end of the pipeline ball valve 7a, and the rear end of the pipeline ball valve 7a is connected to the unlocking port of the aerospace hydraulic damper via the unlocking port adapter 9, thereby connecting to the unlocking chamber of the pneumatic lock mechanism located inside the aerospace hydraulic damper.

[0038] In one implementation of this invention, an embodiment of the pressure regulating valve assembly 11 is provided, such as... Figure 1 , Figure 2 ,as well as Figure 5 and Figure 6 As shown, the valve block assembly in this implementation includes: a nylon washer 11.1, a valve core sealing ring 11.2, a valve core 11.3, a nut 11.4, a handle 11.5, a fixing screw 11.6, and a valve sleeve 11.7; The nylon gasket 11.1 is fixedly installed at the front end of the valve sleeve 11.7, and the valve core 11.3 is screwed into the valve sleeve 11.7 with its central thread structure. The front part of the valve core 11.3 is configured as a combination structure of a sealing column and a cone front end. Two valve core sealing rings 11.2 are installed between the outer wall of the sealing column at the front of the valve core 11.3 and the valve sleeve 11.7. The cone front end of the valve core 11.3 is embedded in the nylon gasket 11.1 at the front end of the valve sleeve 11.7, thereby achieving end sealing.

[0039] In this implementation, the handle 11.5 is fixedly installed at the end of the valve core 11.3 by a fixing screw 11.6, and is used to control the axial movement of the valve core 11.3 inside the valve sleeve 11.7 by rotating the handle 11.5; a nut 11.4 is installed on the rod of the valve core 11.3 located between the handle and the valve sleeve 11.7, and is used to fix and lock the valve core 11.3 after adjusting the relative position of the valve core 11.3 and the valve sleeve 11.7 by the handle 11.5.

[0040] Furthermore, the pressure regulating valve assembly 11 in this implementation also includes: a valve sleeve sealing ring 11.8 and a locking nut 11.9.

[0041] In this implementation, the valve sleeve 11.7 is embedded inside the valve block 5 with its external thread structure, and is fixed by a locking nut 11.9 fitted on the valve sleeve 11.7. The locking nut 11.9 is screwed into the valve block 5 with its external thread structure, and the valve sleeve 11.7 is pressed into the valve body 5 by its inner end face, so as to ensure that the valve sleeve 11.7 is always fixed inside the valve body 5 when adjusting the relative position of the valve core 11.3 and the valve sleeve 11.7.

[0042] In specific implementation, the pressure regulating valve assembly 11 is provided with multiple sealing structures, namely: The first sealing structure is formed by tightening the nylon gasket 11.1 at the front end of the valve sleeve 11.7; a valve sleeve sealing ring 11.8 is installed on the outer periphery of the valve sleeve 11.7 to form the second sealing structure; the first sealing structure and the second sealing structure are used to prevent gas in the gas storage tank 3 from entering the valve block 5 and then leaking from the outside of the valve sleeve 11.7.

[0043] Based on the pneumatic unlocking device for aerospace hydraulic dampers provided in the embodiments of the present invention, the present invention also provides a pneumatic unlocking method for aerospace hydraulic dampers. In specific implementation, the aerospace hydraulic damper is equipped with a pneumatic unlocking device as provided in any of the above embodiments. The pneumatic unlocking method implemented by the pneumatic unlocking device includes the following steps: Step 1: Place the locked aerospace hydraulic damper horizontally, install the unlocking port adapter 9 onto the unlocking port of the outer cylinder 19 of the aerospace hydraulic damper, and connect the air pipe 8 at the rear end of the pneumatic unlocking component through the lock port adapter 9 to connect the pneumatic unlocking component with the unlocking chamber of the pneumatic lock mechanism inside the aerospace hydraulic damper. Step 2: For the assembled pneumatic unlocking assembly, close the pipeline ball valve 7a and the pressure relief ball valve 7b on the pneumatic unlocking assembly, turn on the air pump 1, and the air pump 1 inputs gas into the valve block 5 through the air storage tank 3. After the gas pressure in the valve block 5 reaches the unlocking pressure of the pneumatic lock mechanism in the aerospace hydraulic damper, open the pipeline ball valve 7a connected to the unlocking port of the aerospace hydraulic damper. Step 3, supplying unlocking gas to the aerospace hydraulic damper through the pressure regulating valve assembly 11, includes: opening and closing the pressure regulating valve assembly 11, so that after the valve core 11.3 moves under the turning of the handle 11.5, the gas flows through the air hole between the valve core 11.3 and the valve sleeve 11.7 to the pressure gauge 10, and is supplied to the unlocking chamber of the aerospace hydraulic damper through the air pipe 8 and the pipeline ball valve 7a; under the action of gas pressure, the locking claw 17 inside the aerospace hydraulic damper is opened, thereby unlocking.

[0044] Furthermore, the pneumatic unlocking method for aerospace hydraulic dampers provided in this embodiment of the invention further includes the following steps after unlocking: Step 4: When the piston rod 18 of the aerospace hydraulic damper begins to retract slowly, close the pressure regulating valve assembly 11 so that the pneumatic unlocking assembly stops supplying air to the pneumatic lock mechanism. Read the pressure value displayed on the pressure gauge 10 on the valve block 5. The read pressure value is the unlocking pressure value set by the aerospace hydraulic damper. Step 5: After the aerospace hydraulic damper is successfully unlocked, open the pressure relief ball valve 7b on valve block 5 to release the high-pressure gas inside the aerospace hydraulic damper through the pressure relief ball valve 7b on valve block 5; and continue to manually compress the piston rod 18 of the aerospace hydraulic damper until the piston rod 18 is completely retracted.

[0045] The existing mechanical unlocking devices and corresponding unlocking methods used in the actuators have limitations. Moreover, the mechanical disassembly method is used to unlock the device, which is complex and requires the disassembly of many parts, making it easy for parts to be lost or damaged. In addition, the repeated assembly and reassembly of the mechanical unlocking device will cause wear and tear on the parts, which will lead to a decrease in the overall accuracy of the device and make it unable to meet the expected functions.

[0046] This invention provides a pneumatic unlocking device and method for aerospace hydraulic dampers. The pneumatic unlocking device has two parts: a pneumatic lock mechanism located inside the aerospace hydraulic damper, and a pneumatic unlocking assembly connected to the unlocking cavity of the outer cylinder 19 of the aerospace hydraulic damper. In the pneumatic lock mechanism, the claw end of the locking claw 17, which is limited and installed at the end of the piston rod 18, engages with the stop end of the spring lock seat assembly installed at the end of the damper in the correct position, so that the claw end and the outer cylinder 19 of the damper form a limiting structure in the engaged state; and an unlocking cavity is formed between the spring lock seat assembly and the outer cylinder 19 of the aerospace hydraulic damper. In the pneumatic unlocking assembly, the air pump 1, the air tank 3, and the valve block assembly are connected in sequence, and the valve block assembly is connected to the unlocking cavity of the outer cylinder 19 of the aerospace hydraulic damper through the air pipe 8; the valve block assembly is equipped with a pressure regulating valve assembly 11, a pressure gauge 10, and a pressure relief assembly. By using this pneumatic unlocking device, a preset pressure of gas can be supplied to the unlocking chamber of the aerospace hydraulic damper through the pneumatic unlocking component. The gas pressure in the unlocking chamber will push the spring lock seat assembly to move away from the lock claw 17. The movement of the spring lock seat assembly will disengage from the lock claw 17, thereby realizing the pneumatic unlocking of the lock mechanism.

[0047] The pneumatic unlocking device provided in this invention has a simple structure, is easy to install and operate; it unlocks the internal pneumatic lock mechanism of the aerospace hydraulic damper without disassembling its parts, avoiding damage to the original structure caused by repeated disassembly, and meeting the usage requirements of various series of aerospace hydraulic dampers. The pressure regulating valve assembly used in this pneumatic unlocking device adopts a conical seal and a double combination seal, resulting in better sealing performance; the unlocking gas used in this device is low-pressure air, which is low-cost, low-risk, and readily available; the air pump 1 used is a portable air pump, easy to carry, and can be repeatedly charged and discharged, meeting the needs of aerospace field working environments. During use, users can monitor the performance changes of the springs and other structures in the aerospace hydraulic damper by comparing the unlocking pressure value with the factory pressure value, facilitating timely replacement. This device has been manufactured and assembled and put into verification tests on aerospace hydraulic dampers. Verification has shown that it can effectively unlock without disassembling the aerospace hydraulic damper.

[0048] The following is an illustrative description of an embodiment of the pneumatic unlocking device and unlocking method for aerospace hydraulic dampers provided by the present invention.

[0049] Implementation Example This implementation example provides a pneumatic unlocking device for aerospace hydraulic dampers, such as Figure 1 and Figure 2 As shown, the pneumatic unlocking device includes: a pneumatic lock mechanism installed inside the aerospace hydraulic damper, and a pneumatic unlocking assembly connected to the unlocking chamber of the outer cylinder 19 of the aerospace hydraulic damper.

[0050] The structure of the pneumatic lock mechanism inside the aerospace hydraulic damper is as follows: Figure 3 and Figure 4 As shown in the above embodiments, the structural form of the locking mechanism and the unlocking function have been described in detail.

[0051] The pneumatic unlocking assembly in this implementation example includes: an air pump 1, an air pump adapter 2, an air tank 3, an air tank adapter 4, a valve block 5, a G1 / 4 adapter 6, a pipeline ball valve 7a, a pressure relief ball valve 7b, an air pipe 8, an unlocking port adapter 9, a pressure gauge 10, a pressure regulating valve assembly 11, a pressure gauge adapter 12, and a screw plug 13. The air tank 3 has two holes; one hole is connected to the air pump 1 via the air pump adapter 2, and the other hole is connected to the valve block 5 via the air tank adapter 4. Pressure gauge 10 is mounted on valve block 5 via pressure gauge adapter 12; pressure relief ball valve 7b is mounted on valve block 5 via G1 / 4 adapter 6; pressure regulating valve assembly 11 is threaded onto pressure regulating valve assembly interface of valve block 5; one end of air pipe 8 is mounted on air pipe interface of valve block 5 via G1 / 4 adapter 6, and the other end is threaded onto pipeline ball valve 7a; the other end of pipeline ball valve 7a is connected to the unlocking port on outer cylinder of aerospace hydraulic damper via unlocking port adapter 9.

[0052] like Figure 5 and Figure 6 As shown, the pressure regulating valve assembly 11 in this embodiment includes: a nylon washer 11.1, a valve core sealing ring 11.2, a valve core 11.3, a nut 11.4, a handle 11.5, a fixing screw 11.6, a valve sleeve 11.7, a valve sleeve sealing ring 11.8, and a locking nut 11.9. In the internal structure of this pressure regulating valve assembly 11, the valve core 11.3 is screwed into the valve sleeve 11.7 with its central threaded structure. The front part of the valve core 11.3 is configured as a combination of a sealing column and a conical front end. Two valve core sealing rings 11.2 are installed between the outer wall of the sealing column at the front of the valve core 11.3 and the valve sleeve 11.7 to ensure gas sealing. The conical front end of the valve core 11.3 has a conical surface that can be directly embedded into the nylon washer 11.1 located at the front end of the valve sleeve 11.7, thereby achieving end sealing.

[0053] The handle 11.5 is fixedly mounted on the end of the valve core 11.3 by a fixing screw 11.6. It is used to control the axial movement of the valve core 11.3 inside the valve sleeve 11.7 by rotating the handle 11.5. In addition, a nut 11.4 is installed on the rod of the valve core 11.3 located between the handle 11.5 and the valve sleeve 11.7. It is used to lock the valve core 11.3 in any position after adjusting the relative position of the valve core 11.3 and the valve sleeve 11.7 by the handle 11.5, and can control the stroke of the valve core 11.3.

[0054] like Figure 5 and Figure 6 As shown, during the movement of the pressure regulating valve assembly 11, the valve sleeve 11.7 is installed inside the valve block 5 with a right-hand thread and is fixed by a locking nut 11.9 fitted onto the valve sleeve 11.7. A nylon washer 11.1 is placed at the bottom of the valve sleeve 11.7. Tightening the valve sleeve 11.7 compresses the nylon washer 11.1, which is the first sealing structure, ensuring that the gas in the gas tank 3 does not leak directly out of the valve sleeve 11.7 after entering the valve block 5. Two valve sleeve sealing rings 11.8 are installed on the outer circumference of the valve sleeve 11.7, which is the second sealing structure, further ensuring that the gas in the gas tank 3 does not leak directly out of the valve sleeve 11.7 after entering the valve block 5. The locking nut 11.9, which is fixedly installed on the outside of the valve sleeve 11.7, is screwed into the valve block 5 with a left-hand thread on the outside and the valve sleeve 11.7 is pressed by the inner end face, ensuring that the valve sleeve 11.7 does not move up and down when adjusting the valve core 11.3.

[0055] like Figure 6 As shown, six vent holes are opened on the circumferential sidewall of the front end of the valve sleeve 11.7. When the valve core 11.3 moves away from the nylon gasket 11.1, a gap is created between the front cone of the valve core 11.3 and the surface of the nylon gasket 11.1. Gas in the gas tank 3 can flow out through this gap from the six vent holes on the front end of the valve sleeve 11.7 and then be transmitted to the rear end of the gas pipe 8 through the internal pipeline of the valve body 5. At this time, the two valve core sealing rings 11.2 installed on the valve core 11.3 can ensure that gas does not leak out from the outside of the valve core 11.3; the two valve sleeve sealing rings 11.8 installed on the outer circumference of the valve sleeve 11.7 can also ensure that gas does not leak out from the outside of the valve sleeve 11.7; thus, a double combination seal is achieved, resulting in a better sealing effect.

[0056] like Figure 7 As shown, the valve block 5 in this embodiment has six end faces. The upper end face is equipped with a pressure gauge 10 and a pressure regulating valve assembly 11. The front end face is equipped with an air tank 3. The left end face is equipped with an air pipe 8 and a ball valve. The other end faces are respectively opened with process holes to realize the communication between various pipelines. The end of the process hole is sealed by a screw plug 13.

[0057] In addition, this implementation example also provides a pneumatic unlocking method for aerospace hydraulic dampers, including the following implementation steps in several stages: Assembly stage: Step 1: Secure the rear end of the locked aerospace hydraulic damper with bolts and place the aerospace hydraulic damper horizontally. Install the unlocking port adapter 9 onto the unlocking port of the aerospace hydraulic damper and connect the air pipe 8 at the rear end of the pneumatic unlocking component through the lock port adapter 9 to connect the pneumatic unlocking component with the unlocking chamber of the pneumatic lock mechanism inside the aerospace hydraulic damper.

[0058] Step 2, assemble the pneumatic unlocking assembly, including: installing the G1 / 4 adapter 6, pressure regulating valve assembly 11, pressure gauge adapter 12, and air tank adapter 4 onto the corresponding interfaces of the valve block 5; installing the pressure gauge 10, pipeline ball valve 7a, pressure relief ball valve 7b, and air tank 3 onto the corresponding connectors; connecting the air pump 1 to the air tank 3 via the air pump adapter 2; and sealing the threaded connections of the above parts using nylon washers, Teflon tape, etc. Debugging phase: Step 3: Close the pipeline ball valve 7a and pressure relief ball valve 7b on the assembled pneumatic unlocking assembly. Set the air pump 1 to the specified pressure (this specified pressure is greater than the unlocking pressure) and then turn on the air pump 1 to allow gas to enter the valve block 5 through the air tank 3. Manually rotate the handle 11.5 on the pressure regulating valve assembly 11 counterclockwise to move the valve core 11.3, allowing gas to flow out through the gap between the valve core 11.3 and the nylon gasket 11.1 from the six air outlets on the bottom side wall of the valve sleeve 11.7, and continue to flow to the pressure gauge 10. Then, through the rear air pipe 8, it flows into the unlocking chamber inside the outer cylinder 19 of the aerospace hydraulic damper. After the air supply pressure in the pneumatic unlocking assembly reaches the set pressure value of the air pump 1, check the display values ​​of the air pump 1 and the pressure gauge 10. If the displayed values ​​remain stable without change, it indicates that the air circuit inside the pneumatic unlocking assembly is well sealed and there is no air leakage. Turn off air pump 1 and open the pressure relief ball valve 7b on valve block 5 to depressurize the pneumatic unlocking assembly.

[0059] Step 4: Close the pipeline ball valve 7a and the pressure relief ball valve 7b on the pneumatic unlocking assembly. Manually rotate the handle 11.5 on the pressure regulating valve assembly 11 clockwise to move the valve core 11.3 to the end of the valve sleeve 11.7, so that there is no gap between the bottom conical surface of the valve core 11.3 and the surface of the nylon washer 11.1. Then, lock the valve core 11.3 with the nut 11.4 to prevent the gas generated by the air pump 1 from entering the unlocking chamber of the aerospace hydraulic damper through the pressure regulating valve assembly 11.

[0060] Unlocking phase: Step 5: Turn on the air pump 1 to pressurize the air tank 3 to 2.5 bar (set according to actual needs), and open the pipeline ball valve 7a connected to the unlocking port of the aerospace hydraulic damper; at this time, the locking claw 17 sleeved on the piston rod 18 inside the aerospace hydraulic damper is locked to the stop end of the spring lock seat assembly, and at this time, the valve core 11.3 in the pressure regulating valve assembly 11 is pressed against the nylon washer 11.1 at the end of the valve sleeve 11.7, and the gas in the valve body 5 has not yet been supplied to the aerospace hydraulic damper; Step 5: Loosen the nut 11.4 on the valve core 11.3 in the pressure regulating valve assembly 11 so that the valve core 11.3 can be turned normally; slowly turn the handle 11.5 counterclockwise so that the valve core 11.3 slowly moves axially along the valve sleeve 11.7 away from the nylon washer 11.1, so that the gas flows out through the gap between the valve core 11.3 and the nylon washer 11.1 from the six air outlets on the bottom side wall of the valve sleeve 11.7 and continues to flow to the pressure gauge 10, and is supplied to the unlocking chamber of the aerospace hydraulic damper through the air pipe 8; under the action of gas pressure, the locking claw 17 inside the aerospace hydraulic damper is opened to unlock.

[0061] Step 6: When the piston rod 18 of the aerospace hydraulic damper begins to slowly retract (indicating that pneumatic unlocking has been achieved), immediately tighten the handle 11.5 clockwise to close the pressure regulating valve assembly 11, ensuring there is no gap between the valve core 11.3 and the nylon washer 11.1, and lock it with the nut 11.4, preventing the gas generated by the air pump 1 from entering the aerospace hydraulic damper through the pressure regulating valve assembly 11. At this time, read the pressure value displayed on the pressure gauge 10 on the valve block 5; the read pressure value is the unlocking pressure value of the aerospace hydraulic damper at the factory.

[0062] It should be noted that by monitoring the unlocking pressure value of the aerospace hydraulic damper during both factory manufacturing and user operation, the performance changes of internal structures such as the internal spring 21 can be determined, facilitating timely replacement. If the monitored pressure value is lower than the unlocking pressure value at the time of manufacture, it indicates that the elasticity of the spring 21 has deteriorated, and replacement is necessary.

[0063] Step 7: After the aerospace hydraulic damper is successfully unlocked, open the pressure relief ball valve 7b on valve block 5 to release the high-pressure gas inside the aerospace hydraulic damper through the pressure relief ball valve 7b on valve block 5; in addition, continue to manually compress the piston rod 18 of the aerospace hydraulic damper until the piston rod 18 is completely retracted.

[0064] Furthermore, when the aerospace hydraulic damper needs to be unlocked again, if the gas tank 3 has sufficient gas, the handle 11.5 on the pressure regulating valve assembly 11 can be adjusted directly to unlock it. If the gas tank 3 has insufficient gas, the air pump 1 can be turned on to replenish the gas. After replenishment, the handle 11.5 on the pressure regulating valve assembly 11 can be adjusted to unlock it.

[0065] While the embodiments disclosed in this invention are as described above, they are merely illustrative of the embodiments to facilitate understanding of the invention and are not intended to limit the invention. Any person skilled in the art to which this invention pertains may make any modifications and variations in the form and details of the implementation without departing from the spirit and scope disclosed herein; however, the scope of patent protection for this invention shall still be determined by the scope defined in the appended claims.

Claims

1. A pneumatic unlocking device for a space flight hydraulic damper, characterized by, The application relates to a spaceflight hydraulic damper. The spaceflight hydraulic damper comprises a gas pressure locking mechanism arranged in the spaceflight hydraulic damper and a gas pressure unlocking assembly communicated with an unlocking cavity of an outer cylinder (19) of the spaceflight hydraulic damper. The locking claw (17) is fixedly arranged in an annular groove formed by the piston rod (18) and the end face piston (15) through a fixed end of the locking claw (17), and the claw end of the locking claw (17) is clamped on a stop end of a spring locking seat assembly arranged on the end of the damper under the pulling of the extension movement of the piston rod (18), so that the claw end is limited by the outer cylinder (19) of the damper in the clamped state; and the spring locking seat assembly and the outer cylinder (19) of the spaceflight hydraulic damper form an unlocking cavity, and the outer cylinder (19) is provided with an unlocking opening for communicating the unlocking cavity and the gas pressure unlocking assembly. The gas pressure unlocking assembly comprises a gas pump (1), a gas storage tank (3) and a valve block assembly connected in sequence through a gas pipe (8), and the valve block assembly is connected to the unlocking opening of the outer cylinder (19) of the spaceflight hydraulic damper through the gas pipe (8); a pressure regulating valve assembly (11), a pressure gauge (10) and a pressure relief assembly are arranged on the valve block assembly, the pressure regulating valve assembly (11) is used for regulating the gas supply pressure of the spaceflight hydraulic damper and closing the gas supply, the pressure gauge (10) is used for measuring the gas supply pressure of the spaceflight hydraulic damper, and the pressure relief assembly is used for discharging the pressure in the valve block assembly after the unlocking of the locking mechanism is realized by supplying gas to the unlocking cavity of the spaceflight hydraulic damper. The gas pressure locking mechanism in the spaceflight hydraulic damper comprises an end nut (14), a piston (15), a locking claw (17), a piston rod (18), an outer cylinder (19), an end cover nut (23) and a spring locking seat assembly.

2. The gas pressure unlock device for a space flight hydraulic damper according to claim 1, wherein The spring locking seat assembly is arranged in an installation cavity at the end of the outer cylinder (19), the piston rod (18) passes through a center hole of the spring locking seat assembly and can axially move relative to the spring locking seat assembly, and the spring locking seat assembly in the outer cylinder (19) is fixedly arranged through the end cover nut (23); the end of the piston rod (18) located in the outer cylinder (19) is sleeved with the piston (15), an annular groove is formed between the piston (15) and the shaft shoulder of the front part of the piston rod (18), the locking claw (17) is fixedly arranged in the annular groove through a fixed end of the locking claw (17), the claw end of the locking claw (17) is located on the side of the extension end of the spring locking seat assembly, and the piston (15) and the locking claw (17) are locked and fixed through the end nut (14) screwed on the end of the piston rod (18). An annular limiting boss is arranged on the inner wall of the outer cylinder (19) and is used for axially limiting a stop piston (20) passing through the annular limiting boss in the spring locking seat assembly, so that the stop piston (20) abuts against the annular limiting boss under the action of a spring (21) in the spring locking seat assembly, and the stop end of the stop piston (20) is limited at a position for locking the claw end of the locking claw (17) after passing through the annular limiting boss. The spring locking seat assembly comprises the stop piston (20), the spring (21), an oil scraping ring (22) and a check ring (24).

3. The gas pressure unlock device for a space flight hydraulic damper according to claim 2, wherein ​ The stop piston (20), the oil scraping ring (22) and the check ring (24) are sequentially sleeved and installed on the piston rod (18), and the axial position of the oil scraping ring (22) is fixed by abutting against the end cover nut (23) which is screwed on the outer cylinder (19), the stop piston (20) is sleeved on the oil scraping ring (22) through the sleeve at the end of the stop piston (20) facing the oil scraping ring (22), and the spring (21) is sleeved and installed between the stop piston (20) and the oil scraping ring (22); The stop end of the stop piston (20) at the end facing the locking claw (17) penetrates and extends inwardly from the annular limiting boss of the outer cylinder (19), and abuts against the annular limiting boss through the stepped end face, so that the stop piston (20) and the annular limiting boss of the outer cylinder (19) form a unlocking cavity acting on the gas pressure lock mechanism.

4. The gas pressure unlock device for a space flight hydraulic damper according to claim 1, wherein The valve block assembly comprises a valve block (5) and a plurality of screw plugs (13). The valve block (5) is provided with a pressure regulating valve assembly interface, a gas tank interface, a pressure pipe interface, a gas pipe interface and a pressure relief interface, and a plurality of valve body pipelines are formed in the valve block (5) to connect the pressure regulating valve assembly interface, the gas tank interface, the pressure pipe interface, the gas pipe interface and the pressure relief interface, respectively; a plurality of process holes are formed in the valve block (5) to form the internal pipeline connection structure, and each process hole is blocked by a screw plug (13).

5. The gas pressure unlock device for a space hydraulic damper according to claim 4, wherein The gas pressure unlocking assembly further comprises a gas pump adapter (2), a gas tank adapter (4), an adapter (6), a pipeline ball valve (7a), an unlocking port adapter (9) and a pressure gauge adapter (12); the pressure relief assembly is a pressure relief ball valve (7b); The output pipeline of the gas pump (1) is connected to the input end interface of the gas tank (3) through the gas pump adapter (2), the output end interface of the gas tank (3) is connected to the gas tank interface of the valve block (5) through the gas tank adapter (4), the valve block (5) is provided with a pressure regulating valve assembly (11) through the pressure regulating valve assembly interface and a pressure gauge (10) through the pressure pipe interface; the pressure relief interface of the valve block (5) is connected to the pressure relief ball valve (7b) through an adapter (6), the gas pipe interface is connected to the rear-end gas pipe (8) through another adapter (6), the rear end of the rear-end gas pipe (8) is connected to the front end of the pipeline ball valve (7a), and the rear end of the pipeline ball valve (7a) is connected to the unlocking port of the aerospace hydraulic damper through the unlocking port adapter (9), so as to be connected to the unlocking cavity of the gas pressure lock mechanism arranged in the aerospace hydraulic damper.

6. The gas pressure unlock device for a space flight hydraulic damper according to claim 1, wherein The pressure regulating valve assembly (11) comprises a nylon gasket (11.1), a valve core sealing ring (11.2), a valve core (11.3), a nut (11.4), a handle (11.5), a fixing screw (11.6) and a valve sleeve (11.7). The nylon gasket (11.1) is fixedly arranged at the front end of the valve sleeve (11.7), and the valve core (11.3) is screwed into the valve sleeve (11.7) through the threaded structure at the middle part thereof; the front part of the valve core (11.3) is provided with a combined structure of a sealing column and a conical front end, two valve core sealing rings (11.2) are arranged between the outer wall of the sealing column of the front part of the valve core (11.3) and the valve sleeve (11.7), and the conical front end of the valve core (11.3) is embedded into the nylon gasket (11.1) arranged at the front end of the valve sleeve (11.7), so as to realize end sealing. The handle (11.5) is fixedly arranged at the end of the valve core (11.3) through the fixing screw (11.6), and is used for controlling the axial movement of the valve core (11.3) in the valve sleeve (11.7) by rotating the handle (11.5); the nut (11.4) is arranged on the rod body between the handle and the valve sleeve (11.7), and is used for fixing and locking the valve core (11.3) after adjusting the relative position of the valve core (11.3) and the valve sleeve (11.7) through the handle (11.5).

7. The gas pressure unlock device for a space hydraulic damper according to claim 6, wherein The pressure regulating valve assembly (11) further comprises a valve sleeve sealing ring (11.8) and a locking nut (11.9). The valve sleeve (11.7) is embedded into the valve block (5) through the external thread structure thereof, is fixed by the locking nut (11.9) arranged on the valve sleeve (11.7), and is screwed into the valve block (5) through the external thread structure of the locking nut (11.9), and the inner side end face of the locking nut (11.9) is used to press the valve sleeve (11.7) tightly in the valve block (5), so that the valve sleeve (11.7) is always fixed in the valve block (5) when the relative position of the valve core (11.3) and the valve sleeve (11.7) is adjusted. The pressure regulating valve assembly (11) is provided with multiple sealing structures, which are respectively: The first sealing structure is formed by tightening the valve sleeve (11.7) to press the nylon gasket (11.1) arranged at the front end of the valve sleeve (11.7); the valve sleeve sealing ring (11.8) is arranged on the outer circumference of the valve sleeve (11.7) to form the second sealing structure; the first sealing structure and the second sealing structure are used to prevent the gas in the gas storage tank (3) from leaking from the outside of the valve sleeve (11.7) after entering the valve block (5).

8. A pneumatic unlock method for a space flight hydraulic damper, characterized by, The spaceflight hydraulic damper is provided with the gas pressure unlocking device for the spaceflight hydraulic damper according to any one of claims 1-7, and the gas pressure unlocking method implemented by the gas pressure unlocking device comprises: Step 1, place the locked spaceflight hydraulic damper horizontally, install the unlocking port adapter (9) on the unlocking port of the spaceflight hydraulic damper outer cylinder (19), and connect the gas pipe (8) at the rear end of the gas pressure unlocking assembly through the unlocking port adapter (9) to connect the gas pressure unlocking assembly and the unlocking cavity of the gas pressure locking mechanism in the spaceflight hydraulic damper; Step 2, for the completed assembly of the pneumatic unlocking assembly, close the pipeline ball valve (7a) and the pressure relief ball valve (7b) on the pneumatic unlocking assembly, open the air pump (1), the air pump (1) inputs gas into the valve block (5) through the gas storage tank (3), when the gas pressure in the valve block (5) reaches the unlocking pressure of the gas pressure lock mechanism in the aerospace hydraulic damper, open the pipeline ball valve (7a) connected with the unlocking port of the aerospace hydraulic damper; Step 3, provide unlocking gas to the aerospace hydraulic damper through the pressure regulating valve assembly (11), including: open the closed pressure regulating valve assembly (11), so that the valve core (11.3) moves under the rotation of the handle (11.5), the gas flows through the air hole between the valve core (11.3) and the valve sleeve (11.7) to the pressure gauge (10), and then through the air pipe (8) and the pipeline ball valve (7a) to the unlocking cavity of the aerospace hydraulic damper; under the action of gas pressure, the locking claw (17) inside the aerospace hydraulic damper is pushed open, and unlocking is realized.

9. The method of claim 8, wherein the method further comprises, Also includes: Step 4, when the piston rod (18) of the aerospace hydraulic damper begins to slowly contract, close the pressure regulating valve assembly (11), so that the pneumatic unlocking assembly does not supply gas to the gas pressure lock mechanism, read the pressure value displayed on the pressure gauge (10) on the valve block (5), and the read pressure value is the set unlocking pressure value of the aerospace hydraulic damper; Step 5, after the aerospace hydraulic damper is successfully unlocked, open the pressure relief ball valve (7b) on the valve block (5) to release the high-pressure gas inside the aerospace hydraulic damper through the pressure relief ball valve (7b) of the valve block (5); and continue to manually compress the piston rod (18) of the aerospace hydraulic damper until the piston rod (18) is completely retracted.

Images