Hydraulic lifting adjusting and locking device for drop test of aircraft landing gear

Abstract

The invention provides a hydraulic lifting adjustment locking device for an aircraft landing gear drop test, and the device comprises a supporting assembly which comprises a base and a support, the support is arranged on the base, and the support comprises four first vertical supports, two second vertical supports and a transverse support; the sliding frame assembly comprises a sliding frame body and a guide wheel set, the sliding frame body is used for bearing a balancing weight for testing, and the sliding frame assembly slides along the vertical support under the guiding effect of the guide wheel set; the lifting assembly comprises two lifting oil cylinders and two linear modules, each linear module comprises a sliding part and a sliding rail arranged along the second vertical support, and the sliding parts tightly hold the lifting oil cylinders through hoops so that the lifting oil cylinders can slide in the vertical direction along the sliding rails; the locking assembly is arranged on the second vertical support and locks the sliding frame assembly when the sliding frame assembly reaches the preset position. The safety assembly is arranged on the vertical support, and after the sliding frame assembly is locked, the sliding frame assembly is positioned through the safety assembly.

Description

Technical Field

[0001] This application relates to the field of aircraft landing gear testing technology, and more specifically to a hydraulic lifting adjustment locking device for aircraft landing gear drop testing. Background Technology

[0002] With the development of my country's aviation industry, the number and types of aircraft are increasing, which in turn increases the demand for aircraft landing gear testing equipment. Therefore, how to better and faster complete the relevant tests of aircraft landing gear is a problem we need to consider. Traditional aircraft landing gear drop tests are carried out by assembling weights with electric hoists. However, the stability and speed of hoisting are relatively low, which cannot meet the future development needs of the aircraft industry. Therefore, a hydraulic lifting adjustment and locking device for aircraft landing gear drop tests is proposed. Summary of the Invention

[0003] The purpose of this application is to address the technical problems in related technologies by providing a hydraulic lifting adjustment locking device for aircraft landing gear drop tests. The specific solution is as follows:

[0004] This application provides a hydraulic lifting adjustment locking device for aircraft landing gear drop tests, comprising:

[0005] A support assembly includes a base and a bracket, the bracket being disposed on the base, and the bracket including four first vertical brackets, two second vertical brackets, and a horizontal bracket;

[0006] A carriage assembly includes a carriage body and a guide wheel assembly. The carriage body is used to carry a counterweight for testing. The carriage assembly slides along the vertical support under the guidance of the guide wheel assembly.

[0007] The lifting assembly includes two lifting cylinders and two linear modules. Each linear module includes a slider and a slide rail arranged along the second vertical support. The slider holds the lifting cylinder with a clamp, so that the lifting cylinder slides vertically along the slide rail.

[0008] A locking component is provided on the second vertical support, which locks the carriage assembly when the carriage assembly reaches a preset position;

[0009] A safety component is provided on the vertical support, which positions the carriage assembly when the carriage assembly is locked.

[0010] In some embodiments, the guide wheel assembly includes four sets of first guide wheel assemblies and two sets of second guide wheel assemblies. Each set of first guide wheel assemblies includes two first guide wheels arranged vertically, and each set of second guide wheel assemblies includes two second guide wheels arranged vertically. The four sets of first guide wheel assemblies slide along the vertical direction of the four first vertical supports, and the two sets of second guide wheel assemblies slide along the vertical direction of the two second vertical supports.

[0011] In some embodiments, the first vertical support includes a first slide groove, the second vertical support includes a second slide groove, the first guide wheel assembly slides along the first slide groove, and the second guide wheel assembly slides along the second slide groove.

[0012] In some embodiments, the locking assembly includes a first positioning cylinder and a safety pin, which lock the carriage assembly when it reaches a preset position.

[0013] In some embodiments, the security component includes:

[0014] The second positioning cylinder is mounted on the second vertical support;

[0015] A locking plate is provided on the transverse support;

[0016] Positioning racks are installed on the four first vertical supports;

[0017] When the carriage assembly reaches the preset position, the second positioning cylinder pushes the locking plate to move and engage with the positioning rack to position the carriage assembly.

[0018] In some embodiments, the positioning rack has trapezoidal teeth with a tooth height of 5mm, a tooth width of 3mm, and a tooth pitch of 100mm.

[0019] In some embodiments, a positioning wheel is provided at the free end of the locking plate. Under the drive of the second positioning cylinder, the positioning wheel is engaged in the tooth groove of the positioning rack, and the fit clearance between the locking plate and the positioning rack is 0.1mm-0.3mm.

[0020] In some embodiments, the first positioning cylinder and the second positioning cylinder share the same hydraulic system, wherein the hydraulic system includes a hydraulic pump, a hydraulic valve and an oil tank, the piston rod end of the first positioning cylinder is connected to the safety pin, and the piston rod end of the second positioning cylinder is connected to the locking plate.

[0021] In some embodiments, the system further includes: four safety posts, each disposed on the base adjacent to the four first vertical supports, with anti-slip pads at the ends of the safety posts, such that when the lifting cylinder reaches the lowest point, the bottom of the slide body contacts the top of the safety posts.

[0022] In some embodiments, the two lifting cylinders are eccentrically designed so that the carriage assembly is subjected to force at two different points on both sides simultaneously.

[0023] Compared with related technologies, the above-described solutions of this application have at least the following beneficial effects:

[0024] This application provides a hydraulic lifting and adjusting locking device for aircraft landing gear drop tests. It can smoothly lift the counterweight to the test height and fix it in the test position through four pairs of locking mechanisms. The counterweight lifting process is fast and the movement is relatively smooth. The device employs a design with 12 sets of guide wheels and 6 sets of guide rail grooves. During the hydraulic lifting operation, the counterweight rises smoothly. After reaching the test height, the counterweight is fixed in the corresponding position by the rack on the column and the release cylinder. This significantly improves the efficiency of aircraft landing gear drop tests and solves the problem that traditional aircraft landing gear drop tests, which rely on electric hoists to assemble the counterweight, have relatively low stability and speed during hoisting, failing to meet the future development needs of the aircraft industry.

[0025] The hydraulic lifting adjustment locking device used in the landing gear drop test improves lifting stability and speed through the synergistic effect of the lifting components and guide wheels. Two sets of lifting cylinders are symmetrically mounted on the bottom base via bottom flanges. The linear module uses clamps to hold the lifting cylinders to ensure that the force is transmitted in the vertical direction. The 12 guide wheels of the carriage assembly roll in the grooves of the column to keep the carriage flatness ±0.5mm. The eccentric design of the lifting cylinders enables force to be applied on both sides. The hydraulic power output is stable and the guidance is precise, avoiding the swaying and deviation of electric hoisting, resulting in faster lifting speed and significantly improved stability and efficiency.

[0026] The hydraulic lifting and adjusting locking device for the aircraft landing gear drop test uses a double-fixing structure of the locking module to ensure the stability of the test position and indirectly improve the hoisting efficiency: after the slide is raised to the test height, the second positioning cylinder pushes the locking plate, and its front guide wheel engages with the tooth groove of the positioning rack on the column. At the same time, the first positioning cylinder pushes out the safety pin to form a double lock. This structure can quickly and accurately fix the slide, avoiding the time-consuming and unstable problems of electric hoisting, and is suitable for the high-efficiency testing requirements.

[0027] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description

[0028] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and are configured together with the description to explain the principles of this application. It is obvious that the drawings described below are merely some embodiments of this application, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort. In the drawings:

[0029] Figure 1 This is a schematic diagram of the overall structure of a hydraulic lifting adjustment locking device according to an exemplary embodiment.

[0030] Figure 2 This is a partial structural schematic diagram of a hydraulic lifting adjustment locking device according to an exemplary embodiment.

[0031] Figure 3 This is a partial structural schematic diagram of a hydraulic lifting adjustment locking device according to an exemplary embodiment.

[0032] Figure 4 This is a partial structural schematic diagram of a hydraulic lifting adjustment locking device according to an exemplary embodiment.

[0033] Figure 5 This is a partial structural schematic diagram of a hydraulic lifting adjustment locking device according to an exemplary embodiment.

[0034] Figure label:

[0035] Hydraulic lifting adjustment locking device 100, aircraft landing gear 200;

[0036] Support assembly 10, base 11, bracket 12, first vertical bracket 121, second vertical bracket 122, horizontal bracket 123, first slide groove 124, second slide groove 125; carriage assembly 20, carriage body 21, guide wheel assembly 22, first guide wheel assembly 221, second guide wheel assembly 222; lifting assembly 30, lifting cylinder 31, linear module 32, sliding component 321, slide rail 322; locking assembly 40, first positioning cylinder 41; safety assembly 50, second positioning cylinder 51, locking plate 52, positioning wheel 521, positioning rack 53. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this application clearer, the application will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0038] The terminology used in the embodiments of this application is for the purpose of describing particular embodiments only and is not intended to limit the application. The singular forms “a,” “the,” and “the” used in the embodiments of this application and the appended claims are also intended to include the plural forms, unless the context clearly indicates otherwise. “Multiple” generally includes at least two, and other quantifiers are similar.

[0039] It should be understood that although the terms "first," "second," "third," etc., may be used in the embodiments of this application, these descriptions should not be limited to these terms. These terms are only used to distinguish the described objects. For example, "first" may also be referred to as "second," and similarly, "second" may also be referred to as "first," without departing from the scope of the embodiments of this application. Furthermore, the terms "first," "second," "third," etc., are configured for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0040] It should be understood that the term "and / or" as used herein is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A alone, A and B simultaneously, and B alone. Additionally, the character " / " in this document generally indicates that the preceding and following related objects have an "or" relationship. The singular forms "a," "the," and "the" are also intended to include the plural forms unless the context clearly indicates otherwise.

[0041] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0042] It should also be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that an article or device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such an article or device. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the article or device that includes said element.

[0043] The optional embodiments of this application are described in detail below with reference to the accompanying drawings.

[0044] like Figure 1As shown in the illustration, this application provides a hydraulic lifting adjustment and locking device 100 for drop testing of an aircraft landing gear 200. The hydraulic lifting adjustment and locking device 100 includes: a support assembly 10, a slide assembly 20, a lifting assembly 30, a locking assembly 40, and a safety assembly 50. The support assembly 10 supports the slide assembly 20. The slide assembly 20, after being equipped with a configuration block, applies force to the aircraft landing gear 200 for drop testing. The lifting assembly 30 provides lifting force to allow the slide assembly 20 to slide vertically. The locking assembly 40 locks the slide assembly 20 after it reaches a predetermined height. The safety assembly 50 further locks the slide assembly 20 for safety protection.

[0045] Specifically, such as Figure 2 , Figure 3 As shown, the support assembly 10 includes a base 11 and a bracket 12. The bracket 12 is disposed on the base 11 and includes four first vertical brackets 121, two second vertical brackets 122, and a transverse bracket 123. The transverse bracket 123 connects the four first vertical brackets 121 and the two second vertical brackets 122. The four first vertical brackets 121 are located at the four corners of the rectangle, and the two second vertical brackets 122 are located at the middle of the first vertical brackets 121 at both ends. The carriage assembly 20 slides up and down within the rectangular space enclosed by the bracket 12 and includes a carriage body 21 and a guide wheel assembly 22. The carriage body 21 is used to support the counterweight for the test, and the carriage assembly 20 slides along the vertical brackets 121 under the guidance of the guide wheel assembly 22. The lifting assembly 30 includes two lifting cylinders 31 and two linear modules 32. Each lifting cylinder 31 and each linear module 32 is located adjacent to the second vertical support 122. Each linear module 32 includes a slider 321 and a slide rail 322 arranged along the second vertical support 122. The slider 321 clamps the lifting cylinder 31 with a clamp, so that the lifting cylinder 31 slides vertically along the slide rail 322, ensuring that the force of the two lifting cylinders 31 is transmitted vertically, avoiding the phenomenon of the slide assembly 20 derailing due to the deviation of the hydraulic lifting force during the lifting process. This structure makes the slide assembly 20 always maintain vertical movement during the lifting process, improving the stability of the lifting process. The locking component 40 is disposed on the second vertical support 122, and locks the carriage assembly 20 when it reaches a preset position; the safety component 50 is disposed on the vertical support 121, and positions the carriage assembly 20 after it is locked.

[0046] In some embodiments, such as Figure 4As shown, the guide wheel assembly 22 includes four sets of first guide wheel assemblies 221 and two sets of second guide wheel assemblies 222. Each set of first guide wheel assemblies 221 includes two first guide wheels arranged vertically, and each set of second guide wheel assemblies 222 includes two second guide wheels arranged vertically. The four sets of first guide wheel assemblies 221 slide along the vertical direction of the four first vertical supports 121, and the two sets of second guide wheel assemblies 222 slide along the vertical direction of the two second vertical supports 122. In some embodiments, the first vertical support 121 includes a first groove 124, and the second vertical support 122 includes a second groove 125. The first guide wheel assemblies 221 slide along the first groove 124, and the second guide wheel assemblies 222 slide along the second groove 125. Each guide wheel is in close contact with the inner wall of each slide groove. When the slide assembly 20 rises, the guide wheels roll in the slide groove, ensuring that the flatness of the slide assembly 20 is kept within ±0.5mm. The setting of 12 sets of guide wheels not only restricts the possibility of the slide assembly 20 moving in other directions, but also ensures the overall stability of the slide assembly 20 during the lifting process, so that the slide assembly 20 can move smoothly in the vertical direction, avoiding the shaking and displacement problems common in traditional test equipment during the lifting process.

[0047] In some embodiments, two sets of lifting cylinders 31 are symmetrically mounted on the bottom base 11 via a flange at the bottom. The two lifting cylinders 31 are eccentrically designed, so that the slide assembly 20 is subjected to force at two different points on both sides at the same time, which further improves the stability of the slide assembly 20 during lifting. When the lifting cylinders 31 are working, the linear module 32 ensures that the force is guided in the vertical direction, while the guide wheel rolls in the slide groove to ensure that the slide assembly 20 moves only in the vertical direction. This coordinated lifting and guiding method allows the counterweight to be lifted smoothly to the test height, making full preparation for subsequent locking and fixing, and significantly improving the efficiency and reliability of the aircraft landing gear drop test.

[0048] In some embodiments, such as Figure 5 As shown, the locking component 40 includes a first positioning cylinder 41 and a safety pin. When the carriage assembly 20 reaches a preset position, the carriage assembly 20 is locked by the first positioning cylinder 41 and the safety pin.

[0049] In some embodiments, the safety component 50 includes: a second positioning cylinder 51 disposed on the second vertical support 122; a locking plate 52 disposed on the horizontal support 123; and a positioning rack 53 disposed on the four first vertical supports 121. When the carriage assembly 20 reaches a preset position, the second positioning cylinder 51 pushes the locking plate 52 to move and engage with the positioning rack 53 to position the carriage assembly 20.

[0050] The positioning rack 53 is 2000mm long, has trapezoidal teeth, a tooth height of 5mm, a tooth width of 3mm, and a tooth pitch of 100mm, and is fixedly installed on the opposite side of the first vertical support 121.

[0051] In some embodiments, a positioning wheel 521 is provided at the free end of the locking plate 52. Under the drive of the second positioning cylinder 51, the positioning wheel 521 is engaged in the tooth groove of the positioning rack 53, and the fit clearance between the locking plate 52 and the positioning rack 53 is 0.1mm-0.3mm.

[0052] When the carriage assembly 20 rises to the corresponding experimental height, the second positioning cylinder 51 extends, pushing the locking plate 52 forward. The guide wheel in front of the locking plate 52 engages in the tooth groove of the positioning rack 53, fixing the carriage assembly 20 in the corresponding position. The clearance between the locking plate 52 and the positioning rack 53 is controlled within the range of 0.1-0.3mm, ensuring the accuracy and stability of the locking. At the same time, the first positioning cylinder 41 extends, pushing the safety pin to extend. After the safety pin reaches the corresponding position, the carriage assembly 20 can smoothly fall on the safety pin, forming a double locking mechanism, which further enhances the stability of the carriage assembly 20 during the test.

[0053] In some embodiments, the first positioning cylinder 41 and the second positioning cylinder 51 share the same hydraulic system, wherein the hydraulic system includes a hydraulic pump, a hydraulic valve and an oil tank, the piston rod end of the first positioning cylinder 41 is connected to the safety pin, and the piston rod end of the second positioning cylinder 51 is connected to the locking plate 52.

[0054] In some embodiments, the hydraulic lifting adjustment locking device 100 further includes four safety posts 60, which are respectively disposed on the base 11 adjacent to the four first vertical supports 121. The ends of the safety posts 60 are provided with anti-slip pads. When the lifting cylinder 31 reaches the lowest point, the bottom of the slide body 21 contacts the top of the safety post 60, and the contact surface is a planar contact, which provides a safety guarantee for the operator to operate the equipment. This safety design ensures that even if an accident occurs during the lifting process, the slide assembly 20 can be placed stably on the safety post 60 to prevent equipment damage and personnel injury, and greatly improves the safety of the test process.

[0055] The lifting process of the hydraulic lift adjustment lock device during the landing gear drop test of this aircraft is as follows:

[0056] At the start of the test, the hydraulic system is activated, and two sets of lifting cylinders 4 are symmetrically mounted on the top of the bottom base 1 via flanges at the bottom, providing lifting power. Two sets of linear modules 5 clamp the lifting cylinders 4 with clamps to ensure that the force is transmitted in the vertical direction, preventing the carriage 3 from derailing due to hydraulic lifting force deviation during the lifting process. The eight sets of guide wheels 11 at the four corners of the carriage 3 roll in the pulley grooves 12 of the column 2, keeping the flatness of the carriage 3 within ±0.5mm. The two sets of lifting cylinders 4 adopt an eccentric design, so that the two sides of the carriage 3 are simultaneously subjected to force at two different points, improving the stability of the carriage 3 during rise. The carriage 3 is smoothly lifted to the predetermined test height, and the guide wheels 11 roll in the pulley grooves 12 to ensure that the carriage 3 moves only in the vertical direction.

[0057] The positioning and locking process of the hydraulic lift adjustment lock device during the landing gear drop test of this aircraft is as follows:

[0058] When the slide 3 reaches the predetermined test height, the second positioning cylinder 9 extends, pushing the locking plate 7 forward. The guide wheel 11 in front of the locking plate 7 engages in the tooth groove of the positioning rack 6. The positioning rack 6 is a trapezoidal rack with a length of 2000mm, a tooth pitch of 100mm, a tooth height of 5mm, and a tooth width of 3mm. The clearance between the locking plate 7 and the positioning rack 6 is controlled within the range of 0.1-0.3mm to ensure the accuracy and stability of the locking. At the same time, the first positioning cylinder 8 extends, pushing the safety pin to extend. After the safety pin reaches the corresponding position, the slide 3 smoothly falls above the safety pin, forming a double locking mechanism. The slide 3 is double-locked at the test height to ensure that it will not shift during the test.

[0059] The test procedure for the hydraulic lift adjustment lock device during the landing gear drop test of this aircraft is as follows:

[0060] At the start of the test, the counterweight was placed on the slide assembly 20 to conduct a landing gear drop test. During the test, the slide assembly 20 was kept stable by a double locking mechanism to ensure the accuracy of the test data. During the test, the flatness of the slide assembly 20 was kept within ±0.5mm, and the guide wheel rolled in the slide groove to ensure the accuracy of the test.

[0061] The release and descent process of the hydraulic lift adjustment lock device during the landing gear drop test of this aircraft is as follows:

[0062] After the test command is issued, the first positioning cylinder 41 retracts, and the safety pin retracts; the second positioning cylinder 51 drives the locking plate 52 to retract, and the guide wheel disengages from the tooth groove of the positioning rack 53; the lifting cylinder 31 begins to descend, and the carriage assembly 20 begins to descend; when the carriage assembly 20 descends to the lowest point, its bottom contacts the top of the safety post 60, and the contact surface is a flat contact, ensuring that the carriage assembly 20 is placed stably; after the lifting cylinder 31 reaches the lowest point, the carriage assembly 20 is stably placed on the safety post 60, preparing for the next test.

[0063] In summary, the hydraulic lifting adjustment and locking device for aircraft landing gear drop tests enhances lifting stability and speed through the synergistic effect of the lifting assembly and the slide assembly. Two sets of lifting cylinders are symmetrically mounted on the bottom base via bottom flanges. The linear module uses clamps to hold the lifting cylinders, ensuring that the force is transmitted vertically. The eight guide wheels at the four corners and the four guide wheels at both ends of the slide assembly roll within the grooves of the column, maintaining the flatness of the slide assembly at ±0.5mm. Furthermore, the eccentric design of the lifting cylinders enables force distribution on both sides. The hydraulic power output is stable and the guidance is precise, avoiding the swaying and deviation of electric hoisting, resulting in faster lifting speeds and significantly improved stability and efficiency.

[0064] Furthermore, the hydraulic lifting and locking device for aircraft landing gear drop tests utilizes a double-fixing structure of the locking module to ensure stable test position and indirectly improve hoisting efficiency: after the slide assembly is raised to the test height, the second positioning cylinder pushes the locking plate, and its front guide wheel engages with the tooth groove of the positioning rack on the column. At the same time, the first positioning cylinder pushes out the safety pin to form a double lock. This structure can quickly and accurately fix the slide assembly, avoiding the time-consuming and unstable problems of electric hoisting, adapting to the high-efficiency requirements of testing, and solving the problem that traditional aircraft landing gear drop tests are completed by electric hoisting and assembling weights, which has relatively low stability and hoisting speed, and cannot meet the future development needs of the aircraft industry.

[0065] Finally, it should be noted that 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 systems or apparatus disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the descriptions are relatively simple, and relevant parts can be referred to the method section.

[0066] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.

Claims

1. A hydraulic lifting adjustment locking device for aircraft landing gear drop testing, characterized in that, include: The support assembly (10) includes a base (11) and a bracket (12), wherein the bracket (12) is disposed on the base (11), and the bracket (12) includes four first vertical brackets (121), two second vertical brackets (122) and a horizontal bracket (124); The carriage assembly (20) includes a carriage body (21) and a guide wheel assembly (22). The carriage body (21) is used to carry the counterweight for the test. The carriage assembly slides along the vertical support (121) under the guidance of the guide wheel assembly (22). The lifting assembly (30) includes two lifting cylinders (31) and two linear modules (32). Each linear module (32) includes a slider (321) and a slide rail (322) arranged along the second vertical support (122). The slider (321) clamps the lifting cylinder (31) with a clamp, so that the lifting cylinder (31) slides in the vertical direction along the slide rail (322). A locking component (40) is provided on the second vertical support (122) to lock the carriage assembly when the carriage assembly reaches a preset position; A safety component (50) is provided on the vertical support (121) to position the carriage assembly when the carriage assembly is locked.

2. The hydraulic lifting adjustment locking device for aircraft landing gear drop test according to claim 1, characterized in that: The guide wheel assembly (22) includes four sets of first guide wheel assemblies (221) and two sets of second guide wheel assemblies (222). Each set of first guide wheel assemblies (221) includes two first guide wheels arranged vertically, and each set of second guide wheel assemblies (222) includes two second guide wheels arranged vertically. The four sets of first guide wheel assemblies (221) slide vertically along the four first vertical supports (121), and the two sets of second guide wheel assemblies (222) slide vertically along the two second vertical supports (122).

3. The hydraulic lifting adjustment locking device for aircraft landing gear drop test according to claim 2, characterized in that: The first vertical support (121) includes a first slide groove (124), the second vertical support (122) includes a second slide groove (125), the first guide wheel assembly (13) slides along the first slide groove (124), and the second guide wheel assembly (14) slides along the second slide groove (125).

4. The hydraulic lifting adjustment locking device for aircraft landing gear drop test according to claim 1, characterized in that: The locking assembly includes a first positioning cylinder (41) and a safety pin. When the carriage assembly reaches a preset position, the carriage assembly is locked by the first positioning cylinder (41) and the safety pin.

5. The hydraulic lifting adjustment locking device for aircraft landing gear drop test according to claim 4, characterized in that: The security components include: The second positioning cylinder (51) is mounted on the second vertical support (122); Locking plate (52) is provided on the transverse support (124); Positioning racks (53) are provided on the four first vertical supports (121); When the carriage assembly reaches the preset position, the second positioning cylinder (51) pushes the locking plate (52) to move and engage with the positioning rack (53) to position the carriage assembly.

6. The hydraulic lifting adjustment locking device for aircraft landing gear drop test according to claim 5, characterized in that: The positioning rack (53) has trapezoidal teeth with a tooth height of 5mm, a tooth width of 3mm, and a tooth pitch of 100mm.

7. The hydraulic lifting adjustment locking device for aircraft landing gear drop test according to claim 5, characterized in that: The free end of the locking plate (52) is provided with a positioning wheel (521). Under the drive of the second positioning cylinder (51), the positioning wheel (521) is engaged in the tooth groove of the positioning rack (53). The fit gap between the locking plate (52) and the positioning rack (53) is 0.1mm-0.3mm.

8. The hydraulic lifting adjustment locking device for aircraft landing gear drop test according to claim 5, characterized in that: The first positioning cylinder (41) and the second positioning cylinder (51) share the same hydraulic system, wherein the hydraulic system includes a hydraulic pump, a hydraulic valve and an oil tank, the piston rod end of the first positioning cylinder (41) is connected to the safety pin, and the piston rod end of the second positioning cylinder (51) is connected to the locking plate (52).

9. The hydraulic lifting adjustment locking device for aircraft landing gear drop test according to claim 1, characterized in that: Also includes: Four safety posts (60) are respectively placed on the base (11) adjacent to the four first vertical supports (121). The ends of the safety posts (60) are provided with anti-slip pads. When the lifting cylinder (31) reaches the lowest point, the bottom of the slide body (21) contacts the top of the safety posts (60).

10. The hydraulic lifting adjustment locking device for aircraft landing gear drop test according to claim 1, characterized in that: The two lifting cylinders (31) are eccentrically designed so that the carriage assembly is subjected to force at two different points on both sides at the same time.

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