A compression strength detection system and method for landing gear struts

Abstract

The application belongs to the technical field of aircraft accessory production, and particularly relates to a compression strength detection system and method for landing gear support rods, which comprises a clamping assembly, an inner seam welding assembly, an outer seam welding assembly, an inner support pipe plugging assembly, an inner support pipe compression strength detection assembly and an outer support pipe compression strength detection assembly; the clamping assembly clamps the combined landing gear support rods in a ring array; the inner seam welding assembly is used for welding the ring-shaped inner seam between the inner support pipe and the ear seat component; the outer seam welding assembly is used for welding the ring-shaped outer seam between the outer support pipe and the ear seat component; the inner support pipe plugging assembly and the inner support pipe compression strength detection assembly are used for detecting the compression strength of the inner support pipe; and the outer support pipe compression strength detection assembly is used for detecting the compression strength of the outer support pipe. The application can meet the compression strength detection requirements of the outer support pipe and the inner support pipe of the combined landing gear support rods, and verify the influence of the welding process on the compression capacity of the rods.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft accessory production, and particularly relates to a compression strength detection system and method for a landing gear stay rod piece. BACKGROUND

[0002] The landing gear stay rod is an auxiliary load-bearing component in the process of aircraft taking off and landing, and its compression strength is directly related to flight safety and structural reliability. When the aircraft lands, the landing gear stay rod needs to bear impact load several times the weight of the fuselage. If the compression performance of the landing gear stay rod is insufficient, the rod may be buckled and deformed or even broken, which may cause disastrous consequences such as collapse of the landing gear. Therefore, it is necessary to quantitatively evaluate the stay rod piece by using the compression strength detection system. The detection can confirm the stability of the stay rod piece under the limit load, ensure that the stay rod piece meets the safety margin required by the airworthiness standard, and avoid sudden failure caused by material defects or fatigue cracks.

[0003] The compression strength detection system for the traditional landing gear stay rod piece has the following deficiencies: first, it cannot simultaneously meet the compression strength detection requirements of the outer stay tube and the inner stay tube of the combined landing gear stay rod piece; second, it cannot meet the compression strength change detection requirements of the outer stay tube and the inner stay tube of the combined landing gear stay rod piece before and after welding, and cannot verify the influence of the welding process on the compression capacity of the rod piece during the manufacturing process.

[0004] Therefore, the inventor expects to design a compression strength detection system and method for a landing gear stay rod piece. SUMMARY

[0005] The application aims to overcome at least one of the above problems in the prior art, and provide a compression strength detection system and method for a landing gear stay rod piece.

[0006] To achieve the above technical purposes and effects, the application is implemented by the following technical solutions:

[0007] The application provides a compression strength detection system for a landing gear stay rod piece, which comprises clamping assemblies, inner seam welding assemblies, outer seam welding assemblies, inner stay tube plugging assemblies, inner stay tube compression strength detection assemblies and outer stay tube compression strength detection assemblies.

[0008] The clamping assemblies are symmetrical and are arranged in pairs, and the two clamping assemblies jointly clamp a combined landing gear stay rod piece arranged in a ring array. The combined landing gear stay rod piece comprises an ear seat member, an inner stay tube, an outer stay tube, a spring mounting seat and a supporting spring.

[0009] The inner seam welding assemblies are arranged in pairs and are respectively arranged on the adjacent clamping assemblies. The inner seam welding assemblies are used for welding the annular inner seam between the inner stay tube and the ear seat member.

[0010] There are two external seam welding assemblies, which are respectively installed on adjacent clamping assemblies. The external seam welding assemblies are used to weld the annular external seam between the external support tube and the lug member.

[0011] The inner support tube sealing assembly and the inner support tube compressive strength testing assembly are symmetrically installed on the adjacent clamping assembly and are used together to test the compressive strength of the inner support tube.

[0012] The compressive strength testing component for the outer support tube is positioned above the area between the two clamping components and is used to test the compressive strength of the outer support tube.

[0013] Furthermore, in the above-mentioned landing gear strut compressive strength testing system, there are two lug members, with an inner support tube and an outer support tube sandwiched between the two lug members. A support spring is installed in the area between the inner support tube and the outer support tube, and spring mounting seats that can be threadedly connected to the lug members are fixed at both ends of the support spring.

[0014] The ear seat component includes a groove-shaped ear seat, the outer wall of the web of the groove-shaped ear seat is provided with a protruding tube, the inner diameter of the protruding tube is equal to the outer diameter of the inner support tube, the web of the groove-shaped ear seat is provided with an external through hole, and the diameter of the external through hole is equal to the inner diameter of the inner support tube, the outer side of the protruding tube is provided with an external thread, and each of the two side plates of the groove-shaped ear seat is provided with a hinge hole.

[0015] The spring mounting base includes an annular seat with an internal thread groove that mates with the external threaded portion. The outer diameter of the annular seat is equal to the inner diameter of the outer support tube. An internal through hole is provided at the inner end of the annular seat located in the internal thread groove, and the diameter of the internal through hole is equal to the outer diameter of the inner support tube.

[0016] Furthermore, in the above-mentioned landing gear strut compressive strength testing system, the clamping assembly includes a base plate, an outer rotary driver, an outer cover, an annular end plate, positioning blocks, and a locking mechanism. The base plate is mounted with an outer cover with an annular end plate via the outer rotary driver. Several positioning blocks are provided circumferentially on the outer side of the annular end plate. A locking mechanism is installed inside the outer cover.

[0017] The annular end plate has a first through hole on the back side of the positioning block, and a second through hole is provided in the positioning block. The outer side of the positioning block has a snap-fit ​​groove for facilitating the snap-fit ​​of the ear seat component and a locking groove that is perpendicularly connected to the inner snap-fit ​​groove. The specifications of the locking groove are matched with the specifications of the hinge hole.

[0018] The locking mechanism includes an inner cover, a support block, a locking rod, an inner rotary drive, and a movable disc. The inner wall of the inner end plate of the inner cover supports the movable disc via the inner rotary drive. The outer side of the movable disc is provided with several arc-shaped push grooves along the circumference. The outer end plate of the inner cover is provided with several radial sliding grooves along the circumference. The support block slides and is restricted in the radial sliding grooves. The inner end of the support block is provided with an anti-dislodgement head that slides and is restricted in the arc-shaped push grooves. The outer end of the support block is equipped with a locking rod that can extend into the locking groove.

[0019] Furthermore, in the aforementioned landing gear strut compressive strength testing system, the inner seam welding assembly includes a first drive push rod, a rotary joint, a square shaft, a first welding head, a first bracket, a first motor, a first belt drive component, and a torsion sleeve. The cylinder of the first drive push rod is mounted on the base plate, and the movable end of the first drive push rod is connected to one end of the square shaft via the rotary joint. The other end of the square shaft is equipped with the first welding head. The first motor is fixed to the base plate via the first bracket, and the output shaft of the first motor is connected to the torsion sleeve via the first belt drive component. The torsion sleeve is sleeved on the outside of the square shaft, and the torsion sleeve is provided with movable support by the first bracket.

[0020] Furthermore, in the aforementioned landing gear strut compressive strength testing system, the outer seam welding assembly includes a second bracket, a carrier, a second motor, a semi-hinge, a semi-circular plate, an arc-shaped slide rail, a slider, and a second welding head. The carrier is fixed to the base plate by the second bracket. The second motor is symmetrically installed on the outer side of the carrier. A semi-hinge is installed at the output end of the second motor. Two semi-hinges are spliced ​​together to form a hinged joint. The semi-hinge is connected to a semi-circular plate. An arc-shaped slide rail is provided on the inner side of the semi-circular plate. Two arc-shaped slide rails are joined together to form a circular slide rail. The slider is installed on one of the arc-shaped slide rails and forms an arc-shaped guide rail pair with it. A second welding head is installed on the outer side of the slider.

[0021] Furthermore, in the above-mentioned landing gear strut compressive strength testing system, the inner strut sealing assembly includes a second drive push rod and a solid plug. The cylinder of the second drive push rod is fixed on the corresponding base plate, and the movable end of the second drive push rod is equipped with a solid plug.

[0022] Furthermore, in the aforementioned landing gear strut compressive strength testing system, the inner strut compressive strength testing component includes a third drive push rod, a coupling, a hollow shaft, a hollow plug, a pressurized air pump, a pressurized air pipe, and a pressure gauge. The cylinder of the third drive push rod and the pressurized air pump are fixed on corresponding base plates. The movable end of the third drive push rod is connected to one end of the hollow shaft via the coupling. A hollow plug is installed at the other end of the hollow shaft. The side end of the hollow shaft is connected to the air supply end of the pressurized air pump via the pressurized air pipe. A pressure gauge with a built-in pressure sensor is installed on the pressurized air pipe.

[0023] Furthermore, in the aforementioned landing gear strut compressive strength testing system, the outer strut compressive strength testing assembly includes a slide rail base, a linear guide pair, a first mounting plate, a third motor, a second mounting plate, a straightening ring sleeve, a straightening ring, a drop hammer box, an annular flexible pad, a locking push rod, a drop hammer block, and a drop hammer punch. The slide rail of the linear guide pair is fixed to the slide rail base. The first mounting plate is fixed to the outside of the slider of the linear guide pair. The second mounting plate is mounted on the first mounting plate via the third motor. A straightening mechanism consisting of a straightening ring sleeve and a straightening ring is installed between the first mounting plate and the second mounting plate. A drop hammer box is installed on the outer side of the second mounting plate. The two end plates of the drop hammer box are symmetrically provided with drop hammer punches. Annular flexible pads are installed at both ends of the inner cavity of the drop hammer box. Locking push rods are symmetrically installed on the outer side of the drop hammer box. A drop hammer block is movable inside the drop hammer box. Drop hammer punches are symmetrically installed on both sides of the drop hammer block. A positioning hole is provided on the rear side of the drop hammer block. Guide holes corresponding to the positions of the positioning holes are symmetrically provided on the back plate of the drop hammer box. Locking push rods are symmetrically installed on the back plate of the drop hammer box. The movable end of the locking push rod can extend into the positioning hole of the drop hammer block through the guide hole.

[0024] Furthermore, the aforementioned landing gear strut compressive strength testing system also includes a controller, which is connected to the clamping assembly, the inner seam welding assembly, the outer seam welding assembly, the inner strut sealing assembly, the inner strut compressive strength testing assembly, and the outer strut compressive strength testing assembly, respectively. The controller is connected to the back-end terminal via a wireless communication module.

[0025] The present invention also provides a method for testing the compressive strength of landing gear struts, which is based on the above-mentioned system for testing the compressive strength of landing gear struts, and includes the following steps:

[0026] S1. Two clamping components are used to jointly clamp the combined landing gear struts distributed in a ring array.

[0027] S2. Use the inner support tube sealing assembly and the inner support tube compressive strength testing assembly to test the compressive strength of the inner support tube that is not welded to the ear seat component; use the outer support tube compressive strength testing assembly to test the compressive strength of the outer support tube that is not welded to the ear seat component.

[0028] S3. Use the inner seam welding assembly to weld the annular inner seam between the inner support tube and the ear seat component; use the outer seam welding assembly to weld the annular outer seam between the outer support tube and the ear seat component.

[0029] S4. Use the inner support tube sealing assembly and the inner support tube compressive strength testing assembly to test the compressive strength of the inner support tube welded to the ear seat component; use the outer support tube compressive strength testing assembly to test the compressive strength of the outer support tube welded to the ear seat component.

[0030] The beneficial effects of this invention are:

[0031] 1. Meets multiple testing needs

[0032] This system can simultaneously meet the compressive strength testing requirements of both the outer and inner struts of composite landing gear struts. By using an inner strut sealing assembly, an inner strut compressive strength testing assembly, and an outer strut compressive strength testing assembly, the compressive strength of the inner and outer struts is tested independently, solving the problem that traditional systems cannot test both types of components simultaneously. Furthermore, it can meet the requirement of testing the compressive strength changes of composite landing gear struts before and after welding. Testing the inner and outer struts before welding (before welding to the lug assembly) and testing again after welding verifies the impact of the welding process on the strut's compressive strength, providing data support for optimizing the manufacturing process.

[0033] 2. High degree of integration and automation

[0034] The entire testing system integrates multiple functional components, each connected to a controller. The controller, in turn, connects to a back-end terminal via a wireless communication module, enabling automated control and data transmission throughout the testing process. Operators can remotely monitor and control the testing process through the back-end terminal, improving efficiency and reducing human error.

[0035] Of course, any product implementing this invention does not necessarily need to achieve all of the above advantages at the same time. Attached Figure Description

[0036] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0037] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0038] Figure 2 This is a schematic diagram of the internal structure of the combined landing gear strut in this invention;

[0039] Figure 3 This is a schematic diagram of the external structure of the combined landing gear strut in this invention;

[0040] Figure 4 This is an exploded view of the combined landing gear strut in this invention.

[0041] Figure 5 This is a schematic diagram of the clamping component in the present invention;

[0042] Figure 6 This is a schematic diagram of the locking mechanism in this invention;

[0043] Figure 7 This is a schematic diagram of the clamping component in the present invention;

[0044] Figure 8 This is a schematic diagram of the internal seam welding assembly in this invention;

[0045] Figure 9 This is an exploded view of the internal seam welding assembly in this invention;

[0046] Figure 10 This is a schematic diagram of the unused state of the inner seam welding assembly in this invention;

[0047] Figure 11 This is a schematic diagram showing the usage state of the inner seam welding assembly in this invention;

[0048] Figure 12 This is a schematic diagram of the internal support tube sealing assembly in this invention;

[0049] Figure 13 This is a schematic diagram of the internal support tube compressive strength testing component in this invention;

[0050] Figure 14 This is a schematic diagram of the main structure of the external support tube compressive strength testing component in this invention;

[0051] Figure 15 This is a side view of the compressive strength testing component for the external support tube in this invention.

[0052] Figure 16 This is a connection block diagram of the main components in this invention;

[0053] In the attached diagram, the components represented by each number are as follows:

[0054] 1-Clamping assembly, 101-Baseboard, 102-Outer rotary actuator, 103-Outer cover, 104-Annular end plate, 105-Positioning block, 106-First through hole, 107-Second through hole, 108-Snap-fit ​​groove, 109-Locking groove, 110-Inner cover, 111-Support block, 112-Locking rod, 113-Inner rotary actuator, 114-Moving disk, 115-Radial slide groove;

[0055] 2-Inner seam welding assembly, 201-First drive push rod, 202-Rotary joint, 203-Square shaft, 204-First welding head, 205-First bracket, 206-First motor, 207-First belt drive component, 208-Torsion sleeve;

[0056] 3-External seam welding assembly, 301-Second bracket, 302-Carrier, 303-Second motor, 304-Half hinge, 305-Semi-circular plate, 306-Arc-shaped slide rail, 307-Slider, 308-Second welding head;

[0057] 4-Inner support tube sealing assembly, 401-Second drive push rod, 402-Solid plug;

[0058] 5-Inner support tube compressive strength testing component, 501-Third drive push rod, 502-Coupling, 503-Hollow shaft, 504-Hollow plug, 505-Pressurizing air pump, 506-Pressurizing air pipe, 507-Pressure gauge;

[0059] 6-External support tube compressive strength testing component, 601-Slide rail base frame, 602-Linear guide rail pair, 603-First mounting plate, 604-Third motor, 605-Second mounting plate, 606-Straightening ring sleeve, 607-Straightening ring, 608-Falling hammer box, 609-Falling hammer punch, 610-Annular flexible pad, 611-Locking push rod, 612-Falling hammer block, 613-Falling hammer punch rod;

[0060] 7-Combined landing gear strut, 71-Ear mount assembly, 711-Slotted ear mount, 712-Protruding tube, 713-External threaded part, 714-Hinge hole, 715-External through hole, 72-Inner support tube, 73-External support tube, 74-Spring mounting seat, 741-Annular seat, 742-Internal threaded groove, 743-Internal through hole, 75-Support spring;

[0061] 8-Controller. Detailed Implementation

[0062] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0063] like Figure 1 As shown, this embodiment provides a compressive strength testing system for landing gear struts, including a clamping assembly 1, an inner seam welding assembly 2, an outer seam welding assembly 3, an inner strut sealing assembly 4, an inner strut compressive strength testing assembly 5, and an outer strut compressive strength testing assembly 6. There are two clamping assemblies 1, symmetrically distributed, which together clamp a combined landing gear strut 7 arranged in a circular array. The distance between the two clamping assemblies 1 can be adjusted as needed; at least one clamping assembly 1 is displaced by a moving mechanism to achieve distance adjustment. Figure 2As shown, the combined landing gear strut 7 includes a lug member 71, an inner strut tube 72, an outer strut tube 73, a spring mounting base 74, and a support spring 75. There are two inner seam welding assemblies 2, each mounted on an adjacent clamping assembly 1. The inner seam welding assemblies 2 are used to weld the annular inner seam between the inner strut tube 72 and the lug member 71. There are also two outer seam welding assemblies 3, each mounted on an adjacent clamping assembly 1. The outer seam welding assemblies 3 are used to weld the annular outer seam between the outer strut tube 73 and the lug member 71. An inner strut tube sealing assembly 4 and an inner strut tube compressive strength testing assembly 5 are symmetrically mounted on adjacent clamping assemblies 1, and are used together to test the compressive strength of the inner strut tube 72. An outer strut tube compressive strength testing assembly 6 is located above the area between the two clamping assemblies 1, and is used to test the compressive strength of the outer strut tube 73.

[0064] like Figures 2-4 As shown, the combined landing gear strut 7 includes two lug members 71, an inner strut tube 72, an outer strut tube 73, two spring mounting seats 74, and a support spring 75. The inner strut tube 72 and the outer strut tube 73 are sandwiched between the two lug members 71. The support spring 75 is installed in the area between the inner strut tube 72 and the outer strut tube 73. Both ends of the support spring 75 are fixed with spring mounting seats 74 that can be threadedly connected to the lug members 71. The lug member 71 includes a slotted lug 711. The outer wall of the web of the slotted lug 711 has a protruding tube 712. The inner diameter of the protruding tube 712 is equal to the outer diameter of the inner strut tube 72. The web of the slotted lug 711 has an external through hole 715, the diameter of which is equal to the inner diameter of the inner strut tube 72. The outer side of the protruding tube 712 has an external threaded portion 713. Each of the two side plates of the slotted lug 711 has a hinge hole 714. The spring mounting seat 74 includes an annular seat 741, in which an internal thread groove 742 is provided to mate with the external thread portion 713. The outer diameter of the annular seat 741 is equal to the inner diameter of the outer support tube 73. An inner through hole 743 is provided at the inner end of the annular seat 741 located in the internal thread groove 742. The diameter of the inner through hole 743 is equal to the outer diameter of the inner support tube 72.

[0065] In the combined landing gear strut 7, the two lug members 71 are pre-assembled into an inner support assembly consisting of a support spring 75 and spring mounting seats 74 on both sides. This facilitates reliable clamping of the inner support tube 72 and the outer support tube 73 before welding the inner and outer annular seams. Simultaneously, the support spring 75 provides internal support for the outer support tube 73 and external support for the inner support tube 72. This method helps improve the overall compressive strength of the combined landing gear strut 7 after welding.

[0066] like Figures 5-6As shown, the clamping assembly 1 includes a base plate 101, an outer rotary actuator 102, an outer cover 103, an annular end plate 104, positioning blocks 105, and a locking mechanism. The base plate 101 is mounted with the outer cover 103, which has an annular end plate 104, via the outer rotary actuator 102. Several positioning blocks 105 are circumferentially formed on the outer side of the annular end plate 104, and a locking mechanism is installed inside the outer cover 103. A first through hole 106 is formed on the back side of the annular end plate 104 near the positioning blocks 105, and a second through hole 107 is formed in the positioning blocks 105. The diameters of the first through hole 106 and the second through hole 107 are equal to the inner diameter of the inner support tube 72. The outer side of the positioning blocks 105 has an inwardly formed engagement groove 108 for facilitating engagement with the ear seat member 71, and a locking groove 109 perpendicularly communicating with the inner engagement groove 108. The specifications of the locking groove 109 are matched with the specifications of the hinge hole 714. The locking mechanism includes an inner cover 110, a support block 111, a locking rod 112, an inner rotary drive 113, and a movable disc 114. The inner wall of the inner end plate of the inner cover 110 is supported by the inner rotary drive 113. The outer side of the movable disc 114 is provided with several arc-shaped push grooves along the circumference. The outer end plate of the inner cover 110 is provided with several radial sliding grooves 115 along the circumference. The support block 111 is slidably restricted in the radial sliding grooves 115. The inner end of the support block 111 is provided with an anti-dislodgement head that is slidably restricted in the arc-shaped push groove. The outer end of the support block 111 is equipped with a locking rod 112 that can extend into the locking groove 109.

[0067] Working principle of clamping assembly 1: When the locking mechanism is working, the inner rotary drive 113 drives the movable disk 114 to rotate. The arc-shaped push groove on the movable disk 114 pushes the support block 111 to slide in the radial slide groove 115. The locking rod 112 at the outer end of the support block 111 extends into the locking groove 109, thereby locking the ear seat component 71. Thus, the two clamping assemblies 1 together clamp the combined landing gear support rods 7 arranged in a ring array. The outer rotary drive 102 can drive the clamped combined landing gear support rods 7 to rotate circumferentially.

[0068] like Figure 7 As shown, the inner seam welding assembly 2 includes a first drive push rod 201, a rotary joint 202, a square shaft 203, a first welding head 204, a first bracket 205, a first motor 206, a first belt drive component 207, and a torsion sleeve 208. The cylinder of the first drive push rod 201 is mounted on the base plate 101. The movable end of the first drive push rod 201 is connected to one end of the square shaft 203 via the rotary joint 202. The other end of the square shaft 203 is equipped with the first welding head 204. The first motor 206 is fixed to the base plate 101 via the first bracket 205. The output shaft of the first motor 206 is connected to the torsion sleeve 208 via the first belt drive component 207. The torsion sleeve 208 is sleeved on the outside of the square shaft 203 and is movably supported by the first bracket 205.

[0069] Working principle of inner seam welding assembly 2: During operation, the first drive push rod 201 pushes the square shaft 203 and the first welding head 204 to the appropriate position. The welding angle of the first welding head 204 faces the annular inner seam. The first motor 206 drives the torsion sleeve 208 to rotate through the first belt drive component 207, thereby driving the square shaft 203 and the first welding head 204 to rotate, so as to realize the welding of the annular inner seam between the inner support tube 72 and the ear seat component 71.

[0070] like Figures 8-11 As shown, the external seam welding assembly 3 includes a second bracket 301, a carrier 302, a second motor 303, a semi-hinge 304, a semi-circular plate 305, an arc-shaped slide rail 306, a slider 307, and a second welding head 308. The carrier 302 is fixed to the base plate 101 by the second bracket 301. The second motor 303 is symmetrically mounted on the outer side of the carrier 302. The output end of the second motor 303 is mounted with a semi-hinge 304. Two semi-hinges 304 are spliced ​​together to form a hinged hinge. The semi-hinges 304 are connected to the semi-circular plate 305. The inner side of the semi-circular plate 305 is provided with an arc-shaped slide rail 306. Two arc-shaped slide rails 306 are joined together to form a circular slide rail. The slider 307 is mounted on one of the arc-shaped slide rails 306 and forms an arc-shaped guide rail pair with it. The second welding head 308 is mounted on the outer side of the slider 307.

[0071] Working principle of the outer seam welding assembly 3: During operation, the second motor 303 drives the half hinge 304 and the semi-circular plate 305 to rotate, causing the second welding head 308 to move along the circular slide rail, thereby realizing the welding of the annular outer seam between the outer support tube 73 and the ear seat component 71.

[0072] like Figure 12 As shown, the inner support tube sealing assembly 4 includes a second drive push rod 401 and a solid plug 402. The cylinder of the second drive push rod 401 is fixed on the corresponding base plate 101, and the solid plug 402 is installed on the movable end of the second drive push rod 401.

[0073] The working principle of the inner support tube sealing assembly 4: During operation, the second drive push rod 401 pushes the solid plug 402 to seal one end of the inner support tube 72, providing a closed environment for subsequent compressive strength testing of the inner support tube 72. The insertion depth of the solid plug 402 can be adjusted as needed during sealing. When a compressive strength test is required on the inner support tube 72 that is not welded to the ear member 71, the solid plug 402 seals the annular inner seam upon insertion; when a compressive strength test is required on the inner support tube 72 that is welded to the ear member 71, the solid plug 402 exposes the annular inner seam upon insertion.

[0074] like Figure 13As shown, the inner support tube compressive strength testing component 5 includes a third drive push rod 501, a coupling 502, a hollow shaft 503, a hollow plug 504, a pressurizing air pump 505, a pressurizing air pipe 506, and a pressure gauge 507. The cylinder of the third drive push rod 501 and the pressurizing air pump 505 are fixed on the corresponding base plate 101. The movable end of the third drive push rod 501 is connected to one end of the hollow shaft 503 via the coupling 502, and the other end of the hollow shaft 503 is equipped with a hollow plug 504. The side end of the hollow shaft 503 is connected to the air supply end of the pressurizing air pump 505 via the pressurizing air pipe 506, and a pressure gauge 507 with a built-in pressure sensor is installed on the pressurizing air pipe 506.

[0075] The working principle of the inner support tube compressive strength testing component 5 is as follows: During operation, the third drive push rod 501 pushes the hollow shaft 503 and the hollow plug 504, causing the hollow plug 504 to seal the other end of the inner support tube 72. The pressurizing air pump 505 pressurizes the inner support tube 72 through the pressurizing air pipe 506, and the pressure gauge 507 monitors the pressure in real time, thereby detecting the compressive strength of the inner support tube 72. The insertion depth of the hollow plug 504 can be adjusted as needed during sealing. When it is necessary to test the compressive strength of the inner support tube 72 that is not welded to the ear member 71, the hollow plug 504 seals the annular inner seam when inserted; when it is necessary to test the compressive strength of the inner support tube 72 that is welded to the ear member 71, the hollow plug 504 exposes the annular inner seam when inserted.

[0076] like Figures 14-15As shown, the external support tube compressive strength testing component 6 includes a slide rail base 601, a linear guide pair 602, a first mounting plate 603, a third motor 604, a second mounting plate 605, a straightening ring sleeve 606, a straightening ring 607, a drop hammer box 608, an annular flexible pad 610, a locking push rod 611, a drop hammer block 612, and a drop hammer punch 613. The slide rail of the linear guide pair 602 is fixed on the slide rail base 601. The first mounting plate 603 is fixed to the outside of the slider of the linear guide pair 602. The second mounting plate 605 is mounted on the first mounting plate 603 via the third motor 604. The cylinder of the third motor 604 is fixed on the first mounting plate 603, and the output end of the third motor 604 is mounted on the second mounting plate 605. A straightening mechanism consisting of a straightening ring sleeve 606 and a straightening ring 607 is installed between the first mounting plate 603 and the second mounting plate 605. The straightening ring 607 is movable and restricted within the straightening ring sleeve 606. A drop hammer box 608 is installed on the outer side of the second mounting plate 605. The two end plates of the drop hammer box 608 are symmetrically provided with drop hammer punch holes 609. Annular flexible pads 610 are installed at both ends of the inner cavity of the drop hammer box 608. Two locking push rods 611 are symmetrically installed on the outer side of the drop hammer box 608. The internal movement of the drop hammer box 608 is restricted by a drop hammer block 612. Drop hammer punch rods 613 are symmetrically installed on both sides of the drop hammer block 612. A positioning hole 614 is opened on the rear side of the drop hammer block 612. The back plate of the drop hammer box 608 is symmetrically provided with guide holes corresponding to the positions of the positioning holes 614. Locking push rods 611 are symmetrically installed on the back plate of the drop hammer box 608. The movable end of the locking push rod 611 can extend into the positioning hole 614 of the drop hammer block 612 through the guide hole.

[0077] The working principle of the outer support tube compressive strength testing component 6 is as follows: During operation, the position of the drop hammer is adjusted by the linear guide pair 602, the rotation direction of the drop hammer box is adjusted by the third motor 604 so that it is vertically downward, the locking push rod 611 releases the drop hammer block 612, the drop hammer block 612 falls vertically under the action of gravity, and the drop hammer impact rod 613 impacts the outer support tube 73. The compressive strength of the outer support tube 73 is detected by measuring the deformation after impact.

[0078] like Figure 16 As shown, it also includes a controller 8, which is connected to the clamping assembly 1, the inner seam welding assembly 2, the outer seam welding assembly 3, the inner support tube sealing assembly 4, the inner support tube compressive strength detection assembly 5, and the outer support tube compressive strength detection assembly 6 respectively. The controller 8 is connected to the back-end terminal through a wireless communication module.

[0079] This embodiment also provides a method for testing the compressive strength of landing gear struts, including the following steps:

[0080] S1. Two clamping components 1 are used to jointly clamp the combined landing gear struts 7 arranged in a ring array.

[0081] S2. The compressive strength of the inner support tube 72, which is not welded to the ear member 71, is tested using the inner support tube sealing component 4 and the inner support tube compressive strength testing component 5; the compressive strength of the outer support tube 73, which is not welded to the ear member 71, is tested using the outer support tube compressive strength testing component 6.

[0082] S3. The inner seam welding assembly 2 is used to weld the annular inner seam between the inner support tube 72 and the ear member 71; the outer seam welding assembly 3 is used to weld the annular outer seam between the outer support tube 73 and the ear member 71.

[0083] S4. The compressive strength of the inner support tube 72 welded to the ear member 71 is tested using the inner support tube sealing component 4 and the inner support tube compressive strength testing component 5; the compressive strength of the outer support tube 73 welded to the ear member 71 is tested using the outer support tube compressive strength testing component 6.

[0084] This system can simultaneously meet the compressive strength testing requirements of both the outer and inner struts of composite landing gear struts. By using an inner strut sealing assembly, an inner strut compressive strength testing assembly, and an outer strut compressive strength testing assembly, the compressive strength of the inner and outer struts is tested independently, solving the problem that traditional systems cannot test both types of components simultaneously. Furthermore, it can meet the requirement of testing the compressive strength changes of composite landing gear struts before and after welding. Testing the inner and outer struts before welding (before welding to the lug assembly) and testing again after welding verifies the impact of the welding process on the strut's compressive strength, providing data support for optimizing the manufacturing process.

[0085] The preferred embodiments of the present invention disclosed above are merely illustrative of the invention. These preferred embodiments do not exhaustively describe all details, nor do they limit the invention to specific implementations. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention. The invention is limited only by the claims and their full scope and equivalents.

Claims

1. A system for testing the compressive strength of landing gear struts, characterized in that, It includes clamping components, inner seam welding components, outer seam welding components, inner support tube sealing components, inner support tube compressive strength testing components, and outer support tube compressive strength testing components; There are two clamping assemblies, which are symmetrically distributed. The two clamping assemblies together clamp the combined landing gear struts arranged in a ring array. The combined landing gear struts include lug members, inner struts, outer struts, spring mounting seats, and support springs. There are two inner seam welding assemblies, which are respectively installed on adjacent clamping assemblies. The inner seam welding assemblies are used to weld the annular inner seam between the inner support tube and the lug member. There are two external seam welding assemblies, which are respectively installed on adjacent clamping assemblies. The external seam welding assemblies are used to weld the annular external seam between the external support tube and the lug member. The inner support tube sealing assembly and the inner support tube compressive strength testing assembly are symmetrically mounted on adjacent clamping assemblies and are used together to test the compressive strength of the inner support tube. The inner support tube sealing assembly includes a second drive push rod and a solid plug. The cylinder of the second drive push rod is fixed on a corresponding base plate, and the movable end of the second drive push rod is equipped with a solid plug. The inner support tube compressive strength testing assembly includes a third drive push rod, a coupling, a hollow shaft, a hollow plug, a pressurizing air pump, a pressurizing air pipe, and a pressure gauge. The cylinder of the third drive push rod and the air pump are fixed on a corresponding base plate. The movable end of the third drive push rod is connected to one end of the hollow shaft via the coupling. The other end of the hollow shaft is equipped with a hollow plug. The side end of the hollow shaft is connected to the air supply end of the pressurizing air pump via the pressurizing air pipe. A pressure gauge with a built-in pressure sensor is installed on the pressurizing air pipe. The external support tube compressive strength testing component is positioned above the area between the two clamping components and is used to test the compressive strength of the external support tube. The external support tube compressive strength testing component includes a slide rail base, a linear guide pair, a first mounting plate, a third motor, a second mounting plate, a straightening ring, a straightening ring, a drop hammer box, an annular flexible pad, a locking push rod, a drop hammer block, and a drop hammer punch. The slide rail of the linear guide pair is fixed to the slide rail base. The first mounting plate is fixed to the outside of the slider of the linear guide pair. The second mounting plate is mounted on the first mounting plate via the third motor. A straightening ring is installed between the first and second mounting plates. The straightening mechanism consists of a straightening ring and a drop hammer box. A drop hammer box is installed on the outer side of the second mounting plate. The two end plates of the drop hammer box are symmetrically provided with drop hammer punches. The two ends of the inner cavity of the drop hammer box are provided with annular flexible pads. Locking push rods are symmetrically installed on the outer side of the drop hammer box. The drop hammer block is movable and restricted inside the drop hammer box. Drop hammer punches are symmetrically installed on both sides of the drop hammer block. A positioning hole is provided on the rear side of the drop hammer block. The back plate of the drop hammer box is symmetrically provided with guide holes corresponding to the positions of the positioning holes. Locking push rods are symmetrically installed on the back plate of the drop hammer box. The movable end of the locking push rod can extend into the positioning hole of the drop hammer block through the guide hole.

2. The system for testing the compressive strength of landing gear struts according to claim 1, characterized in that, There are two ear seat components, with an inner support tube and an outer support tube sandwiched between the two ear seat components. A support spring is installed in the area between the inner support tube and the outer support tube, and spring mounting seats that can be threadedly connected to the ear seat components are fixed at both ends of the support spring. The ear seat component includes a groove-shaped ear seat, the outer wall of the web of the groove-shaped ear seat is provided with a protruding tube, the inner diameter of the protruding tube is equal to the outer diameter of the inner support tube, the web of the groove-shaped ear seat is provided with an external through hole, and the diameter of the external through hole is equal to the inner diameter of the inner support tube, the outer side of the protruding tube is provided with an external thread, and each of the two side plates of the groove-shaped ear seat is provided with a hinge hole. The spring mounting base includes an annular seat with an internal thread groove that mates with the external threaded portion. The outer diameter of the annular seat is equal to the inner diameter of the outer support tube. An internal through hole is provided at the inner end of the annular seat located in the internal thread groove, and the diameter of the internal through hole is equal to the outer diameter of the inner support tube.

3. The system for testing the compressive strength of landing gear struts according to claim 2, characterized in that, The clamping assembly includes a base plate, an external rotary driver, an outer cover, an annular end plate, positioning blocks, and a locking mechanism. The base plate is mounted with an outer cover having an annular end plate via the external rotary driver. Several positioning blocks are provided circumferentially on the outer side of the annular end plate. A locking mechanism is installed inside the outer cover. The annular end plate has a first through hole on the back side of the positioning block, and a second through hole is provided in the positioning block. The outer side of the positioning block has a snap-fit ​​groove for facilitating the snap-fit ​​of the ear seat component and a locking groove that is perpendicularly connected to the inner snap-fit ​​groove. The specifications of the locking groove are matched with the specifications of the hinge hole. The locking mechanism includes an inner cover, a support block, a locking rod, an inner rotary drive, and a movable disc. The inner wall of the inner end plate of the inner cover supports the movable disc via the inner rotary drive. The outer side of the movable disc is provided with several arc-shaped push grooves along the circumference. The outer end plate of the inner cover is provided with several radial sliding grooves along the circumference. The support block slides and is restricted in the radial sliding grooves. The inner end of the support block is provided with an anti-dislodgement head that slides and is restricted in the arc-shaped push grooves. The outer end of the support block is equipped with a locking rod that can extend into the locking groove.

4. The compressive strength testing system for landing gear struts according to claim 3, characterized in that, The inner seam welding assembly includes a first drive push rod, a rotary joint, a square shaft, a first welding head, a first bracket, a first motor, a first belt drive component, and a torsion sleeve. The cylinder of the first drive push rod is mounted on the base plate. The movable end of the first drive push rod is connected to one end of the square shaft via the rotary joint. The other end of the square shaft is equipped with the first welding head. The first motor is fixed to the base plate via the first bracket. The output shaft of the first motor is connected to the torsion sleeve via the first belt drive component. The torsion sleeve is sleeved on the outside of the square shaft and is movably supported by the first bracket.

5. The compressive strength testing system for landing gear struts according to claim 4, characterized in that, The external seam welding assembly includes a second bracket, a carrier, a second motor, a semi-hinge, a semi-circular plate, an arc-shaped slide rail, a slider, and a second welding head. The carrier is fixed to the base plate by the second bracket. The second motor is symmetrically installed on the outer side of the carrier. A semi-hinge is installed at the output end of the second motor. Two semi-hinges are spliced ​​together to form a hinged joint. The semi-hinge is connected to a semi-circular plate. An arc-shaped slide rail is provided on the inner side of the semi-circular plate. Two arc-shaped slide rails are joined together to form a circular slide rail. The slider is installed on one of the arc-shaped slide rails and forms an arc-shaped guide rail pair with it. A second welding head is installed on the outer side of the slider.

6. The compressive strength testing system for landing gear struts according to claim 5, characterized in that, It also includes a controller, which is connected to the clamping assembly, the inner seam welding assembly, the outer seam welding assembly, the inner support tube sealing assembly, the inner support tube compressive strength testing assembly, and the outer support tube compressive strength testing assembly, respectively. The controller is connected to the back-end terminal through a wireless communication module.

7. A method for testing the compressive strength of landing gear struts, implemented based on the compressive strength testing system for landing gear struts as described in claim 6, characterized in that, Includes the following steps: S1. Two clamping components are used to jointly clamp the combined landing gear struts distributed in a ring array. S2. Use the inner support tube sealing assembly and the inner support tube compressive strength testing assembly to test the compressive strength of the inner support tube that is not welded to the ear seat component; use the outer support tube compressive strength testing assembly to test the compressive strength of the outer support tube that is not welded to the ear seat component. S3. Use the inner seam welding assembly to weld the annular inner seam between the inner support tube and the ear seat component; use the outer seam welding assembly to weld the annular outer seam between the outer support tube and the ear seat component. S4. Use the inner support tube sealing assembly and the inner support tube compressive strength testing assembly to test the compressive strength of the inner support tube welded to the ear seat component; use the outer support tube compressive strength testing assembly to test the compressive strength of the outer support tube welded to the ear seat component.

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