A test device for the turning life of the front landing gear of a catapult-launched carrier-based aircraft

Abstract

The invention provides a turning life test device for the front landing gear of a catapult-launched carrier-based aircraft, including a support frame, and a loading mechanism and a driving mechanism arranged thereon, wherein: the loading mechanism includes an inner ring torque loading mechanism and an outer ring torque loading mechanism which are coaxial and respectively arranged on the support frame, and the inner ring loading mechanism and the outer ring torque loading mechanism are each provided with a rotating element, and the rotating element of the inner ring loading mechanism is provided with a fixture for clamping the wheel axle structure at the bottom end of the front landing gear, and the rotating element of the outer ring torque loading mechanism is provided with a tension loading mechanism, which performs tension loading and torque transmission in the three states of landing gear traction turning, catapult turning and restraining turning. The test device created by the invention adopts a universal design concept, and through the combination of various detection modules, ensures that all four tests can be completed on the platform, reducing the economic cost, time cost and floor space of the test platform system.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace vehicle landing gear, and in particular relates to a turning life test device for a front landing gear of a catapult-launched carrier-based aircraft. Background Art

[0002] When a carrier-based aircraft takes off by catapult, the catapult shuttle on the aircraft carrier applies a very large pulling force to the front landing gear traction rod, and the check rod applies resistance to the front landing gear. When the traction force reaches a certain value, the check rod is released instantly, the carrier-based aircraft obtains a large instantaneous acceleration, and the shuttle continues to pull the traction rod forward, so that the carrier-based aircraft can fly away from the aircraft carrier deck in a shorter distance. Compared with non-catapulted aircraft, the front landing gear of carrier-based aircraft bears very complex and very large loads. Therefore, it is necessary to study the front take-off turning life of carrier-based aircraft under complex loads, which is also one of the technical difficulties of catapult take-off of carrier-based aircraft.

[0003] The turning life test of the front landing gear of a carrier-based aircraft launched by catapult mainly tests the turning life of the front landing gear of the carrier-based aircraft under four working conditions. During the test, dynamic loads need to be applied to the front landing gear under four working conditions: traction turning, catapult turning, restraint turning and control turning, to simulate the actual loading conditions. When the front landing gear is in traction turning, catapult turning and restraint turning conditions, the front landing gear is simultaneously subjected to the support reaction force of the ground, the friction torque between the tire and the ground, and the external tension. Therefore, the front landing gear is in a multi-load dynamic process with tension, pressure and torque coexisting when undergoing the turning life test.

[0004] The traditional nose landing gear turning life test only conducts the maneuvering turning life test, the load application is relatively simple, and the technology is relatively mature. At present, there are no relevant public test research reports on the turning life test of the nose landing gear of carrier-based aircraft at home and abroad. The public patents and literature are mostly theoretical analysis and simulation of the ejection process of carrier-based aircraft, static test of the nose landing gear of carrier-based aircraft, etc., and there is no relevant experimental research. Summary of the invention

[0005] In view of this, the invention aims to propose a turning life test device for the front landing gear of a catapult-launched carrier-based aircraft, so as to realize the life tests of control turning, traction turning, catapult turning and restraint turning on the same type of landing gear.

[0006] To achieve the above object, the technical solution created by the present invention is implemented as follows:

[0007] A turning life test device for the front landing gear of a catapult-launched carrier aircraft comprises a support frame, and a loading mechanism and a driving mechanism arranged thereon, wherein:

[0008] The loading mechanism includes an inner ring torque loading mechanism and an outer ring torque loading mechanism which are coaxial and respectively arranged on the support frame. The inner ring loading mechanism and the outer ring torque loading mechanism are respectively provided with a rotating element. The rotating element of the inner ring loading mechanism is provided with a fixture for clamping the wheel axle structure at the bottom end of the front landing gear. The rotating element of the outer ring torque loading mechanism is provided with a tension loading mechanism. The outer ring torque loading mechanism transmits torque to the front landing gear through the tension loading mechanism, and at the same time, tension loading is applied to the landing gear in three states: traction turning, ejection turning and restraint turning.

[0009] The driving mechanism is arranged corresponding to the top structure of the landing gear, and the driving mechanism and the inner ring loading mechanism work together to realize the turning loading test of the front landing gear operation.

[0010] Furthermore, the outer ring torque loading mechanism comprises an outer ring slewing bearing mounted on a support frame, and a driving member matched with the outer ring slewing bearing, and the outer ring torque loading mechanism rotating member is an outer ring load plate mounted on the outer ring slewing bearing.

[0011] Furthermore, the driving component is a hydraulic motor.

[0012] Furthermore, the support seat is provided with a dial for displaying the rotation angle of the outer ring load plate.

[0013] Furthermore, the inner ring loading mechanism includes a turntable support, the rotating part of the inner ring loading mechanism is an inner ring load plate, the turntable support is installed on a support frame, the turntable support is provided with a swing cylinder for loading ground friction torque, the inner ring load plate is installed at the power output end of the swing cylinder, and the output end of the swing cylinder is provided with a torque sensor.

[0014] Furthermore, the tension loading mechanism comprises a fixed support, a push rod element, a lever and a pull rod, the fixed support is mounted on the rotating element of the ring torque loading mechanism, the push rod element base is hinged on the fixed support through a ball joint structure, the lever is hinged on the fixed support, and one end of the lever and the push rod of the push rod element are hinged through a ball joint structure, and the other end of the pull rod is provided with a hinge structure, the ejection turning traction point, the restraining turning traction point and the traction turning traction point of the tractor on the front landing gear are connected to the hinge structure according to the test sequence, and lateral tension loading is applied to each traction point of the front landing gear;

[0015] A tension sensor is arranged at the push rod end of the push rod element.

[0016] Furthermore, the lever is a labor-saving lever structure.

[0017] The driving mechanism comprises a bracket horizontally slidably arranged on a support frame through a screw driving mechanism, a motor is arranged on the bracket, a joint corresponding to the front landing gear shaft is arranged on the main shaft of the motor, and the front landing gear shaft is driven to rotate through the joint.

[0018] Furthermore, the fixture includes a wheel axle support, and a guide rail slider follower structure arranged on the rotating part of the inner ring loading mechanism, the wheel axle support is installed on the slider on the guide rail slider follower structure, the moving direction of the slider of the guide rail slider follower structure is arranged corresponding to the loading direction of the tension loading mechanism, and the top surface of the wheel axle support is provided with a V-shaped groove corresponding to the front landing gear axle, and the wheel axle support is also matched with a pressure plate to lock the front landing gear axle in the V-shaped groove.

[0019] Compared with the prior art, the present invention creates a catapult take-off carrier aircraft front landing gear turning life test device with the following advantages:

[0020] 1. This test device adopts a universal design concept. Through the combination of various detection modules, it ensures that all four tests can be completed on the test bench, reducing the economic cost, time cost and floor space of the test bench system;

[0021] 2. This test device meets the dynamic loading turning life test of the front landing gear of carrier-based aircraft under four working conditions: towing turning, ejection turning, restraining turning and maneuvering turning. It is a set of mechanical, electrical and hydraulic integrated servo system;

[0022] 3. This test device is composed of inner and outer ring torque loading mechanisms and lever-type tension loading mechanisms, which can simultaneously apply active rotation torque, passive resistance torque, and large-load external tension loads. It has a compact structure and occupies little space.

[0023] 4. All tension and torque loading mechanisms are within the test device frame. The force is self-balanced during loading, and will not cause damage to the ground outside the test device. The test device is easy to fix and has low requirements on the site.

[0024] 5. The tension loading mechanism adopts a lever structure, which can not only apply tension but also transmit torque to the force application point, and the lever structure also reduces the load requirements for the loading hydraulic cylinder; both ends of the loading hydraulic cylinder are provided with a radial joint bearing ball joint structure, so that the hydraulic cylinder and the tension sensor form a two-force rod structure, which is not affected by the lateral force;

[0025] 6. The backlash-eliminating reducer is used to transmit torque, so that the system is always in a compacted state after the rotary system is in place, improving the accuracy of the transmission system and ensuring the positioning accuracy of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The drawings constituting part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments and descriptions of the present invention are used to explain the present invention and do not constitute an improper limitation on the present invention. In the drawings:

[0027] Figure 1It is a three-dimensional schematic diagram of this embodiment;

[0028] Figure 2 is a three-dimensional schematic diagram of the loading mechanism in this embodiment;

[0029] Figure 3 This is a three-dimensional schematic diagram of the outer ring torque loading mechanism in this embodiment;

[0030] Figure 4 This is a three-dimensional schematic diagram of the inner ring torque loading mechanism in this embodiment;

[0031] Figure 5 This is the internal structure diagram of the inner ring torque loading mechanism in this embodiment;

[0032] Figure 6 is a three-dimensional schematic diagram of the tension loading mechanism in this embodiment;

[0033] Figure 7 is a three-dimensional schematic diagram of the driving mechanism in this embodiment;

[0034] Figure 8 Schematic diagram of the launch turn test for the landing gear;

[0035] Fig. 9 Schematic diagram of the restrained turning test for the front landing gear;

[0036] Fig.10 Schematic diagram of the towing turning test for the front landing gear;

[0037] Fig.11 Schematic diagram of the operational turning test for the nose landing gear;

[0038] Description of reference numerals:

[0039] 1-driving mechanism: 11-handle; 12-screw rod; 13-motor; 14-bracket; 15-base; 16-slide rail; 2-support frame; 3-angle sensor; 4-loading mechanism; 41-inner ring torque loading mechanism: 411-wheel axle support; 412-guide rail slider follower structure; 413-inner ring load plate; 415-turntable support; 416-transmission shaft; 417-torque sensor; 418-swing cylinder; 42-outer ring torque loading mechanism: 421-outer ring turntable bearing; 422-anti-backlash reducer; 423-driving member; 424-outer ring load plate; 425-dial; 43-tension loading mechanism: 431-connecting rod; 433-tension sensor; 434-push rod element; 436-lever; 437-fixed support; 5-support base; 6-escalator; 7-front landing gear. DETAILED DESCRIPTION

[0040] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0041] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0042] In the description of the invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the invention can be understood according to specific circumstances.

[0043] The present invention will be described in detail below with reference to the accompanying drawings and in combination with embodiments.

[0044] like Figure 1 As shown, a turning life test device for the front landing gear of a catapult-launched carrier-based aircraft includes a support frame 2, which is a frame structure, a support base 5 is provided at the bottom, and an escalator 6 is provided on the side. A loading mechanism 4 and a driving mechanism 1 are provided on the support frame 2, wherein the loading mechanism 4 is arranged on the support base 5, and the driving mechanism 1 is arranged on the support frame 2, and the driving mechanism is located above the loading mechanism 4.

[0045] like Figure 2As shown, the loading mechanism 4 includes an inner ring torque loading mechanism 41 and an outer ring torque loading mechanism 42 respectively arranged on the support frame 2, and the inner ring loading mechanism 41 and the outer ring torque loading mechanism 42 are each provided with a rotating element, and the rotating elements of the inner ring loading mechanism 41 and the outer ring torque loading mechanism 42 are provided with an axis setting. In order to save space, in this embodiment, the outer ring torque loading mechanism 42 is provided with an avoidance hole, and the inner ring loading mechanism 41 is arranged through the avoidance hole. The inner ring loading mechanism 41 is used to simulate the friction torque between the front landing gear wheel and the ground when turning. The rotating element of the inner ring loading mechanism 41 is provided with a fixture for clamping the wheel axle structure at the bottom end of the front landing gear 7, which is used to clamp and fix the wheel axle of the front landing gear 7. The outer ring torque loading mechanism 42 is used to simulate the active torque applied by the front landing gear 7 during the ejection turn, traction turn and restraint turn state, so the outer ring torque loading mechanism 42 is provided with a tension loading mechanism 43 on the rotating element, and the active loading force is simulated by the tension loading mechanism 43. In the experimental device, the outer ring torque loading mechanism 42 realizes torque transmission to the front landing gear 7 through the tension loading mechanism 43, and the inner ring loading mechanism 41 directly applies torque to the bottom end of the front landing gear. Under the action of the inner ring torque loading mechanism 41 and the outer ring torque loading mechanism 42, the tension loading mechanism 43 is respectively connected to the ejection turning traction point, the traction turning traction point, and the restraint turning traction point on the front landing gear 7, so as to realize the life test of the landing gear 7 in three states: ejection turning, traction turning and restraint turning, respectively. Figure 8 , 9 10. In the specific experimental process, the top of the front landing gear 7 is fixed to the locking structure of the support frame 2 by means of locking fixings such as bolts, screws, and pins, and then the tension loading mechanism 43 and the traction ejection turning traction point, turning traction point, and restraint turning traction point on the front landing gear 7 are connected in sequence according to the test requirements. For example, the ejection turning traction point is first connected to perform an ejection turning life test, and after the ejection turning life test is completed, the tension loading mechanism 43 is connected to the traction turning traction point of the front landing gear 7 as required to perform a traction turning life test, and finally the tension loading mechanism 43 is connected to the restraint turning traction point of the front landing gear 7 to perform a restraint turning life test. During the three different state tests, the tension loading mechanism 43 applies external tension to different traction points on the front landing gear 7, the outer ring torque loading mechanism 42 drives the tension loading mechanism 43 to rotate, simulating the active traction state of the landing gear, and the inner ring loading mechanism 41 simulates the friction loss torque of the internal rotating parts of the front landing gear 7, and the friction torque of the wheels and the bottom surface, so its torque direction is opposite to the torque of the outer ring torque loading mechanism 42.

[0046] In this embodiment, Figure 1As shown, in order to detect the life condition of the front landing gear 7 during normal driving and turning, a driving mechanism 1 is arranged at the upper end of the support frame 2. The driving mechanism 1 corresponds to the top structure of the landing gear 7. The driving mechanism 1 applies an active turning torque to the upper end of the front landing gear 7 to simulate the turning torque applied to the top end of the front landing gear 7 during normal turning of the landing gear. Similarly, the inner ring loading mechanism 41 simulates the friction torque between the wheel and the bottom surface. The driving mechanism 1 and the inner ring loading mechanism 41 work together to realize the front landing gear operation turning loading test.

[0047] like Figure 3 As shown, the outer ring torque loading mechanism 42 includes an outer ring turntable bearing 421 mounted on the support base 5. Preferably, the outer ring turntable bearing 421 is an outer gear ring structure. The outer ring turntable bearing 421 is matched with a driving member 423, and the driving member 423 is a hydraulic motor. In order to reduce noise, the output end of the driving member 423 is provided with a backlash reduction reducer 422. The power of the driving member 43 is transmitted to the outer ring turntable bearing 421 through the backlash reduction reducer 422, driving the outer ring turntable bearing 421 to rotate, and the transmission system accuracy is improved, ensuring the positioning accuracy of the system. The rotating member of the outer ring torque loading mechanism 42 is an outer ring load disk 424 mounted on the outer ring turntable bearing 421, and the outer ring load disk 424 is a ring structure. In order to detect the rotation angle of the outer ring load disk 424, the support seat 2 is provided with a dial 425 for displaying the rotation angle of the outer ring load disk 424.

[0048] like Figure 4 , 5 As shown, the inner ring loading mechanism 41 includes a turntable support 415, and the rotating part of the inner ring loading mechanism 41 is an inner ring load disk 413. The turntable support 415 is installed on the supporting base 5. The turntable support 415 is provided with a swing cylinder 418, and the main shaft of the swing cylinder is vertically upward. The main shaft output end of the swing cylinder 418 is provided with a torque sensor 417 for detecting the output torque and passive torque of the swing cylinder 418 to obtain the turning torque loaded on the front starter. The bottom end of the transmission shaft 416 is connected to the torque sensor 417 through a flange, and the upper end thereof is connected to the inner ring load disk 413 through a spline, thereby driving the inner ring load disk 413 to rotate.

[0049] like Figure 4 , 5As shown, the jig includes an axle support 411, and a guide rail slider follower structure 412 arranged on the inner ring load plate 413 of the inner ring loading mechanism 41, the axle support 411 is installed on the slider on the guide rail slider follower structure 412, and the slider movement direction of the guide rail slider follower structure 412 is corresponding to the loading direction of the tension loading mechanism 43. The guide rail slider follower structure 412 is used to adapt to the self-deformation of the front landing gear 7 when it is subjected to a tensile load, which is consistent with the actual use of the front landing gear. At the same time, the guide rail slider follower structure 412 can withstand lateral loads and can transmit torque. The top surface of the axle support 411 is provided with a V-shaped groove corresponding to the axle of the front landing gear 7, and the axle support 411 is also matched with a pressure plate that locks the axle of the front landing gear 7 in the V-shaped groove.

[0050] like Figure 6 As shown, the tension loading mechanism 43 includes a fixed support 437, a push rod element 434, a lever 436 and a pull rod 431. The fixed support 437 is installed on the rotating element of the ring torque loading mechanism 42. The base of the push rod element 434 is hinged to the fixed support 437 through a ball joint structure. The lever 436 is hinged to the fixed support 437 through a hinge pin. The hinge point is the fulcrum of the lever 436, forming a force-saving lever structure of the lever 436. One end of the lever 436 is hinged to the push rod of the push rod element 434 through a ball joint structure. One end is hinged with one end of the pull rod 431 through a hinge pin, and the thrust element 434 is a hydraulic cylinder. Both ends of the hydraulic cylinder 434 adopt a ball joint connection structure to form a two-force rod structure, which is not affected by the lateral torque. The other end of the pull rod 431 is respectively used to be hinged with the ejection turning traction point, the restraint turning traction point and the traction turning traction point of the tractor on the front landing gear 7, and the lateral tension is applied to each traction point of the front landing gear 7 through the tension loading mechanism 43; at the same time, under the action of the outer ring torque loading mechanism, the active torque during turning is transmitted to the front landing gear 7. In order to detect the size of the lateral tension applied to the front landing gear 7 by the tension loading mechanism 43, a tension sensor 433 is provided at the push rod end of the push rod element 434.

[0051] like Figure 1 , 7 As shown, the driving mechanism 1 includes a bracket 14 which is horizontally slidably arranged on a support frame through a screw drive mechanism, wherein the screw drive mechanism is installed on a base 15 at the top of the support frame 2, and its screw 12 is horizontally arranged, a handle 11 is provided at the outer end of the screw, a bracket 14 is provided at the inner end of the screw, and a slide groove parallel to the screw is provided on the base 15. The bracket 14 is equipped with a slide rail 16 matching the slide groove, and the slide rail is installed in the slide groove to form a moving pair. A motor 13 is arranged on the bracket 14, and the motor main shaft is arranged vertically downward. A joint 17 corresponding to the rotating shaft of the driving wheel in the front landing gear 7 is arranged on the main shaft of the motor 13, and the front landing gear rotating shaft is driven to rotate through the joint 17. When operating the turning test, as shown in FIG. Fig.11As shown, the tension loading mechanism 43 and the outer ring torque loading mechanism 42 are not working, the motor 13 drives the rotating shaft in the front landing gear 7 to rotate, and at the same time, the inner ring torque loading mechanism 41 is turned on to simulate the aircraft operation turning state. In order to detect the rotation angle of the front landing gear during the operation turning test, an angle measuring sensor 3 is set on the support frame 2.

[0052] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A catapult-launched carrier aircraft nose landing gear turning life test device, characterized in that: It comprises a support frame (2), and a loading mechanism (4) and a driving mechanism (1) arranged thereon, wherein: The loading mechanism (4) comprises an inner ring torque loading mechanism (41) and an outer ring torque loading mechanism (42) which are coaxial and respectively arranged on a support frame. The inner ring torque loading mechanism (41) and the outer ring torque loading mechanism (42) are respectively provided with a rotating element. The rotating element of the inner ring torque loading mechanism (41) is provided with a fixture for clamping the wheel axle structure at the bottom end of the front landing gear (7). The rotating element of the outer ring torque loading mechanism (42) is provided with a tension loading mechanism (43). The tension loading mechanism (43) transmits the torque of the outer ring torque loading mechanism (42) to the front landing gear (7), and at the same time, applies tension loading to the front landing gear (7) in three states: traction turning, ejection turning and restraint turning. The driving mechanism (1) is arranged corresponding to the top structure of the landing gear (7), and the driving mechanism (1) and the inner ring torque loading mechanism (41) work together to realize the turning loading test of the front landing gear; The inner ring torque loading mechanism (41) comprises a turntable support (415), the rotating part of the inner ring torque loading mechanism (41) is an inner ring load plate (413), the turntable support (415) is mounted on a support frame (2), the turntable support (415) is provided with a swing cylinder (418), the inner ring load plate (413) is mounted at the power output end of the swing cylinder (418), and the output end of the swing cylinder (418) is provided with a torque sensor (417); The tension loading mechanism (43) includes a fixed support (437), a push rod element (434), a lever (436) and a pull rod (431), wherein the fixed support (437) is mounted on the rotating element of the outer ring torque loading mechanism (42), the base of the push rod element (434) is hinged on the fixed support (437) through a ball joint structure, the lever (436) is hinged on the fixed support (437), one end of the lever (436) is hinged to the push rod of the push rod element (434) through a ball joint structure, and the other end is hinged to one end of the pull rod (431), and the other end of the pull rod (431) is provided with a hinge structure, and the ejection turning traction point, the restraining turning traction point and the traction turning traction point of the tractor on the front landing gear (7) are connected to the hinge structure according to the test sequence, and lateral tension loading is applied to each traction point of the front landing gear (7); A tension sensor (433) is provided at the push rod end of the push rod element (434); The outer ring torque loading mechanism (42) comprises an outer ring turntable bearing (421) mounted on a support frame (2), and a driving member (423) matched with the outer ring turntable bearing (421); the rotating member of the outer ring torque loading mechanism (42) is an outer ring load plate (424) mounted on the outer ring turntable bearing (421).

2. The turning life test device for the front landing gear of a catapult-launched carrier aircraft according to claim 1, characterized in that: The driving member (423) is a hydraulic motor.

3. The turning life test device for the front landing gear of a catapult-launched carrier aircraft according to claim 2, characterized in that: The output end of the driving member (423) is provided with a backlash-eliminating reducer (422).

4. The turning life test device for the front landing gear of a catapult-launched carrier aircraft according to claim 1, characterized in that: The support frame (2) is provided with a dial (425) for displaying the rotation angle of the outer ring load disc (424).

5. The turning life test device for the front landing gear of a catapult-launched carrier aircraft according to claim 1, characterized in that: The push rod element (434) is a hydraulic cylinder, and the lever (436) is a force-saving lever structure.

6. The turning life test device for the front landing gear of a catapult-launched carrier aircraft according to claim 1, characterized in that: The driving mechanism (1) comprises a bracket (14) which is horizontally slidably arranged on a support frame through a screw drive mechanism, a motor (13) is arranged on the bracket (14), a joint (17) corresponding to the front landing gear shaft is arranged on the main shaft of the motor (13), and the front landing gear shaft is driven to rotate through the joint (17).

7. A catapult-launched carrier aircraft nose landing gear turning life test device according to any one of claims 1 to 6, characterized in that: The jig comprises an axle support (411) and a guide rail slider follower structure (412) arranged on a rotating part of an inner ring torque loading mechanism (41); the axle support (411) is mounted on a slider on the guide rail slider follower structure (412); the slider movement direction of the guide rail slider follower structure (412) and the loading direction of the tension loading mechanism (43) are arranged correspondingly; a V-shaped groove corresponding to the axle structure of the front landing gear (7) is opened on the top surface of the axle support (411); the axle support is also matched with a pressure plate for locking the axle of the front landing gear (7) in the V-shaped groove.

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