CN216375058U

CN216375058U - Aircraft landing gear uplock lock test device

Info

Publication number: CN216375058U
Application number: CN202122773262.XU
Authority: CN
Inventors: 林纯景; 董文珂; 陈劲松
Original assignee: SICHUAN LINGFENG AVIATION HYDRAULIC MACHINERY CO Ltd
Current assignee: SICHUAN LINGFENG AVIATION HYDRAULIC MACHINERY CO Ltd
Priority date: 2021-11-12
Filing date: 2021-11-12
Publication date: 2022-04-26
Anticipated expiration: 2031-11-12

Abstract

The utility model discloses a testing device for the lock bump of an aircraft landing gear uplock, which is convenient to assemble and disassemble, reliable in loading, strong in compatibility and high in testing precision. The utility model is realized by the following technical scheme: the trigger type upper lock is movably clamped on the lock ring through a locking and locking lock hook fixedly connected with the back end; the hydraulic cylinder is used as a power source, the loading hydraulic cylinder extends out of a piston rod of the loading hydraulic cylinder, sequentially passes through a through hole of a vertical plate of the rear support, a loading spring and a support copper sleeve, passes through the back end of the vertical plate of the bearing support and is connected with a tension pressure sensor assembly, a lock ring of a locking part is provided on a lock ring motion track guide groove plate, a locking and locking lock hook which moves into a tested trigger type upper lock is locked, a locking and locking linear load is applied, and the locking load value and the locking ring motion track of the locking part which meet the actual use working condition are measured; the pull pressure sensor assembly is connected to the piston rod and connected to the display via wires to display the pressurizing load value and the linear latch test load value applied to the latch hook by the latch component.

Description

Aircraft landing gear uplock lock test device

Technical Field

The utility model relates to the technical field of reliability tests of an aircraft landing gear uplock, in particular to a collision lock test device of the aircraft landing gear uplock.

Background

The landing gear retraction position lock is used to lock the landing gear in either the retracted or the extended position to prevent the landing gear from being automatically retracted during flight and from being automatically retracted when impacted. The landing gear uplock is used for locking or unlocking various motion mechanisms on an airplane, is an important part of an airplane landing gear system, and is an important part for judging whether the landing gear can normally work or not. In normal flight, the uplock should be normally closed and kept in a normally locked state or normally opened, otherwise, the uplock will cause the failure of the flight mission and affect the flight safety of the airplane. Particularly, in the landing stage of the airplane, if the uplock cannot be normally opened, the landing gear cannot be normally put down, and serious accidents are possibly caused. The retractable position lock generally has two forms: strut-type and hook-and-loop type. The strut lock is also called the over-center lock, lock the tie rod, lock spring and unlock the actuator cylinder to make up, the strut lock is kept locking by the lock spring, is unlocked by unlocking the actuator cylinder, its locking principle is: when the landing gear is put down, the upper side stay bar and the lower side stay bar move to an over-center state and are kept at an over-center position by the lock connecting rod, namely, the landing gear enters a locking state; the landing gear is pushed by the retractable actuating cylinder to fold the side stay bar, so that the landing gear is retracted. The undercarriage lower lock, the upper lock and the cabin door lock usually adopt a hook-and-loop lock mechanism which mainly comprises a lock hook, a lock spring, a lock ring (or lock catch or lock roller), an unlocking actuator cylinder, an emergency unlocking actuator cylinder and a trigger switch, wherein the lock ring on the undercarriage moving component is hooked by the lock hook arranged on the body mechanism of the hook-and-loop lock, so that the moving component is fixed at a required position, and the lock mechanism is actuated through the lock actuator cylinder, a rocker arm and a connecting rod during working. When the lock ring enters the lock hook, the lock ring is in a locked state, and the lock spring can keep the lock ring in the locked state when hydraulic pressure is not supplied. When the undercarriage is put down and in place, the lock ring connected to the strut enters the arc claw of the side plate to touch the lock hook to rotate, the lock hook hooks the lock cylinder immediately, meanwhile, the lock key on the back of the lock hook is firmly locked at the put-down position under the spring force of the actuator cylinder, when the undercarriage is unlocked, oil enters the unlocking actuator cylinder to pull the lock key to rotate and separate from the lock hook, and then the lock hook deflects to disengage the lock ring on the strut under the action of the spring and the retracting power, namely, the lock is unlocked.

The most important of the lock mechanisms of the landing gear system is an uplock, if the uplock cannot be unlocked, the landing gear cannot be put down, and the airplane can possibly crash, so that for all landing gear parts, the load loaded on the lock hook by the lock ring in the locking and unlocking processes is one of the key factors influencing the unlocking/locking functions and reliability of the uplock. The lock bumping test items of the lock mechanism mainly comprise a lock test, an unlock test, an emergency unlock test and the like, and in order to verify the working reliability of the lock function and guarantee the flight safety, the lock bumping test of the lock mechanism must be accurately performed.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the technical problem in the background technology and provides a collision lock test device of an aircraft landing gear uplock, which has the advantages of simple structure, convenient assembly and disassembly, reliable loading, strong compatibility and high test precision, and can be used for carrying out locking tests, unlocking tests, emergency unlocking tests and other items.

The technical scheme adopted by the utility model for solving the technical problems is as follows: an aircraft landing gear uplock lock test device, comprising: fix fore-stock angle steel riser 2 on test bench 1 through T type groove bolt and hexagonal flange face nut, back support riser support 15, be located fore-stock angle steel riser 2 and bear support 17 and guide way installation fixed bolster 20 between the rear support riser support 15, link up in front and back end riser both sides, through bearing the unsettled pull rod 23 that support 17 front and back plate end clamp 7 couples firmly, be located 20 back of the body ends of guide way installation fixed bolster, through the last lock mounting bracket 3 of the fixed article tested of installation bolt, and the spring loading mechanism that pneumatic cylinder (14) as the power supply link to each other, its characterized in that: the upper lock mounting frame 3 is fixedly connected with a lock ring motion track guide groove 5 which is coupled and connected with the trigger type upper lock 4; the guide groove mounting and fixing support 20 is connected with a lock ring 35 through a lock ring loading connecting block 33 tail connecting sliding groove connected with a piston rod, and the trigger type upper lock 4 is movably clamped on a lock ring 35 cylinder body through a locking and locking lock hook fixedly connected with the back end; the hydraulic cylinder 14 is used as a power source, the loading hydraulic cylinder 14 extends out of a piston rod of the loading hydraulic cylinder, sequentially passes through a through hole of a rear support vertical plate 13, a loading spring mechanism and a support copper sleeve 9, passes through a copper sleeve nut 8 at the back end of a vertical plate of a bearing support 17 to be connected with a tension pressure sensor assembly 6, and applies a locking ring 35 of a locking part on a groove plate of a locking ring motion track guide groove 5 to a locking hook which moves into a tested trigger type upper lock 4, applies a locking linear load, and measures the locking load value and the locking ring motion track of the locking part which meet the actual use working condition; and the tension and pressure sensor assembly 6 connected to the piston rod is connected to the digital display through a wire, and displays a pressurizing load value and a linear latch test load value applied to the latch hook by the latch component through the latch ring.

Compared with the prior art, the utility model has the following beneficial effects.

The utility model fixes a front bracket angle steel vertical plate 2 and a rear bracket vertical plate support 15 on a test bed 1 through a T-shaped groove bolt and a hexagon flange nut, a bearing support 17 and a guide groove installation fixing support 20 which are positioned between the front bracket angle steel vertical plate 2 and the rear bracket vertical plate support 15, a suspension pull rod 23 which penetrates through two sides of the front and rear end vertical plates and is fixedly connected with a front and rear plate end hoop 7 of the bearing support 17, a triggering type upper lock 4 which is positioned at the back end of the guide groove installation fixing support 20 and fixed on a lock ring movement track guide groove of an upper lock mounting rack 3, and the upper lock mounting rack 3 of a tested article is fixed through an installation bolt.

According to the utility model, a piston rod of a loading hydraulic cylinder extends out through the loading hydraulic cylinder 14, sequentially passes through a through hole of a rear support vertical plate 13, a loading spring 10 and a support copper sleeve 9, passes through a copper sleeve nut 8 at the back end of a vertical plate of a bearing support 17 to be connected with a tension pressure sensor assembly 6, and utilizes a lock ring 35 of a lock ring part provided on a groove plate of a lock ring motion track guide groove 5 to apply a linear load of the lock ring to a locking and unlocking lock hook moving into a tested trigger type upper lock 4, so that the size of a lock load value and the lock ring motion track of the lock ring part under the actual use condition are measured; the requirement of the lock bumping test condition is met, and the consistency with the actual installation use condition is ensured, so that the loading is reliable, and the test precision is high.

Drawings

The present invention will be described in further detail with reference to the accompanying drawings and examples.

FIG. 1 is an isometric view of an aircraft landing gear uplock latch testing apparatus of the present invention;

FIG. 2 is a schematic view of the spring-loaded mechanism shown in FIG. 1;

FIG. 3 is a schematic view of the latch member shown in FIG. 1;

FIG. 4 is a schematic view of the pull pressure sensor assembly shown in FIG. 1;

FIG. 5 is an enlarged partial view of the maximum unlocked mounting position of the uplock shown in FIG. 1;

FIG. 6 is an enlarged partial view of the uplock latch loading process 1 shown in FIG. 1;

FIG. 7 is an enlarged partial view of the uplock latch loading process 2 shown in FIG. 1;

FIG. 8 is an enlarged partial view of the final locked state of the uplock shown in FIG. 1.

In the figure: the test bed comprises a 1-T-shaped groove test bed, a 2-front support angle steel vertical plate, a 3-upper lock mounting frame, a 4-trigger type upper lock, a 5-locking ring motion track guide groove, a 6-pull pressure sensor assembly, a 7-clamp, an 8-front support copper sleeve nut, a 9-support copper sleeve, a 10-loading spring, a 13-rear support vertical plate, a 14-loading hydraulic cylinder, a 15-rear support vertical plate support, a 17-bearing support, a 20-guide groove installation and fixing support, a 23-pull rod, a 24-front end cover, a 25-transmission connecting rod, a 27- ㅠ -shaped spring seat cover, a 28-spring adjusting gasket, a 29-spring seat cover, a 30-spring locking nut, a 31-bow arm rear end cover, a 32-spring support pull rod, a 33-loading connecting block, 34-a crosshead shaft, 35-a locking ring, 36-a bushing, 37-an adjusting gasket, 38-a bearing retainer ring, 39-a shaft sleeve, 40-a deep groove ball rolling bearing, 41-a sensor connecting rod and 42-a locking nut.

To further illustrate the concept of the present invention, embodiments of the present invention will be further described with reference to the accompanying drawings.

Detailed Description

See fig. 1-4. In a preferred embodiment described below, an aircraft landing gear uplock testing device comprises: fix fore-stock angle steel riser 2 on test bench 1 through T type groove bolt and hexagonal flange face nut, back support riser support 15, be located fore-stock angle steel riser 2 and bear support 17 and guide way installation fixed bolster 20 between the rear support riser support 15, link up in front and back end riser both sides, through bearing the unsettled pull rod 23 that support 17 front and back plate end clamp 7 couples firmly, be located 20 back of the body ends of guide way installation fixed bolster, through the last lock mounting bracket 3 of the fixed article tested of installation bolt, and the spring loading mechanism that pneumatic cylinder (14) as the power supply link to each other, wherein: the upper lock mounting frame 3 is fixedly connected with a lock ring motion track guide groove 5 which is coupled and connected with the trigger type upper lock 4; the guide groove mounting and fixing support 20 is connected with a lock ring 35 through a lock ring loading connecting block 33 tail connecting sliding groove connected with a piston rod, and the trigger type upper lock 4 is movably clamped on the lock ring 35 through a locking and locking lock hook fixedly connected with the back end; the hydraulic loading cylinder 14 serves as a power source, the hydraulic loading cylinder 14 extends out of a piston rod of the hydraulic loading cylinder, sequentially passes through a through hole of a rear support vertical plate 13, a loading spring mechanism 10 and a support copper sleeve 9, passes through a copper sleeve nut 8 at the back end of the vertical plate of a bearing support 17 to be connected with a tension pressure sensor assembly 6, and applies a locking ring 35 of a locking part on a groove plate of a locking ring motion track guide groove 5 to a locking hook which moves into a tested trigger type uplock 4 to apply a linear load of locking.

The front support angle steel vertical plate 2, the rear support vertical plate support 15 and the bearing support 17 are sequentially and fixedly connected in an overlapping groove formed in the longitudinal arrangement through circumferential bolts on the test pedestal plate, the lock ring motion track guide groove 5 is fixedly connected on the vertical plate at the rear end of the guide groove installation fixing support 20, and the lock ring motion track guide groove 5 provides a reliable loading motion track for the lock ring to impact the lock hook.

Further, the uplock mounting bracket 3 is located 2 rear ends of preceding support angle steel riser, and the outside is equipped with the reinforcement L shape angle bar, and trigger formula uplock 4 is fixed on the scute of L shape angle bar, and L shape angle bar passes through the bolt fastening in the crack groove of test bench bedplate to improve the convenience of dismouting.

See fig. 2. The spring-loaded mechanism includes: the front end cover 24 and the bow arm rear end cover 31 are fixedly connected through two parallel spring frame pull rods 32 to form a spring loading frame, and the spring loading frame restrains the loading spring 10 on two opposite mirror-image-symmetrical loading spring sleeves sleeved on a cantilever shaft of the transmission connecting rod 25 through the front end cover 24. The tail part of the rod body of the transmission connecting rod 25 is provided with a step cylinder, a polished rod on the end face of the step cylinder is sleeved on the cantilever shaft through a spring seat sleeve 27 with an ㅠ -shaped section, a spring seat sleeve 29 is assembled in a central hole of the front end cover 24 in an interference fit mode, the spring seat sleeve 29 on the free end of the cantilever shaft restrains the loading spring 10 through a spring adjusting gasket 28, the spring seat sleeve 29 on the free end is in threaded connection with a locking nut 30 through a threaded hole of the cantilever shaft end to fix the loading spring 10 on the end face of the polished rod on the cantilever shaft end, and the spring seat sleeve 29 and a ㅠ -shaped support copper sleeve 9 on the front end form a spring loading mechanism. The spring loading frame is a frame of the whole spring loading structure, and other parts are combined by taking the spring loading frame as an installation reference. In order to reduce the friction force of the movement of the transmission connecting rod 25, the ㅠ -shaped spring seat sleeve 27 is assembled in the mounting hole; the spring adjusting gasket 28 is assembled at the axial installation end of the loading spring 10 to prevent the loading spring 10 from side deflection during working and generate side load to influence the accuracy of test data, and the central bow arm of the bow arm rear end cover 31 of the spring loading frame is provided with a loading hydraulic cylinder piston rod installation hole connected with the power source loading hydraulic cylinder 14.

See fig. 3. The latch member includes: the U-shaped fork bait is integrally connected with the loading connecting block 33, a cylinder body of the fork bait is inserted into a cylinder body of a locking ring 35 through an upper shaft sleeve 39 of the fork bait, the cylinder body of the locking ring 35 is clamped on a cross head shaft 34 in a U-shaped fork bait groove, the deep groove ball rolling bearing 40 is assembled at two ends of the cross head shaft 34, and the deep groove ball rolling bearing 40 assembled at the free end of the cross head shaft 34 is fixed with a bearing retainer ring 38 through a regulating gasket 37.

Furthermore, the loading connecting block 33 is provided with a kidney-shaped hole to adapt to the up-and-down fluctuation change of the movement track of the locking ring when the locking ring impacts the locking hook, a lining 36 for reducing friction force is assembled between the locking ring 35 and the cross shaft 34, the cross shaft 34 directly reduces the friction torque of a contact part through a shaft sleeve 39 on the opening end of a U-shaped fork bait groove on the loading connecting block 33, the cross shaft 34 ensures the stability of the locking movement through a deep groove ball rolling bearing 40 assembled at two ends of the cross step shaft, and meanwhile, in order to ensure that the deep groove ball rolling bearing completely moves in the locking ring movement track guide groove 5, one end of the cross shaft 34 is finely adjusted through the thickness of an adjusting gasket 37.

See fig. 4. The pulling pressure sensor assembly 6 is connected in series on the rod body of the sensor connecting rod 41, and two ends of the sensor connecting rod 41 are fixedly connected with the transmission connecting rod 25 through the locking nuts 42.

Further, a step shaft at one end of the sensor connecting rod 41 with threads is fixedly connected with the transmission connecting rod 25 through an internal thread hole of the locking nut 42, the other end of the sensor connecting rod is connected with the transmission connecting rod 25 through an internal thread hole of the locking nut 42 along the power loading direction and the spring loading mechanism, and is connected with the locking ring 35 along the locking direction of the test piece, so that the linear load value applied to the locking hook by the locking ring 35 is acquired.

See fig. 5-8. As shown in fig. 5, the trigger type uplock 4 mounted on the uplock mounting bracket 3 by a positioning latch retracts the uplock hook, and in a maximum opening state, the lock ring 35 on the inside of the lock ring movement trajectory guide groove 5 and the groove plate link groove is located at the initial position of the lock ring movement trajectory guide groove 5; after the loading hydraulic cylinder 14 is pressurized, the lock ring 35 part moves to the lock hook approaching position of the upper lock 4 along the lock ring motion track guide groove 5 at a specified motion speed as shown in fig. 6, and at the moment, the lock hook is still in a static state; continuously pressurizing the loading hydraulic cylinder 14, moving the lock ring 35 part to the inner position of the lock hook of the upper lock 4 along the lock ring motion track guide groove 5 at a specified motion speed as shown in fig. 7, rotating the lock hook at a certain angle in the upper lock direction, and simultaneously moving the lock ring 35 upwards along the kidney-shaped hole of the loading connecting block 33 corresponding to the motion track of the lock hook; after the hydraulic cylinder 14 reaches the preset stroke, as shown in fig. 8, the distance between the sensor probe and the target inside the trigger type upper lock 4 is just within the set range, the proximity trigger switch sends a locking liquid supply signal to the locking nozzle, the locking hook hooks the locking ring 35 of the locking part, the lock 35 is hooked to the final locking position, and a locking position signal is sent.

The following describes the specific movement process of the latch test device with reference to the above drawings. In the practical application process, when the upper lock is in the maximum unlocking state, the upper lock is arranged on an upper lock mounting frame 3 through a positioning bolt, an oil path of a test bed 1 is respectively connected with a locking nozzle and an unlocking nozzle of a tested object through a hose/hard tube, an upper lock proximity trigger switch is connected with a 12V direct current power supply, pressure for impacting a locking working load is loaded to a locking ring component through a loading hydraulic cylinder 14, the pressure can be directly read through a display device connected with a pull pressure sensor assembly 6, the locking ring component moves along a locking ring movement track guide groove 5 to push a locking hook to rotate to an upper locking position, when the distance between a sensor probe inside the upper lock and a target is in a set range, the proximity trigger switch sends a signal to supply hydraulic pressure to the locking nozzle of the upper lock, the locking hook hooks the locking ring to a final locking position and sends a locking position signal, wherein, the linear specific load that the shackle hooks the shackle to the final locked position is provided by a spring loaded mechanism.

The above description is only a preferred embodiment of the present invention, but not intended to limit the present invention to the scope of the described embodiments, and various modifications and changes may occur to those skilled in the art, and any modifications, equivalents and improvements made by the present invention are included in the scope of the present invention.

Claims

1. An aircraft landing gear uplock lock test device, comprising: fix fore-stock angle steel riser (2) on test bench (1) through T type groove bolt and hexagonal flange face nut, back support riser support (15), be located fore-stock angle steel riser (2) and bear support (17) and guide way installation fixed bolster (20) between back support riser support (15), link up on front and back end riser both sides, through unsettled pull rod (23) of bearing support (17) front and back plate end clamp (7) solid antithetical couplet, be located guide way installation fixed bolster (20) back end, through the fixed overhead lock mounting bracket (3) of quilt sample of installation bolt, and the spring loading mechanism that pneumatic cylinder (14) as the power supply link to each other, its characterized in that: the upper lock mounting frame (3) is fixedly connected with a lock ring motion track guide groove (5) coupled with the trigger type upper lock (4); the guide groove mounting and fixing support (20) is connected with a lock ring (35) through a lock ring loading connecting block (33) tail connecting sliding groove connected with a piston rod, and the trigger type upper lock (4) is movably clamped on the lock ring (35) through a locking and locking lock hook fixedly connected with the back end; the loading hydraulic cylinder (14) extends out of a piston rod of the loading hydraulic cylinder, sequentially passes through a through hole of a rear support vertical plate (13), a loading spring (10) and a support copper sleeve (9), passes through a bearing support (17) and a copper sleeve nut (8) at the back end of the vertical plate to be connected with a tension pressure sensor assembly (6), and utilizes a lock ring (35) provided with a locking part on a lock ring motion track guide groove (5) and a groove plate to lock and unlock a lock hook on a tested trigger type upper lock (4) in a moving mode to apply a linear load of locking.

2. An aircraft landing gear uplock testing device according to claim 1, characterised in that: the guide groove mounting and fixing support (20) is fixedly connected to an angle plate of the angle steel vertical plate (2) of the front support through bolts, and the lock ring movement track guide groove (5) is fixedly connected to a vertical plate at the rear end of the guide groove mounting and fixing support (20).

3. An aircraft landing gear uplock testing device according to claim 1, characterised in that: the upper lock mounting frame (3) is located at the rear end of the front support angle steel vertical plate (2), a reinforced L-shaped angle iron is arranged on the outer side of the front support angle steel vertical plate, the trigger type upper lock (4) is fixed on an angle plate of the L-shaped angle iron, and the L-shaped angle iron is fixed in a seam-shaped groove of the test bed plate through a bolt.

4. An aircraft landing gear uplock testing device according to claim 1, characterised in that: the spring-loaded mechanism includes: the front end cover (24) and the bow arm rear end cover (31) are fixedly connected through two parallel spring frame pull rods (32) to form a spring loading frame, and the spring loading frame restrains the loading spring (10) on two opposite mirror symmetry loading spring sleeves sleeved on a cantilever shaft of the transmission connecting rod (25) through the front end cover (24).

5. An aircraft landing gear uplock testing device according to claim 1, characterised in that: the tail part of a rod body of the transmission connecting rod (25) is provided with a step cylinder, a polished rod on the end face of the step cylinder is sleeved on the cantilever shaft through a ㅠ -shaped spring seat sleeve (27) with an ㅠ -shaped section, the spring seat sleeve (29) is assembled in a center hole of the front end cover (24) in an interference mode, the spring seat sleeve (29) on the free end of the cantilever shaft restrains the loading spring (10) through a spring adjusting gasket (28), the spring seat sleeve (29) on the free end is in threaded connection with a spring locking nut (30) through a threaded hole at the end of the cantilever shaft to fix the loading spring (10) on the end face of the polished rod at the end of the cantilever shaft, and the spring seat sleeve and a ㅠ -shaped support copper sleeve (9) on the front end form a spring loading mechanism.

6. An aircraft landing gear uplock testing device according to claim 1, characterised in that: the loading connecting block (33) is provided with a kidney-shaped hole to adapt to the up-and-down fluctuation change of a moving track of the locking ring when the locking ring impacts the locking hook, a lining (36) used for reducing friction force is assembled between the locking ring (35) and the cross head shaft (34), the cross head shaft (34) directly reduces the friction torque of a contact part through a shaft sleeve (39) on the opening end of the U-shaped fork bait groove on the loading connecting block (33), and meanwhile, in order to ensure that the deep groove ball rolling bearing completely moves in the locking ring moving track guide groove (5), one end of the cross head shaft (34) is finely adjusted through the thickness of the adjusting gasket (37).

7. An aircraft landing gear uplock testing device according to claim 1, characterised in that: the tension and pressure sensor assembly (6) is connected in series on the rod body of the sensor connecting rod (41), and two ends of the sensor connecting rod (41) are fixedly connected with the transmission connecting rod (25) through a locking nut (42).

8. An aircraft landing gear uplock testing device according to claim 1, characterised in that: a step shaft at one end of a sensor connecting rod (41) with threads is fixedly connected with a transmission connecting rod (25) through an internal thread hole of a locking nut (42), the other end of the sensor connecting rod is connected with the transmission connecting rod (25) through the internal thread hole of the locking nut (42) along a power loading direction, and is connected with a locking ring (35) component along a test piece locking direction, and the linear load value applied to a locking hook by the locking ring (35) is collected.

9. An aircraft landing gear uplock testing device according to claim 1, characterised in that: draw pressure sensor subassembly (6) to establish ties on the sensor connecting rod (41) body of rod, sensor connecting rod (41) both ends are passed through lock nut (42) and are linked firmly on transmission connecting rod (25), the sensor connecting rod (41) one end step axle that system screwed passes through lock nut (42) internal thread hole fastening connection transmission connecting rod (25), the other end passes through lock nut (42) internal thread hole, link to each other transmission connecting rod (25) with spring loading mechanism along the power loading direction, and link to each other with catch (35) part along test piece lock bumping direction, gather the linear load value size that catch (35) applyed the shackle.

10. An aircraft landing gear uplock testing device according to claim 1, characterised in that: the trigger type uplock (4) arranged on the uplock mounting frame (3) through a positioning bolt is used for retracting the uplock hook, in a maximum opening state, the uplock hook (35) in a groove plate connecting rod sliding groove of the uplock movement track guide groove (5) is positioned at the initial position of the uplock movement track guide groove (5), after the loading hydraulic cylinder (14) is pressed, the part of the uplock hook (35) moves to the near position of the uplock hook of the uplock (4) along the lock ring movement track guide groove (5) at a specified movement speed, the uplock hook is in a static state, the pressing is continuously performed to the loading hydraulic cylinder (14), the part of the uplock hook (35) moves to the internal position of the uplock hook of the uplock (4) along the lock ring movement track guide groove (5) at a specified movement speed, at the moment, the lock hook rotates by a certain angle to the uplock direction, and the lock loop (35) moves upwards along the waist-shaped hole of the loading connecting block (33), corresponding to the movement track of the lock hook, after the loading hydraulic cylinder (14) reaches a preset stroke, the distance between a sensor probe and a target in the trigger type upper lock (4) is just in a set range, the proximity trigger switch sends a locking liquid supply signal to a locking nozzle, the lock hook hooks a lock ring (35) of a lock collision component, and the lock hook is locked to a final locking position and sends a locking position signal.