Aircraft landing gear static load detection device

Abstract

The invention relates to the field of static load detection, and discloses an aircraft landing gear static load detection device which comprises a detection platform, a fixing assembly and a loading assembly are arranged on the detection platform, the fixing assembly fixes a landing gear body, the loading assembly applies a load to the landing gear body, and the aircraft landing gear static load detection device further comprises a balance maintaining assembly arranged on the loading assembly. When the loading assembly applies a load to the undercarriage main body, the balance maintaining assembly is used for maintaining the loading assembly in a horizontal placement state; according to the aircraft landing gear static load detection device, through arrangement of the balance maintaining assembly, when the landing gear main body deforms, the deformed landing gear main body extrudes the loading assembly, and the loading assembly inclines and deflects, the balance maintaining assembly adjusts the loading assembly to recover to a horizontal placement state; therefore, the situation that the static load test data of the undercarriage main body is inaccurate due to the fact that the loading assembly is in an inclined state is avoided.

Description

Technical Field

[0001] The invention relates to the field of static load detection, and in particular to a static load detection device for an aircraft landing gear. Background Art

[0002] The landing gear is an accessory device on the aircraft that supports the aircraft during takeoff, landing or ground taxiing and is used for ground movement; the landing gear is an important load-bearing and maneuverable component of the aircraft, and it shoulders an extremely important mission in the safe takeoff and landing of the aircraft; the landing gear is a necessary support system for the aircraft to take off, land, taxi, move on the ground and park, and is one of the main components of the aircraft. The quality of its performance is directly related to the use and safety of the aircraft; during the manufacturing and production of existing landing gears, in order to detect the performance of the landing gear, the landing gear is required to undergo static load tests, limit load tests, destructive tests, fatigue tests, drop shock tests, buffer system leakage tests, etc.

[0003] For example, a patent with publication number CN106240841B and publication date January 18, 2019, discloses a landing gear test loading device, which includes a main load-bearing mechanism frame composed of multiple columns, and the main load-bearing mechanism frame is fixed on the ground; a lifting platform is connected to the inside of the main load-bearing mechanism frame through a guide rail, and the lifting platform is arranged parallel to the ground, and a lifting motor system for driving the lifting platform to move is installed on the side of the lifting platform away from the ground; the landing gear is fixed to the side of the lifting platform close to the ground through a landing gear fixing support device, and a dummy wheel is installed on the other side of the landing gear, and the dummy wheel is connected to the load loading system fixed on the main load-bearing mechanism frame, so as to apply a load to the dummy wheel; the landing gear test loading device provided by the patent is used to control the stroke change of the buffer in the landing gear, and the relative position of the loading point and the wheel remains unchanged, so as to realize loading of variable stroke without manual intervention.

[0004] Some large aircraft, due to their large weight, in order to reduce the pressure of the wheels on the ground, improve the floatation of the aircraft, and avoid factors such as wheels being too large to be stored, the landing gear of existing large aircraft is generally designed in the form of a multi-wheeled trolley. The lower end of this type of landing gear is equipped with two or four (or even more) wheels in a front and rear longitudinal row through a wheel frame. When the landing gear is subjected to a static load test, the pressure plate used to provide load to the wheels contacts the multiple wheels on one side of the landing gear. When the pressure plate applies load to the wheels, due to the individual differences of each wheel during the production and assembly process, the multiple wheels cannot maintain consistent stress. The wheel frame connecting the wheels is easily deformed due to extrusion, and the height of the wheel on the deformed wheel frame will be lower than the height of the wheel on the normal wheel frame. At this time, as the loading assembly continues to apply load, the wheel on the wheel frame that has not deformed or has little deformation squeezes the loading assembly upward, which easily causes the loading assembly to deform, causing the force on the landing gear to be unbalanced, affecting the accuracy of the static load test data. Summary of the invention

[0005] The object of the present invention is to provide a static load detection device for aircraft landing gear to solve the above-mentioned deficiencies in the prior art.

[0006] In order to achieve the above object, the present invention provides the following technical solutions: A static load detection device for an aircraft landing gear comprises a detection platform, on which a fixing component and a loading component are arranged, wherein the fixing component is used to fix a landing gear body, a pressure plate of the loading component is used to apply a load to a wheel of the landing gear body, and a balance maintaining component is arranged on the loading component, wherein when the loading component applies a load to the landing gear body, the balance maintaining component is used to maintain the pressure plate in a horizontal position.

[0007] The balance maintaining assembly comprises a balance telescopic rod, which is hung on the detection platform, and the telescopic end of the balance telescopic rod is connected to the plate surface of the pressure plate away from the wheel.

[0008] As mentioned above, the balance maintaining assembly further comprises two vertically arranged guide plates, and the adjacent plate surfaces of the two guide plates are both provided with vertical guide grooves.

[0009] As mentioned above, the loading assembly includes a hydraulic telescopic rod and a contact pressure strip. The hydraulic telescopic rod is hoisted on the detection platform. The telescopic end of the hydraulic telescopic rod is connected to the center of the contact pressure strip. Two guide plates are disposed at both ends of the contact pressure strip. The two ends of the contact pressure strip are respectively inserted into the guide grooves on both sides.

[0010] As mentioned above, the detection platform is provided with an avoidance groove, the balance telescopic rod is slidably installed in the avoidance groove along the vertical direction, and the detection platform is also provided with a connecting groove, which connects the avoidance groove with the guide groove on the adjacent guide plate.

[0011] As mentioned above, a balance adjustment mechanism is also provided in the guide groove, and the balance adjustment mechanism adjusts the tilted and stuck contact pressure strip to a horizontal placement state based on the extension and retraction of the compensation telescopic sleeve.

[0012] As mentioned above, the balance telescopic rod is connected to the bottom of the avoidance groove through a limiting spring, and an extrusion wedge is fixedly mounted on the side wall of the balance telescopic rod.

[0013] The above-mentioned balance adjustment mechanism includes two rotating gears arranged at an interval up and down, and an annular transmission toothed belt is jointly sleeved on the outer sides of the two rotating gears. The transmission toothed belt is annular, and a matching toothed belt is installed on the outer circumferential surface of the transmission toothed belt. A driving rack is slidably installed in the connecting groove, and the driving rack cooperates with the matching toothed belt, and one end of the driving rack extends into the avoidance groove. A traction block is also installed on the transmission toothed belt, and the traction block includes a sliding top plate, a fixed bottom plate and a connecting side plate. The sliding top plate and the fixed bottom plate are arranged at an interval up and down, and the connecting side plate connects the sliding top plate and the fixed bottom plate. A clamping notch is formed between the sliding top plate and the fixed bottom plate, and the clamping notch is adapted to the end of the contact strip.

[0014] As mentioned above, the end of the driving rack located in the avoidance groove is spaced apart from the extrusion wedge block.

[0015] As mentioned above, the two rotating gears are connected to the guide plate via a ratchet and pawl mechanism, and the ratchet and pawl mechanism is used to limit the two rotating gears to rotate in one direction.

[0016] The beneficial effect of the present invention is that in the above technical scheme, a static load detection device for an aircraft landing gear provided by the present invention is provided with a balance maintaining component. When the landing gear body is deformed and the deformed landing gear body squeezes the loading component, causing the loading component to tilt and deflect, the balance maintaining component adjusts the loading component to return to a horizontal placement state, thereby avoiding the tilt of the loading component, which causes inaccurate static load test data of the landing gear body. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0018] Figure 1 A schematic structural diagram of a landing gear body provided by an embodiment of the present invention; Figure 2 A schematic structural diagram of a static load detection device for an aircraft landing gear provided by an embodiment of the present invention; Figure 3 A front schematic diagram of a static load detection device for an aircraft landing gear provided by an embodiment of the present invention; Figure 4 A schematic diagram of the cooperation between the loading assembly and the landing gear body provided by an embodiment of the present invention; Figure 5 A structural schematic diagram of a balance adjustment mechanism provided by an embodiment of the present invention; Figure 6The embodiment of the present invention provides Figure 5 A magnified schematic diagram of point A; Figure 7 A schematic diagram of the connection between the traction block and the transmission belt provided in an embodiment of the present invention; Figure 8 A schematic cross-sectional structure diagram of a traction block provided in an embodiment of the present invention.

[0019] Description of reference numerals: 1. Detection platform; 2. Fixing assembly; 3. Loading assembly; 31. Hydraulic telescopic rod; 32. Contact pressure strip; 4. Landing gear body; 41. Wheel; 5. Balance maintenance assembly; 51. Balance telescopic rod; 52. Guide plate; 53. Guide groove; 6. Avoidance groove; 7. Extrusion wedge block; 8. Connecting groove; 9. Balance adjustment mechanism; 91. Rotating gear; 92. Transmission toothed belt; 93. Matching toothed belt; 94. Driving rack; 95. Traction block; 951. Sliding top plate; 952. Fixed bottom plate; 953. Connecting side plate; 96. Clamping notch. DETAILED DESCRIPTION

[0020] In order to enable those skilled in the art to better understand the technical solution of the present invention, Figure 1-8 , the present invention is further introduced in detail.

[0021] An embodiment of the present invention provides an aircraft landing gear static load detection device, including a detection platform 1, on which a fixing component 2 and a loading component 3 are arranged, the fixing component 2 is used to fix a landing gear body 4, the loading component 3 applies a load to the landing gear body 4, and also includes a balance maintaining component 5 arranged on the loading component 3, when the loading component 3 applies a load to the landing gear body 4, the balance maintaining component 5 is used to maintain the loading component 3 in a horizontal position.

[0022] Specifically, the aircraft landing gear static load detection device provided by the present invention is used to perform a static load test on the aircraft landing gear. The landing gear body 4 is mainly composed of a buffer strut, a wheel frame and a plurality of wheels 41 (the composition of the landing gear body 4 is the prior art, and the specific structure is not repeated). In this embodiment, the detection platform 1 includes a bottom plate and an upper frame. When performing the test, the bottom plate of the detection platform 1 is fixedly installed on the ground by bolts. The bottom plate and the upper frame of the detection platform 1 are both provided with a plurality of mounting holes. The fixing assembly 2 is installed on the mounting holes on the bottom plate, and the loading assembly 3 is installed in the mounting holes on the upper frame. Among them, the fixing assembly 2 can be selected as a common fixing sleeve and locking bolt. The fixing sleeve is in a cylindrical state. The fixing sleeve is installed on the bottom plate of the detection platform 1 through the mounting hole. The upper surface of the fixing sleeve is provided with a mounting notch for placing the landing gear body 4. When the landing gear body 4 needs to be installed, the staff inserts the landing gear body 4 into the mounting notch on the fixing sleeve, and then locks the landing gear by bolts. The main body 4 is fixed (it should be noted that the fixing method of the landing gear main body 4 on the fixing sleeve is not unique, and magnetic locking or latch fixing and other methods can also be used to stably fix the landing gear main body 4), and the loading component 3 can use a combination of a telescopic member and a pressure plate, the telescopic member is arranged on the upper frame of the detection platform 1, and the loading component 3 is located above the fixing component 2, wherein the telescopic member is vertically arranged, and the telescopic end of the telescopic member is connected to the center of the pressure plate, and the pressure plate is against the upper surface of the wheel 41 under the action of the telescopic member. When it is necessary to perform a static load test on the landing gear main body 4, the landing gear main body 4 is manually moved to the detection platform 1 using mechanical equipment, and then the staff fixes the landing gear main body 4 on the detection platform 1 through the fixing component 2, and then the telescopic member on the loading component 3 begins to extend, and the telescopic member presses on the surface of the wheel 41 of the landing gear main body 4 with the pressure plate, and then, the load force is applied to the landing gear main body 4 through the extension of the telescopic member to perform a static load test on the landing gear main body 4.

[0023] Obviously, some large aircrafts have a large weight. In order to reduce the pressure of the wheels 41 on the ground and improve the buoyancy of the aircraft, and to avoid the factors such as the wheels 41 being too large to be stored, the landing gears of existing large aircrafts are generally designed in the form of a multi-wheeled cart. The lower end of the landing gear of this form is equipped with two or four (or even more) wheels 41 in a front and rear longitudinal row through a wheel frame. In this embodiment, the wheel frame of the selected landing gear body 4 is equipped with a total of four wheels 41. When a static load test is required, in order to simulate the ground to apply pressure to the landing gear body 4, the landing gear body 4 is usually placed upside down (at this time, the distance between the wheels 41 and the detection platform 1 is the farthest), and the wheels 41 on the landing gear of the aircraft are usually symmetrically distributed. In order to detect asymmetric problems in design or manufacturing and ensure the stability and safety of the landing gear body 4, when performing a static load test, the wheels 41 on both sides of the landing gear body 4 are usually pressed separately. That is, in this embodiment In the embodiment, two groups of loading components 3 are provided, and the pressure plates on each group of loading components 3 are in contact with two wheels 41 on one side of the landing gear body 4. When the pressure plates apply load to the two wheels 41 below, due to the individual differences of each wheel 41 during the production and assembly process, the two wheels 41 cannot maintain consistency in stress, and the wheel frame connected to the wheels 41 is easily deformed due to extrusion. The height of the wheel 41 on the deformed wheel frame will be lower than the height of the wheel 41 on the normal wheel frame. At this time, as the loading component 3 continues to apply load, the wheel 41 on the wheel frame that has not been deformed or has a small deformation will press one side of the pressure plate upward. Under the extrusion of this force, the pressure plate is easily deformed and deflected around the connection position with the telescopic member (similar to a lever), and the deformed pressure plate is transformed into an inclined placement state. When the inclined pressure plate applies load to the landing gear body 4, the load force on the landing gear body 4 is not vertically downward, thereby affecting the accuracy of the static load test data of the landing gear body 4.

[0024] In order to solve the above problem, a balance maintaining component 5 is further provided on the loading component 3. When the loading component 3 applies a load to the landing gear body 4, the balance maintaining component 5 is used to maintain the pressure plate of the loading component 3 in a horizontal position.

[0025] Specifically, in the present embodiment, the balance maintaining assembly 5 comprises two balance telescopic rods 51, and the two balance telescopic rods 51 are both arranged on the upper frame of the detection platform 1, wherein the two balance telescopic rods 51 correspond to the two wheels 41 one by one, and the telescopic ends of the two balance telescopic rods 51 are both connected to the plate surface of the pressure plate away from the wheel 41, and the connection position is located directly above the corresponding wheel 41, wherein the telescopic amount of the two balance telescopic rods 51 is consistent with the telescopic part in the loading assembly 3; when the landing gear body 4 is subjected to a static load test, due to the individual differences of each wheel 41 during the production and assembly process, it is almost impossible for the two wheels 41 to maintain completely consistent stress. If the wheel frame of one of the wheels 41 connected to the wheel 41 is deformed due to extrusion and has a vertical displacement greater than that of the other wheel 41, the corresponding connected wheel 41 will be deformed. The height of wheel 41 is lower than that of the normal wheel 41 on the wheel frame, or in other words, the reverse extrusion force of the wheel 41 on the pressure plate is smaller than that of the other wheel 41. As the loading assembly 3 continues to apply load, the wheel 41 on the wheel frame that has not been deformed or, more precisely, has a smaller deformation, exerts a greater reverse force on the pressure plate to press upward. However, the corresponding balancing telescopic rod 51 supports the pressure plate on the other side of the pressure plate, preventing the pressure plate from tilting and deflecting around the connection position of the telescopic part on the loading assembly 3 under the pressure of the normal wheel 41, thereby avoiding the pressure plate from tilting. That is, during the subsequent static load test, the pressure plate of the loading assembly 3 is always in a horizontal position, and the load direction applied to the landing gear body 4 is always downward, thereby avoiding the occurrence of inaccurate static load test data of the landing gear body 4 due to the tilt of the pressure plate in the loading assembly 3.

[0026] Preferably, the balance maintaining assembly 5 also includes two vertically arranged guide plates 52, and the adjacent plate surfaces of the two guide plates 52 are provided with vertical guide grooves 53, wherein the loading assembly 3 includes a hydraulic telescopic rod 31 and a contact pressure strip 32, wherein the hydraulic telescopic rod 31 is the above-mentioned telescopic part, and the contact pressure strip 32 is the above-mentioned pressure plate, and the hydraulic telescopic rod 31 is hoisted on the upper frame of the detection platform 1, and the telescopic end of the hydraulic telescopic rod 31 is connected to the center of the contact pressure strip 32, wherein the two guide plates 52 are disposed at both ends of the contact pressure strip 32, and the two ends of the contact pressure strip 32 are respectively inserted into the guide grooves 53 on both sides.

[0027] Specifically, when the landing gear body 4 is subjected to a static load test, as the hydraulic telescopic rod 31 is extended, the contact pressure strip 32 applies a load to the surface of the wheel 41. At this time, the guide grooves 53 on the guide plates 52 on both sides of the contact pressure strip 32 guide the downward movement of the contact pressure strip 32 and limit the movement of the contact pressure strip 32 in the front and rear directions, thereby ensuring that the area of ​​the contact pressure strip 32 applying the load force to the wheel 41 remains stable, thereby avoiding the contact pressure strip 32 from tilting in the front and rear directions, resulting in a large difference in the contact area between the two wheels 41 on the landing gear body 4 and the contact pressure strip 32, causing uneven force on the landing gear body 4, thereby causing inaccurate static load test data.

[0028] It should also be noted that, in this embodiment, in order to adapt to the static load test of different models of landing gear bodies 4, the guide plate 52 is detachably mounted on the detection platform 1 by bolts, so as to facilitate the adjustment of the position of the guide plate 52 on the detection platform 1.

[0029] Obviously, in the present embodiment, the downward movement of the contact pressure strip 32 is based on the joint action of the hydraulic telescopic rod 31 and the two balancing telescopic rods 51, and in order to keep the contact pressure strip 32 always in a horizontal state, the extension and contraction amounts of the hydraulic telescopic rod 31 and the two balancing telescopic rods 51 need to be kept consistent at all times. However, after the hydraulic telescopic rod 31 and the two balancing telescopic rods 51 have been used for a long time, due to aging, wear or other problems, the extension and contraction amounts between the hydraulic telescopic rod 31 and the two balancing telescopic rods 51 are easily inconsistent. At this time, when the contact pressure strip 32 slides along the guide groove 53, the contact pressure strip 32 is easy to tilt and get stuck in the guide groove 53, affecting the normal progress of the static load test.

[0030] In order to solve the above problems, preferably, the hydraulic telescopic rod 31 is rotatably connected to the contact pressure strip 32, and the two balancing telescopic rods 51 are also rotatably connected to the contact pressure strip 32, wherein a avoidance groove 6 is provided on the upper frame of the detection platform 1, and one of the balancing telescopic rods 51 is slidably installed in the avoidance groove 6 along the vertical direction, and the balancing telescopic rod 51 is connected to the bottom of the avoidance groove 6 through a limiting spring, and an extrusion wedge 7 is also fixedly installed on the side wall of the balancing telescopic rod 51; a connecting groove 8 is also provided on the upper frame of the detection platform 1, and the connecting groove 8 connects the avoidance groove 6 with the closest guide plate 52 The guide grooves 53 are connected, and a balance adjustment mechanism 9 is also arranged in the guide groove 53. The balance adjustment mechanism 9 adjusts the tilted and stuck contact pressure strip 32 to a horizontal placement state based on the movement of the balance telescopic rod 51 in the avoidance groove 6; the balance adjustment mechanism 9 includes two rotating gears 91 spaced apart from each other, and the two rotating gears 91 are connected to the guide plate 52 through a ratchet and pawl mechanism, and the ratchet and pawl mechanism is used to limit the two rotating gears 91 to rotate in one direction, and the outer sides of the two rotating gears 91 are jointly sleeved with an annular transmission toothed belt 92, and the transmission toothed belt 92 is annular, and the outer side of the transmission toothed belt 92 A matching toothed belt 93 is installed on the circular surface, and a driving rack 94 is slidably installed in the connecting groove 8. The driving rack 94 cooperates with the matching toothed belt 93, and one end of the driving rack 94 extends into the avoidance groove 6 and is spaced between the surface of the extrusion wedge block 7 (preferably, the end has an inclined surface to form a wedge-shaped fit with the extrusion wedge block 7). A traction block 95 is also installed on the transmission toothed belt 92. The traction block 95 includes a sliding top plate 951, a fixed bottom plate 952 and a connecting side plate 953. The connecting side plate 953 is connected to the transmission toothed belt 92, and the sliding top plate 951 and the fixed bottom plate 952 are spaced apart. The upper and lower plates are arranged at intervals, and the connecting side plates 953 connect the sliding top plate 951 and the fixed bottom plate 952. A clamping notch 96 is formed between the sliding top plate 951 and the fixed bottom plate 952. The clamping notch 96 is adapted to the end of the contact strip 32, and the clamping notch 96 is used to clamp the end of the contact strip 32. The sliding top plate 951 is slidably installed on the connecting side plates 953, and the sliding top plate 951 and the connecting side plates 953 are connected by a traction spring. The side of the sliding top plate 951 close to the landing gear body 4 is in an inclined shape, and the sliding top plate 951 is shorter than the length of the fixed bottom plate 952.

[0031] Specifically, it should be noted that when the connection positions of the balancing telescopic rod 51 and the hydraulic telescopic rod 31 on the detection platform 1 are at the same height, the contact pressure strip 32 is kept in a horizontal state under the joint action of the hydraulic telescopic rod 31 and the two balancing telescopic rods 51. At this time, the limiting spring connecting the balancing telescopic rod 51 is in a compressed state, and the compressed state is not a compression limit state, that is, the limiting spring can continue to be compressed, and because the two rotating gears 91 are connected to the guide plate 52 through the ratchet pawl mechanism, the two rotating gears 91 can only rotate in one direction on the guide plate 52 (wherein, it should be noted that when the two rotating gears 91 rotate, if they are far away from the starting point, the contact pressure strip 32 will be in a horizontal state. The transmission toothed belt 92 on one side of the landing gear body 4 moves downward, then the traction block 95 is fixed on the transmission toothed belt 92 on the side away from the landing gear body 4. Conversely, if the transmission toothed belt 92 on the side close to the landing gear body 4 moves downward, then the traction block 95 is fixed on the transmission toothed belt 92 on the side close to the landing gear body 4). Therefore, in this embodiment, the traction block 95 is fixedly installed on the transmission toothed belt 92 on the side away from the landing gear body 4, that is, the two rotating gears 91 rotate in a clockwise direction, wherein the inclined surface of the sliding top plate 951 is inclined from top to bottom toward the direction of the landing gear body 4, and, in the initial state, the contact pressure strip 32 is located above the two traction blocks 95.

[0032] Therefore, the steps of performing a static load test on the landing gear body 4 are as follows: First, the landing gear body 4 to be subjected to the static load test is manually moved to the testing platform 1 in an inverted state by mechanical equipment, and then the landing gear body 4 is fixed by the fixing assembly 2 to complete the fixing of the landing gear body 4; Subsequently, the hydraulic telescopic rod 31 and the two balancing telescopic rods 51 begin to extend, and the contact pressure strip 32 approaches the surface of the wheel 41 of the landing gear body 4 in the vertical direction. When the contact pressure strip 32 moves along the guide groove 53 on the guide plate 52, the end of the contact pressure strip 32 contacts the inclined surface of the sliding top plate 951 of the corresponding traction block 95 in the guide plate 52, and as the contact pressure strip 32 moves, the contact pressure strip 32 presses the inclined surface of the sliding top plate 951, and the sliding top plate 951 moves on the connecting side plate 953 toward the side away from the landing gear body 4. The sliding top plate 951 slides in the opposite direction. At this time, the traction spring connected to the sliding top plate 951 is deformed and accumulates elastic potential energy. As the sliding top plate 951 slides, the sliding top plate 951 avoids the contact pressure strip 32, and the contact pressure strip 32 continues to move into the clamping gap 96 between the sliding top plate 951 and the fixed bottom plate 952. At this time, the sliding top plate 951 loses the restriction of the contact pressure strip 32, and the traction spring releases the accumulated elastic potential energy, and the sliding top plate 951 returns to its initial position. The sliding top plate 951 cooperates with the fixed bottom plate 952 to cover the upper and lower sides of the contact pressure strip 32; Afterwards, the hydraulic telescopic rod 31 and the two balancing telescopic rods 51 continue to extend until the contact pressure strip 32 abuts against the surface of the wheel 41 of the landing gear body 4, and the contact pressure strip 32 applies a load to the landing gear body 4 to perform a static load test; Moreover, one of the balancing telescopic rods 51 is slidably installed in the avoidance groove 6 along the vertical direction, and the balancing telescopic rod 51 can move along the vertical direction on the detection platform 1, that is, the balancing telescopic rod 51 is movably installed on the detection platform 1, and the balancing telescopic rod 51 and the detection platform 1 are flexibly connected. Obviously, when the contact pressure strip 32 is stuck, the side of the contact pressure strip 32 connected by the balancing telescopic rod 51 only has two situations of tilting upward or downward. At this time, the telescopic amount of the flexible balancing telescopic rod 51 is less than or greater than the telescopic length of the hydraulic telescopic rod 31 and the other balancing telescopic rod 51; When the telescopic length of the balancing telescopic rod 51 is greater than the telescopic length of the hydraulic telescopic rod 31 and the other balancing telescopic rod 51: as the balancing telescopic rod 51 is extended, the limiting spring connected to the balancing telescopic rod 51 contracts, and the balancing telescopic rod 51 moves vertically toward the avoidance groove 6 of the detection platform 1. The position of the balancing telescopic rod 51 on the detection platform 1 is higher than that of the other balancing telescopic rods 51 and the hydraulic telescopic rod 31. There is a height difference between the balancing telescopic rod 51 and the other balancing telescopic rods 51 and the hydraulic telescopic rod 31. The height difference is used to compensate for the extra extension length of the balancing telescopic rod 51, so that the balancing telescopic rod 51 and the contact pressure strip are aligned. The connection position of 32 is consistent in height with the connection positions of the remaining balancing telescopic rods 51, the hydraulic telescopic rod 31 and the contact pressure strip 32 in the vertical direction, so as to realize self-balancing of the contact pressure strip 32. At this time, the stuck state of the contact pressure strip 32 is released, and the contact pressure strip 32 can continue to move downward under the action of the balancing telescopic rod 51 and the hydraulic telescopic rod 31 to carry out a static load test; and, because there is a gap between the extrusion wedge block 7 and the driving rack 94, the gap provides a certain space margin for the upward movement of the extrusion wedge block 7. As the extrusion wedge block 7 moves upward, the driving rack 94 will not be squeezed immediately to move, and the self-balancing of the contact pressure plate can be realized by limiting the contraction of the spring.

[0033] When the telescopic length of the balanced telescopic rod 51 is less than the telescopic length of the hydraulic telescopic rod 31 and the other balanced telescopic rod 51: as the balanced telescopic rod 51 continues to extend, under the action of the reaction force, the limiting spring connected to the balanced telescopic rod 51 contracts, and the balanced telescopic rod 51 moves toward the avoidance groove 6 of the detection platform 1 in the vertical direction, and the extrusion wedge block 7 on the balanced telescopic rod 51 moves synchronously into the avoidance groove 6, and the wedge surface of the extrusion wedge block 7 squeezes the end of the driving rack 94, and the driving rack 94 moves along the connecting groove 8 in the direction away from the landing gear body 4, and the driving rack 94 is meshed with the matching toothed belt 93, and the matching toothed belt 93 drives the transmission toothed belt 92 to move synchronously. The transmission toothed belt 92 rotates the rotating gear 91 in a clockwise direction, so that the traction block 95 on the transmission toothed belt 92 away from the side of the landing gear body 4 moves downward synchronously. At this time, the traction block 95 applies a downward thrust to one end of the contact pressure strip 32. At this time, the contact pressure strip 32 moves downward synchronously with the balancing telescopic rod 51 as a whole. When the connection position between the balancing telescopic rod 51 and the contact pressure strip 32 and the connection position between the hydraulic telescopic rod 31 and the contact pressure strip 32 reach the same height, the stuck state of the contact pressure strip 32 is released, and the contact pressure strip 32 can continue to move downward under the action of the balancing telescopic rod 51 and the hydraulic telescopic rod 31, and the static load test can continue.

[0034] It should also be noted that the two balancing telescopic rods 51 can also be changed into a flexible state, that is, two avoidance grooves 6 and two connecting grooves 8 are provided on the detection platform 1, the two avoidance grooves 6 correspond to the two balancing telescopic rods 51 respectively, and the two connecting grooves 8 correspond to the two avoidance grooves 6 one by one, and the connecting groove 8 connects the corresponding avoidance groove 6 with the guide groove 53 on the guide plate 52 closest to it. At this time, there are balance adjustment mechanisms 9 in the guide grooves 53 in the two guide plates 52. When the contact pressure strip 32 is stuck, the balance adjustment mechanism 9 on both sides of the contact pressure strip 32 is adjusted. The mechanisms 9 work together to release the stuck state of the contact pressure strip 32. When the contact pressure strip 32 is stuck, with one of the balancing telescopic rods 51 as a reference, the end of the contact pressure strip 32 close to the balancing telescopic rod 51 will appear in two states of tilting upward or tilting downward, and the other end of the contact pressure strip 32 will appear in a state of tilting downward or tilting upward. At this time, the balance adjustment mechanisms 9 on both sides of the contact pressure strip 32 repeat the above movement process according to the tilt state of the corresponding end of the contact pressure strip 32, so as to prevent the contact pressure strip 32 from getting stuck.

[0035] Furthermore, if the balancing telescopic rod 51 is damaged, the balancing telescopic rod 51 cannot continue to support the contact pressure strip 32. At the moment of damage, the landing gear body 4 applies an upward reaction force to the contact pressure strip 32, which may easily cause damage to the connection position between the contact pressure strip 32 and the hydraulic telescopic rod 31 (in severe cases, the hydraulic telescopic rod 31 may even be damaged). However, in this embodiment, since the rotating gear 91 is connected to the guide plate 52 through a ratchet and pawl mechanism, the rotating gear 91 can only rotate in one direction. When the balancing telescopic rod 51 is damaged, the traction block 95 still limits the upward movement of the contact pressure strip 32, thereby protecting the connection position between the contact pressure strip 32 and the hydraulic telescopic rod 31 and avoiding damage to the hydraulic telescopic rod 31.

[0036] Obviously, the static load test needs to be carried out multiple times. Therefore, in this embodiment, the ratchet pawl mechanism can be unlocked, and the unlocked ratchet can rotate back and forth. This is a prior art and its principle will not be repeated. Therefore, after the static load test is completed, the ratchet pawl mechanism is unlocked, the hydraulic telescopic rod 31 is retracted, and the contact pressure strip 32 is returned to the initial position, waiting for the next round of static load test.

[0037] The above description is only by way of illustration of certain exemplary embodiments of the present invention. It is undoubted that those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. An aircraft landing gear static load detection device, comprising a detection platform (1), on which a fixing component (2) and a loading component (3) are arranged, wherein the fixing component (2) is used to fix a landing gear body (4), and a pressure plate of the loading component (3) is used to apply a load to a wheel of the landing gear body (4), characterized in that: Also includes: A balance maintaining component (5) is arranged on the loading component (3), and when the loading component (3) applies a load to the landing gear body (4), the balance maintaining component (5) is used to maintain the pressure plate in a horizontal placement state.

2. The static load detection device for aircraft landing gear according to claim 1, characterized in that: The balance maintaining assembly (5) comprises a balance telescopic rod (51), the balance telescopic rod (51) is suspended on the detection platform (1), and the telescopic end of the balance telescopic rod (51) is connected to the plate surface of the pressure plate away from the machine wheel (41).

3. The static load detection device for aircraft landing gear according to claim 2, characterized in that: The balance maintaining assembly (5) further comprises two vertically arranged guide plates (52), and adjacent plate surfaces of the two guide plates (52) are both provided with vertical guide grooves (53).

4. The aircraft landing gear static load detection device according to claim 3, characterized in that: The loading assembly (3) comprises a hydraulic telescopic rod (31) and a contact pressure strip (32). The hydraulic telescopic rod (31) is hoisted on the detection platform (1). The telescopic end of the hydraulic telescopic rod (31) is connected to the center of the contact pressure strip (32). Two guide plates (52) are respectively disposed at two ends of the contact pressure strip (32). The two ends of the contact pressure strip (32) are respectively inserted into the guide grooves (53) on both sides.

5. The aircraft landing gear static load detection device according to claim 4, characterized in that: The detection platform (1) is provided with an avoidance groove (6), and the balance telescopic rod (51) is slidably installed in the avoidance groove (6) along the vertical direction. The detection platform (1) is also provided with a connecting groove (8), and the connecting groove (8) connects the avoidance groove (6) with a guide groove (53) on a nearby guide plate (52).

6. The aircraft landing gear static load detection device according to claim 4, characterized in that: A balance adjustment mechanism (9) is also provided in the guide groove (53), and the balance adjustment mechanism (9) adjusts the tilted and stuck contact pressure strip (32) to a horizontal placement state based on the extension and retraction of the compensation telescopic sleeve (7).

7. The aircraft landing gear static load detection device according to claim 6, characterized in that: The balancing telescopic rod (51) is connected to the bottom of the avoidance groove (6) via a limiting spring, and an extrusion wedge (7) is fixedly mounted on the side wall of the balancing telescopic rod (51).

8. The aircraft landing gear static load detection device according to claim 7, characterized in that: The balance adjustment mechanism (9) comprises two rotating gears (91) spaced apart from each other, an annular transmission toothed belt (92) being sleeved on the outer sides of the two rotating gears (91), the transmission toothed belt (92) being annular, a matching toothed belt (93) being mounted on the outer circumferential surface of the transmission toothed belt (92), a driving rack (94) being slidably mounted in the connecting groove (8), the driving rack (94) matching the matching toothed belt (93), and one end of the driving rack (94) extending into the avoidance groove (6), the transmission toothed belt (92) A traction block (95) is also installed on the top, and the traction block (95) includes a sliding top plate (951), a fixed bottom plate (952) and a connecting side plate (953). The sliding top plate (951) and the fixed bottom plate (952) are arranged with an upper and lower interval, and the connecting side plate (953) connects the sliding top plate (951) and the fixed bottom plate (952). A clamping notch (96) is formed between the sliding top plate (951) and the fixed bottom plate (952), and the clamping notch (96) is adapted to the end of the contact pressure strip (32).

9. The aircraft landing gear static load detection device according to claim 8, characterized in that: An end of the driving rack (94) located in the avoidance groove (6) is spaced apart from the extrusion wedge (7).

10. The aircraft landing gear static load detection device according to claim 9, characterized in that: The two rotating gears (91) and the guide plate (52) are connected via a ratchet and pawl mechanism, and the ratchet and pawl mechanism is used to limit the two rotating gears (91) from rotating in one direction.

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