Aerodynamic load simulation test device suitable for aircraft landing gear cabin door

Abstract

The invention discloses an aerodynamic load simulation test device suitable for an aircraft landing gear cabin door, which comprises a test bed, a uniformly distributed loading unit and a follow-up loading unit, and is characterized in that when a loading simulation test is carried out, along with the opening of the cabin door of a test piece, a loading driver drives a follow-up loading frame to rotate; the follow-up loading frame transmits acting force to the loading point position element through the force transmission mechanism, the direction and the size are kept unchanged, normal loading along the cabin door of the test piece is achieved, the acting force applied by the follow-up loading frame is distributed to a plurality of loading points on the surface of the cabin door through the force transmission mechanism, the load actually borne by the cabin door is simulated, and the force transmission rods are flexibly connected. Therefore, the load fluctuation in the movement process is reduced, a powerful basis is provided for evaluating the deformation condition of the cabin door, and the influence of the aerodynamic load on the cabin door driving actuator cylinder and the influence on the locking performance can be evaluated. The test bench utilizes the clamping mechanism to clamp the test piece, so that the structural stability of the test piece is ensured, and the portal frame provides stable support for the clamping mechanism.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft testing and peripheral supporting facilities thereof, in particular to an aerodynamic load simulation test device suitable for an aircraft landing gear door. Background Art

[0002] The aircraft landing gear door opens or closes as the landing gear is retracted or extended during takeoff and landing. During the door opening and closing process, due to the influence of airflow, the door will be deformed by the aerodynamic load, which may cause the door to be unable to lock or fatigue damage. The aerodynamic load will also be transmitted to the door actuator, which will also affect the locking of the door. The safety and reliability of the door are crucial to the flight safety of the aircraft.

[0003] The actual aerodynamic load on the aircraft landing gear door is always along the normal direction of the door, and the loading direction needs to change with the rotation of the door. Existing aerodynamic load loading tests are usually for static processes, and the load direction and magnitude cannot be changed at any time. The load on the simulated door is quite different from the actual load on the door, and it is difficult to analyze and evaluate the deformation of the door in actual operation. Summary of the invention

[0004] The purpose of the present invention is to provide an aerodynamic load simulation test device suitable for an aircraft landing gear door, so as to solve the problems existing in the above-mentioned related technologies, so that the test device can simulate the actual loads on the aircraft landing gear door, provide a strong basis for evaluating the deformation of the aircraft landing gear door, and help to improve the structural reliability of the aircraft landing gear door.

[0005] To achieve the above object, the present invention provides the following solutions:

[0006] The present invention provides an aerodynamic load simulation test device suitable for an aircraft landing gear door, comprising:

[0007] A test bench, the test bench comprising a gantry and a clamping mechanism, the clamping mechanism is connected to the gantry, and the clamping mechanism can clamp a fixed structure of a test piece;

[0008] A uniform loading unit, the uniform loading unit comprising a loading point element and a force transmission mechanism, the loading point element being fixable on the hatch of the test piece, the force transmission mechanism being flexibly connected to the loading point element so that the force transmitted by the force transmission mechanism to the loading point element is always perpendicular to the hatch of the test piece;

[0009] A follower loading unit, the follower loading unit includes a follower loading frame and a loading driver, the follower loading frame is rotatably connected to the test bench, and the rotation axis of the follower loading frame is colinear with the rotation axis of the hatch of the test piece, the loading driver is arranged on the gantry, the loading driver is transmission-connected to the follower loading frame; the follower loading frame is connected to the force transmission mechanism.

[0010] Preferably, the loading point element is made of a flexible material, and the loading point element can fit in with and be adhered to the hatch of the test piece.

[0011] Preferably, the number of the loading point elements is multiple groups, and the loading point elements are all flexibly connected to the force transmission mechanism by using steel wire ropes.

[0012] Preferably, the loading point element and the connection position between the force transmission mechanism and the steel wire rope can be adjusted to achieve regulation of the loading direction and the loading load.

[0013] Preferably, the force transmission mechanism is a lever force transmission mechanism.

[0014] Preferably, the follow-up loading frame includes a loading rocker arm and a loading beam, the two loading rocker arms are rotatably connected to the gantry, the output end of the loading driver is transmission-connected to one of the loading rocker arms, the ends of the two loading rocker arms away from the gantry are connected to the loading beam, the loading beam is parallel to the rotation axis of the loading rocker arm, and the loading beam is connected to the force transmission mechanism.

[0015] Preferably, the loading rocker arm and the loading crossbeam are provided with weight-reducing holes; and a reinforcement angle bracket is also provided at the connection between the loading rocker arm and the loading crossbeam;

[0016] A tension sensor is arranged on the loading crossbeam, and the tension sensor is connected to the force transmission mechanism by a traction ring.

[0017] Preferably, the loading rocker arm is rotatably connected to the gantry by a loading shaft, and a bearing seat is arranged between the loading shaft and the gantry;

[0018] The follow-up loading unit also includes a counterweight block, and the counterweight block is arranged on the loading rocker arm.

[0019] Preferably, the gantry frame comprises a gantry column and a suspension beam, and the two gantry columns are respectively connected to the two ends of the suspension beam;

[0020] The test bench also includes a platform crossbeam, a platform longitudinal beam and a clamping column. The two platform crossbeams and the two platform longitudinal beams form a rectangular frame structure. The gantry column is connected to the platform longitudinal beam, the clamping column is connected to the platform crossbeam, and the clamping column is arranged parallel to the gantry column.

[0021] Preferably, the clamping mechanism includes a hoisting adjustment beam, a first clamp and a second clamp, the hoisting adjustment beam is connected to the suspension beam, the first clamp is connected to the hoisting adjustment beam, and the first clamp can fix the top of the fixed structure of the test piece, the second clamp is connected to the platform longitudinal beam, and the connection position of the second clamp and the platform longitudinal beam can be adjusted, and the second clamp can fix the back of the fixed structure of the test piece.

[0022] Compared with the related art, the present invention has achieved the following technical effects: the pneumatic load simulation test device suitable for the door of an aircraft landing gear of the present invention comprises a test bench, a uniform loading unit and a follow-up loading unit, the test bench comprises a gantry and a clamping mechanism, the clamping mechanism is connected to the gantry, and the clamping mechanism can clamp the fixed structure of the test piece; the uniform loading unit comprises a loading point element and a force transmission mechanism, the loading point element can be fixed on the door of the test piece, the force transmission mechanism is flexibly connected to the loading point element, so that the force transmitted by the force transmission mechanism to the loading point element is always perpendicular to the door of the test piece; the follow-up loading unit comprises a follow-up loading frame and a loading driver, the follow-up loading frame is rotatably connected to the test bench, and the rotation axis of the follow-up loading frame is colinear with the rotation axis of the door of the test piece, the loading driver is arranged on the gantry, and the loading driver is transmission-connected to the follow-up loading frame; the follow-up loading frame is connected to the force transmission mechanism.

[0023] The pneumatic load simulation test device for aircraft landing gear doors of the present invention, when performing a loading simulation test, as the door of the test piece is opened, the loading driver drives the follower loading frame to rotate, and the follower loading frame uses a force transmission mechanism to transmit the force to the loading point element. Since the force transmission mechanism is flexibly connected to the loading point element, the force transmitted by the force transmission mechanism to the loading point element is always perpendicular to the door of the test piece, and the normal loading of the door of the test piece is realized, simulating the actual load on the door, thereby providing a strong basis for evaluating the deformation of the door, and at the same time, it is also conducive to evaluating the influence of the pneumatic load on the door drive actuator and the locking performance. The test bench uses a clamping mechanism to clamp the test piece, which ensures the structural stability of the test piece during the test, and the gantry provides stable support for the clamping mechanism. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or related technologies, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0025] Figure 1 It is an axonometric schematic diagram of an aerodynamic load simulation test device suitable for an aircraft landing gear door of the present invention;

[0026] Figure 2 It is a front view schematic diagram of the aerodynamic load simulation test device applicable to the aircraft landing gear door of the present invention;

[0027] Figure 3 It is a side view schematic diagram of the aerodynamic load simulation test device applicable to the aircraft landing gear door of the present invention;

[0028] Figure 4 The diagram is a top view of the aerodynamic load simulation test device suitable for an aircraft landing gear door according to the present invention.

[0029] In the figure: 1, test bench; 101, gantry; 102, clamping mechanism; 103, gantry column; 104, suspension beam; 105, platform beam; 106, platform longitudinal beam; 107, clamping column; 108, hoisting adjustment beam; 109, first fixture; 110, second fixture;

[0030] 2. Uniformly distributed loading unit; 201. Loading point element; 202. Force transmission mechanism; 203. Steel wire rope;

[0031] 3. Follow-up loading unit; 301. Follow-up loading frame; 302. Loading driver; 303. Loading rocker arm; 304. Loading crossbeam; 305. Weight reduction hole; 306. Sensor base; 307. Tension sensor; 308. Loading shaft; 309. Bearing seat; 310. Counterweight block; 311. Reinforcement angle code;

[0032] 4. Test piece. DETAILED DESCRIPTION

[0033] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0034] The purpose of the present invention is to provide an aerodynamic load simulation test device suitable for an aircraft landing gear door, so as to solve the problems existing in the above-mentioned related technologies, so that the test device can simulate the actual loads on the aircraft landing gear door, provide a strong basis for evaluating the deformation of the aircraft landing gear door, and help to improve the structural reliability of the aircraft landing gear door.

[0035] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0036] Embodiment 1

[0037] This embodiment provides an aerodynamic load simulation test device suitable for aircraft landing gear doors. Figure 1-Figure 4 , including a test bench 1, a uniformly distributed loading unit 2 and a follower loading unit 3, the test bench 1 includes a gantry 101 and a clamping mechanism 102, the clamping mechanism 102 is connected to the gantry 101, and the clamping mechanism 102 can clamp the fixed structure of the test piece 4; the uniformly distributed loading unit 2 includes a loading point element 201 and a force transmission mechanism 202, the loading point element 201 can be fixed on the hatch of the test piece 4, and the force transmission mechanism 202 is flexibly connected to the loading point element 201 so that the force transmission mechanism 202 The force transmitted to the loading point element 201 is always perpendicular to the hatch of the test piece 4; the follow-up loading unit 3 includes a follow-up loading frame 301 and a loading driver 302, the follow-up loading frame 301 is rotatably connected to the test bench 1, and the rotation axis of the follow-up loading frame 301 is colinear with the rotation axis of the hatch of the test piece 4, the loading driver 302 is arranged on the gantry 101, and the loading driver 302 is transmission-connected to the follow-up loading frame 301; the follow-up loading frame 301 is connected to the force transmission mechanism 202.

[0038] The pneumatic load simulation test device suitable for aircraft landing gear doors of the present invention, when performing a loading simulation test, as the door of the test piece 4 is opened, the loading driver 302 drives the follower loading frame 301 to rotate, and the follower loading frame 301 uses the force transmission mechanism 202 to transmit the force to the loading point element 201, and transmits the load through the force transmission mechanism 202, so that the load is distributed to multiple loading points on the surface of the door of the test piece 4 according to a certain proportion, so that the force transmitted by the force transmission mechanism 202 to the loading point element 201 is always perpendicular to the door of the test piece 4, and the loading along the normal direction of the door of the test piece 4 is realized, simulating the actual load on the door, thereby providing a strong basis for evaluating the deformation of the door, and at the same time, it is also beneficial to evaluate the influence of the pneumatic load on the door drive actuator and the locking performance. The force transmission mechanism 202 is flexibly connected to the loading point element 201 to reduce the fluctuation of the load during the movement; the rotation axis of the follow-up loading frame 301 is colinear with the rotation axis of the hatch of the test piece 4, so that the applied load is always kept perpendicular to the hatch surface of the test piece 4; the test bench 1 uses the clamping mechanism 102 to clamp the test piece 4, thereby ensuring the structural stability of the test piece 4 during the test, and the gantry 101 provides stable support for the clamping mechanism 102.

[0039] It should be explained here that the force transmission mechanism 202 of the present invention and the loading point element 201 are connected in a flexible manner so that the force transmitted by the force transmission mechanism 202 to the loading point element 201 is always perpendicular to the hatch of the test piece 4. Since the hatch of the test piece 4 is not a plane, the direction of the force transmitted by the force transmission mechanism 202 to the loading point element 201 is perpendicular to the section at the connection between the loading point element 201 and the hatch, so as to achieve the load applied along the normal direction of the hatch. Among them, the structure of the hatch and the aerodynamic load on the hatch normal in actual application are common knowledge to those skilled in the art. In addition, the structure of the test piece 4 includes a fixed structure and a hatch, and the hatch can be rotatably connected to the fixed structure, which are common knowledge to those skilled in the art and will not be repeated here.

[0040] The loading point element 201 is made of a flexible material, and can be attached to and pasted on the hatch of the test piece 4, so that the hatch of the test piece 4 is evenly stressed, which is conducive to further improving the accuracy of the simulation test. In this specific embodiment, the loading point element 201 can be made of a canvas strip and connected to the hatch of the test piece 4 by pasting, which is convenient to connect and avoids damaging the hatch.

[0041] It should also be noted that the number of loading point elements 201 is multiple groups to meet the requirements of the loading point of the hatch. During the simulation test, they can be allocated to each loading point according to the proportion in the simulation data to simulate the load actually received by the hatch. The number and distribution of the loading point elements 201 are reasonably set to meet different simulation test requirements and improve the flexibility and adaptability of the device. The loading point elements 201 are all flexibly connected to the force transmission mechanism 202 using a steel wire rope 203. During the simulation test, the follow-up loading frame 301 rotates with the hatch of the test piece 4, and the follow-up loading frame 301 drives the force transmission mechanism 202 to rotate. The force transmission mechanism 202 is connected to the loading point element 201 using a steel wire rope 203, which effectively avoids the hatch of the test piece 4 being subjected to components in other directions during the rotation process, ensures the smooth transmission of the load, and improves the accuracy of the loading test. The present invention uses a steel wire rope 203 to ensure the structural strength of the device at the same time. In practical applications, other types of ropes can also be used to achieve a flexible connection between the force transmission mechanism 202 and the loading point element 201.

[0042] Specifically, the connection positions of the loading point element 201 and the force transmission mechanism 202 and the steel wire rope 203 can be adjusted to adjust the loading direction and the loading load. In practical applications, movable joints can be connected at both ends of the steel wire rope 203 to adjust the length of the steel wire rope 203, to achieve fine adjustment of the loading direction and the loading load, to improve the flexibility and adaptability of the uniform loading unit 2, and to meet the requirements of the simulation test.

[0043] In this specific embodiment, the force transmission mechanism 202 is a lever force transmission mechanism, which ensures stable and effective transmission of the load, has a simple and compact structure, high transmission efficiency and convenient installation, and is conducive to saving space. In this specific embodiment, six groups of loading point elements 201 are set, and two adjacent loading point elements 201 are connected to the force transmission rods by wire ropes 203, and adjacent force transmission rods are also connected by wire ropes to form a lever force transmission mechanism. The force transmitted by the follower loading frame 301 to the force transmission mechanism 202 is distributed to multiple loading points on the surface of the door of the test piece 4 through multi-stage force transmission rods, simulating the actual load on the door, and realizing the flexible connection between the force transmission rods for load distribution through wire ropes to reduce the load fluctuation during the movement. In the actual simulation test, the number and distribution of the loading point elements 201 can be adjusted according to the test requirements.

[0044] More specifically, the follow-up loading frame 301 includes a loading rocker arm 303 and a loading beam 304. The two loading rockers 303 are rotatably connected to the gantry 101. The output end of the loading driver 302 is connected to one of the loading rockers 303. The ends of the two loading rockers 303 away from the gantry 101 are connected to the loading beam 304. The loading beam 304 is parallel to the rotation axis of the loading rocker arm 303. The loading beam 304 is connected to the force transmission mechanism 202. The loading driver 302 includes a servo motor and a reducer. The servo motor and the reducer drive one of the loading rockers 303 to rotate, and the loading rocker arm 303 drives the loading beam 304 to rotate, so that the follow-up loading frame 301 and the hatch of the test piece 4 can rotate coaxially. The follow-up loading frame 301 adopts a U-shaped structure, which improves the motion stability of the follow-up loading frame 301 and is conducive to ensuring the loading stability of the simulation test.

[0045] It should also be noted that both the loading rocker arm 303 and the loading crossbeam 304 have weight-reducing holes 305, which are helpful to reduce the mass and rotational inertia of the follower loading unit 3 and reduce the load of the loading driver 302. In addition, a reinforcement angle code 311 is also provided at the connection between the loading rocker arm 303 and the loading crossbeam 304 to improve the structural strength of the follower loading unit 3 and ensure the working reliability of the follower loading unit 3.

[0046] Furthermore, a tension sensor 307 is provided on the loading beam 304, and the tension sensor 307 is installed on the loading beam 304 using a sensor base 306. The tension sensor 307 is connected to the force transmission mechanism 202 using a traction ring, which is convenient for operators to monitor the load applied by the follow-up loading unit 3 to the door of the test piece 4, thereby improving the convenience of operation of the simulation test device. In actual applications, the tension sensor 307 can also be connected to the force transmission mechanism 202 using a steel wire rope for easy disassembly and assembly.

[0047] In other specific embodiments that can be realized by the present invention, the loading rocker arm 303 is rotatably connected to the gantry 101 using the loading shaft 308, and a bearing seat 309 is arranged between the loading shaft 308 and the gantry 101 to ensure the smooth rotation of the follow-up loading frame 301 and improve the structural reliability of the follow-up loading unit 3.

[0048] In addition, the follow-up loading unit 3 also includes a counterweight block 310 , which is connected to the loading rocker arm 303 . The counterweight block 310 is used to balance the rotational inertia of the follow-up loading frame 301 and reduce the driving torque required by the loading driver 302 .

[0049] In this specific implementation, the gantry 101 includes gantry columns 103 and a suspension beam 104 , and two gantry columns 103 are respectively connected to two ends of the suspension beam 104 to ensure the structural stability of the gantry 101 .

[0050] At the same time, the test bench 1 also includes a platform cross beam 105, a platform longitudinal beam 106 and a clamping column 107. The two platform cross beams 105 and the two platform longitudinal beams 106 form a rectangular frame structure, and the gantry column 103 is connected to the platform longitudinal beam 106 to further improve the structural stability of the test bench 1. In practical applications, the rectangular frame structure formed by the platform cross beam 105 and the platform longitudinal beam 106 can be fixed on the ground or other installation foundations to further improve the structural stability of the simulation test device and provide strong guarantees for subsequent simulation tests. The clamping column 107 is connected to the platform cross beam 105, and the clamping column 107 is arranged parallel to the gantry column 103.

[0051] In order to achieve stable clamping of the test piece 4 and meet the clamping requirements of test pieces 4 of various specifications, the clamping mechanism 102 of the present invention includes a hoisting adjustment beam 108, a first clamp 109 and a second clamp 110. The hoisting adjustment beam 108 is connected to the suspension beam 104, and the first clamp 109 is connected to the hoisting adjustment beam 108. The first clamp 109 can fix the top of the fixed structure of the test piece 4, which is convenient for subsequent simulation tests. The second clamp 110 is connected to the platform longitudinal beam 106, and the connection position of the second clamp 110 and the platform longitudinal beam 106 can be adjusted. The second clamp 110 can fix the back of the fixed structure of the test piece 4. The second clamp 110 can adopt a two-layer clamp structure. The connection holes between the two layers of clamps can adjust the gap in the horizontal and vertical directions to meet the back clamping requirements of test pieces 4 of different specifications, thereby improving the adaptability of the clamping mechanism 102.

[0052] When the pneumatic load simulation test device suitable for an aircraft landing gear door of the present invention is used for a simulation test, as the door is opened, the loading driver 302 drives the follower loading frame 301 to rotate, and the driving torque is adjusted according to the data feedback on the tension sensor 307 to keep the tension on the traction ring the same as the preset value, so as to simulate the total pneumatic load torque received by the door. The pneumatic load is distributed to each loading point according to the proportion in the simulation data through the uniformly distributed loading unit 2, so as to simulate the actual load received by the door, thereby evaluating the deformation of the door, as well as the influence of the pneumatic load on the door drive actuator and the locking performance.

[0053] Embodiment 2

[0054] The present embodiment provides an aerodynamic load simulation test device suitable for an aircraft landing gear door, wherein the force transmission mechanism 202 is rotationally connected to the loading point element 201 by a connecting rod, and the rotational connection surfaces between the connecting rod and the force transmission mechanism 202 and the loading point element 201 are all spherical surfaces, so that when the follow-up loading frame 301 and the door of the test piece 4 rotate synchronously, the force transmission mechanism 202 always transmits the force to the loading point element 201 along the normal direction of the door.

[0055] The other structures of the aerodynamic load simulation test device for aircraft landing gear doors of this embodiment are the same as those of the first embodiment and will not be described in detail here.

[0056] Embodiment 3

[0057] This embodiment provides an aerodynamic load simulation test device suitable for aircraft landing gear doors. In this specific embodiment, the force transmission mechanism 202 adopts a pulley group force transmission mechanism, which is flexible and efficient.

[0058] The other structures of the aerodynamic load simulation test device for aircraft landing gear doors of this embodiment are the same as those of the first embodiment and will not be described in detail here.

[0059] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. At the same time, for those skilled in the art, according to the ideas of the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. An aerodynamic load simulation test device suitable for aircraft landing gear doors, characterized in that: include: A test bench, the test bench comprising a gantry and a clamping mechanism, the clamping mechanism is connected to the gantry, and the clamping mechanism can clamp a fixed structure of a test piece; A uniform loading unit, the uniform loading unit comprising a loading point element and a force transmission mechanism, the loading point element being fixable on the hatch of the test piece, the force transmission mechanism being flexibly connected to the loading point element so that the force transmitted by the force transmission mechanism to the loading point element is always perpendicular to the hatch of the test piece; A follower loading unit, the follower loading unit includes a follower loading frame and a loading driver, the follower loading frame is rotatably connected to the test bench, and the rotation axis of the follower loading frame is colinear with the rotation axis of the hatch of the test piece, the loading driver is arranged on the gantry, the loading driver is transmission-connected to the follower loading frame; the follower loading frame is connected to the force transmission mechanism.

2. The aerodynamic load simulation test device for aircraft landing gear doors according to claim 1, characterized in that: The loading point element is made of a flexible material, and the loading point element can be attached to and pasted on the hatch of the test piece.

3. The aerodynamic load simulation test device for aircraft landing gear doors according to claim 1, characterized in that: The number of the loading point elements is multiple groups, and the loading point elements are all flexibly connected to the force transmission mechanism by using steel wire ropes.

4. The aerodynamic load simulation test device for aircraft landing gear doors according to claim 3, characterized in that: The loading point element and the connection position between the force transmission mechanism and the steel wire rope can be adjusted to achieve the regulation of the loading direction and the loading load.

5. The aerodynamic load simulation test device for aircraft landing gear doors according to any one of claims 1 to 4, characterized in that: The force transmission mechanism is a lever force transmission mechanism.

6. The aerodynamic load simulation test device for aircraft landing gear doors according to any one of claims 1 to 4, characterized in that: The follow-up loading frame includes a loading rocker arm and a loading beam. The two loading rocker arms are rotatably connected to the gantry. The output end of the loading driver is transmission-connected to one of the loading rocker arms. One end of the two loading rocker arms away from the gantry is connected to the loading beam. The loading beam is parallel to the rotation axis of the loading rocker arm, and the loading beam is connected to the force transmission mechanism.

7. The aerodynamic load simulation test device for aircraft landing gear doors according to claim 6, characterized in that: The loading rocker arm and the loading crossbeam are both provided with weight-reducing holes; a reinforcement angle bracket is also provided at the connection between the loading rocker arm and the loading crossbeam; A tension sensor is arranged on the loading crossbeam, and the tension sensor is connected to the force transmission mechanism by a traction ring.

8. The aerodynamic load simulation test device for aircraft landing gear doors according to claim 6, characterized in that: The loading rocker arm is rotatably connected to the gantry by a loading shaft, and a bearing seat is arranged between the loading shaft and the gantry; The follow-up loading unit also includes a counterweight block, and the counterweight block is arranged on the loading rocker arm.

9. The aerodynamic load simulation test device for aircraft landing gear doors according to claim 1, characterized in that: The gantry frame includes a gantry column and a suspension beam, and the two gantry columns are respectively connected to the two ends of the suspension beam; The test bench also includes a platform crossbeam, a platform longitudinal beam and a clamping column. The two platform crossbeams and the two platform longitudinal beams form a rectangular frame structure. The gantry column is connected to the platform longitudinal beam, the clamping column is connected to the platform crossbeam, and the clamping column is arranged parallel to the gantry column.

10. The aerodynamic load simulation test device for aircraft landing gear doors according to claim 9, characterized in that: The clamping mechanism includes a hoisting adjustment beam, a first clamp and a second clamp, the hoisting adjustment beam is connected to the suspension beam, the first clamp is connected to the hoisting adjustment beam, and the first clamp can fix the top of the fixed structure of the test piece, the second clamp is connected to the platform longitudinal beam, and the connection position of the second clamp and the platform longitudinal beam can be adjusted, and the second clamp can fix the back of the fixed structure of the test piece.

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