Composite loading device for torsion bar of airplane cabin door

Abstract

The invention relates to a composite loading device for a torsion bar of an aircraft cabin door. The composite loading device comprises a primary loading system, the second-stage loading system is matched with the first-stage loading system and is used for realizing a periodic rotating fatigue test of the torsion bar in a pre-torque loading state; the moving structure is matched with the secondary loading system and is used for realizing conversion between linear motion and rotary motion; the torsion bar supporting tool is used for supporting all test equipment and test pieces; the control system comprises an electromagnetic valve device, an electromagnetic switch device and a data acquisition module and is used for controlling a loading process and acquiring loading data; through the graded loading design of the first-stage air cylinder and the second-stage air cylinder, independent control of pre-torque loading and periodic angle loading is achieved, the moment superposition phenomenon in the loading process is avoided, and the stability of loading action and the consistency of test data are improved.

Description

Technical Field

[0001] The present invention relates to the field of mechanical technology, and particularly to a composite loading device for the torsion bar of an aircraft cabin door. Background Art

[0002] As a key component in the opening and closing system of an aircraft cabin door, the torsion bar of the aircraft cabin door mainly provides stable torque support during the opening and closing process of the cabin door, ensuring the safety and reliability of the cabin door operation. During the use of aircraft, the torsion bar of the cabin door needs to withstand multiple cyclic loadings under complex mechanical environments, and its fatigue performance is crucial for the long-term stable operation and service life of the cabin door system. Therefore, conducting fatigue performance tests on the torsion bar, especially under high pre-torque and periodic loading conditions, is one of the core links in the research, development, manufacturing, and certification processes of aviation devices. Currently, the loading devices used for torsion bar fatigue tests in the prior art have the following significant problems in terms of structural design and function implementation:

[0003] Coupling between pre-torque loading and periodic angular loading: Traditional loading devices usually perform loading through a single cylinder or motor. The application of pre-torque and the action of periodic angular loading cannot be effectively separated, resulting in interference between the two loading methods. This design is prone to torque superposition during the loading process, making it difficult to accurately maintain the pre-torque, and at the same time reducing the stability and consistency of periodic angular loading, affecting the reliability of fatigue test results.

[0004] Insufficient ability to adjust loading angle and frequency: Existing devices usually rely on mechanical limit structures to control the loading angle, but the mechanical limit design has poor adjustment flexibility and is difficult to meet the dynamic requirements of the test for specific rotation angles (such as 22 degrees) and loading frequencies (such as in the range of 0.1 Hz to 3 Hz), restricting the adaptability of the device to different test conditions.

[0005] It can be seen that the prior art urgently needs a torsion bar fatigue test device that can achieve separate control of pre-torque loading and periodic angular loading, and has high precision and flexible adjustment capabilities to meet the actual needs of high-reliability tests in the aviation field.

[0006] In view of the above problems, it is necessary to improve them. Summary of the Invention

[0007] The technical problem to be solved by the present invention is to provide a cyclic loading device for the torsion bar of an aircraft cabin door with separate control capabilities, high loading precision, and flexible adjustment performance, aiming at the problems of coupling between pre-torque loading and periodic angular loading, insufficient loading precision, lack of adjustment capabilities, and instability during the loading process existing in the prior art loading devices for the torsion bar of an aircraft cabin door, so as to meet the high reliability and high adaptability requirements of fatigue performance tests for aviation devices.

[0008] To solve the above problems, the present invention adopts the following technical solutions: An aircraft cabin door torsion bar composite loading device, comprising a primary loading system; a secondary loading system, which cooperates with the primary loading system to implement a cyclic rotational fatigue test of the torsion bar under a pre-torque loading state; a moving structure, which cooperates with the secondary loading system to implement the conversion between linear motion and rotational motion; a torsion bar support tooling for supporting each test equipment and test piece; a control system, including a solenoid valve device, an electromagnetic switch device and a data acquisition module, for controlling the loading process and acquiring loading data.

[0009] As a preferred solution of the present invention, the primary loading system includes a primary loading cylinder, a floating joint, a sliding guide rail, a primary cylinder plate and a support block. The primary cylinder plate is used to fix the primary loading cylinder, the sliding guide rail and the support block; the primary loading cylinder is connected to the secondary loading system through a floating joint, and is used to apply a pre-torque to the torsion bar under the guidance of the sliding guide rail.

[0010] Among them, the primary loading cylinder is fixedly installed on the primary cylinder plate and is used to apply a pre-torque; the floating joint is installed at the piston rod end of the primary loading cylinder and is connected to the torsion bar test piece, and is used to absorb the motion deviation during the loading process and avoid stress concentration.

[0011] As a preferred solution of the present invention, the secondary loading system includes a secondary loading cylinder, a secondary cylinder fixing plate and a secondary cylinder moving plate; the secondary loading cylinder is fixedly installed on the secondary cylinder plate, and the secondary cylinder plate is connected to the primary cylinder plate through a sliding guide rail; the piston rod of the secondary loading cylinder is connected to the moving structure through the secondary cylinder moving plate, and is used to implement the conversion between linear motion and rotational motion.

[0012] The secondary loading cylinder is fixedly installed on the secondary cylinder plate and is used to perform reciprocating linear motion along the sliding guide rail; the sliding guide rail is installed on the secondary cylinder plate and is used to guide the linear motion of the secondary cylinder to ensure the motion accuracy.

[0013] As a preferred solution of the present invention, the moving structure includes a connecting plate, a first bearing and a cantilever pin. The secondary cylinder moving plate is connected to the cantilever pin through the connecting plate, and the smooth transmission between linear motion and rotational motion is realized through the first bearing and the cantilever pin.

[0014] The first bearing supports the entire moving structure to ensure the rotational stability during the loading process; the cantilever pin is used to transmit the linear motion of the secondary loading cylinder to the guide shaft.

[0015] As a preferred solution of the present invention, it further includes a guiding structure, which is connected to the moving structure and is used to realize the efficient conversion between linear motion and rotational motion.

[0016] As a preferred embodiment of the present invention, the guiding structure includes a guiding shaft, an angle encoder, a grease bushing and a guiding block. The guiding shaft is connected to the secondary loading system through a cantilever pin and is used to convert linear motion into rotational motion. The angle encoder is used to detect the rotational angle of the guiding shaft. The guiding shaft reduces friction through the grease bushing and improves the stability of rotational motion.

[0017] The guiding shaft is used to convert linear motion into the periodic rotational motion of the test piece, and the rotational angle range is 22°. It can be adjusted to 5° to 30° according to test requirements to meet the fatigue test requirements of different working conditions.

[0018] As a preferred embodiment of the present invention, the torsion bar support tooling includes a torque sensor, a support seat, a flange and a torsion bar test piece. The torque sensor is used to detect the loading state of the primary loading cylinder and feedback the signal to the electromagnetic switch device for the solenoid valve device to switch the loading mode to the pressure-holding state. The support seat is used to fix the torque sensor, and the flange is used to connect the torque sensor and the torsion bar test piece. The torsion bar test piece is the torsion bar of the aircraft door and is used to bear the loading and simulate the fatigue performance test under actual working conditions. The torque sensor is used to monitor the loading torque value of the primary cylinder in real time and transmit the signal to the control system.

[0019] As a preferred embodiment of the present invention, the solenoid valve device includes a first solenoid valve and a second solenoid valve. The electromagnetic switch device includes a first electromagnetic switch, a second electromagnetic switch, a third electromagnetic switch and a fourth electromagnetic switch. Among them, the first electromagnetic switch and the second electromagnetic switch cooperate with the first solenoid valve to control the loading state of the primary loading cylinder. The second solenoid valve cooperates with the third electromagnetic switch and the fourth electromagnetic switch to control the loading state of the secondary loading cylinder.

[0020] The first solenoid valve is a two-position five-way double-electrically controlled solenoid valve: it is connected to the primary loading cylinder and is used to switch the loading state of the primary loading cylinder. When the torque sensor detects a preset torque value, the first solenoid valve switches to the pressure-holding state to maintain the pre-torque loading.

[0021] The second solenoid valve is a two-position five-way double-electrically controlled solenoid valve: it is used to control the reciprocating motion of the secondary loading cylinder. When the rotational angle of the test piece reaches the set value, the second solenoid valve switches direction to make the secondary loading cylinder move in the reverse direction.

[0022] As a preferred embodiment of the present invention, the first-stage cylinder plate is fixedly installed on the floor iron. The surface of the first-stage cylinder plate is provided with an installation reference surface for the sliding guide rail, and the sliding guide rail is used to guide the linear sliding movement of the second-stage cylinder plate; the first-stage cylinder plate is provided with a reference surface for fixing the first-stage cylinder and maintaining the loading accuracy; the first-stage loading cylinder is used to provide pre-torque loading to the torsion bar, and the torque sensor real-time detects the loading torque value, and judges whether the pre-torque reaches the set value through the acquisition control computer.

[0023] As a preferred embodiment of the present invention, the data acquisition module records the key data generated during the loading process, including the pre-torque value, rotation angle, and loading frequency, and supports the export and subsequent analysis of the test data.

[0024] In this embodiment, the loading frequency range is from 0.1 Hz to 3 Hz, and dynamic adjustment can be achieved to meet the requirements of different frequency loadings in the fatigue performance test.

[0025] The beneficial effects of the present invention are as follows:

[0026] 1. The structure of the present invention is simple. Through the design of the split-type loading system, the loading stability and accuracy are improved: through the hierarchical loading design of the first-stage cylinder and the second-stage cylinder, the independent control of the pre-torque loading and the periodic angle loading is realized, avoiding the moment superposition phenomenon during the loading process, and improving the stability of the loading action and the consistency of the test data.

[0027] 2. The present invention is ingeniously designed, with efficient motion conversion and accurate loading: through the precise cooperation design of the sliding guide rail and the guide shaft, the linear motion of the second-stage cylinder is efficiently converted into the rotational motion of the test piece, supporting a fixed angle loading of 22°, and the angle range can be flexibly adjusted from 5° to 30°, adapting to the requirements of different test conditions.

[0028] 3. The present invention has a wide range of applications and high engineering value: this device is applicable to the fatigue performance test of the torsion bar of the aircraft cabin door, and can also be popularized and applied to the performance tests of other similar mechanical structure parts, providing a reliable technical guarantee for the research and development, manufacturing and quality control of aviation devices. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a schematic structural diagram of the periodic loading device for the torsion bar of the aircraft cabin door provided by the embodiment of the present invention.

[0030] Figure 2 It is a top view of the periodic loading device for the torsion bar of the aircraft cabin door provided by the embodiment of the present invention.

[0031] Figure 3 It is a schematic diagram of the first-stage loading system of the periodic loading device for the torsion bar of the aircraft cabin door provided by the embodiment of the present invention.

[0032] Figure 4 Schematic diagram of the secondary loading system of the aircraft door torsion bar periodic loading device provided by the embodiment of the present invention.

[0033] Figure 5 Schematic diagram of the moving structure of the aircraft door torsion bar periodic loading device provided by the embodiment of the present invention.

[0034] Figure 6 Schematic diagram of the guiding structure of the aircraft door torsion bar periodic loading device provided by the embodiment of the present invention patent.

[0035] Figure 7 Schematic diagram of the torsion bar support tooling structure of the aircraft door torsion bar periodic loading device provided by the embodiment of the present invention patent.

[0036] Description of reference numerals: primary loading system 1, secondary loading system 2, moving structure 3, guiding structure 4, torsion bar support tooling 5, floor iron 6, acquisition control computer 7, first solenoid valve 801, second solenoid valve 802, primary cylinder plate 101, support block 102, sliding guide rail 103, first electromagnetic switch 104, second electromagnetic switch 105, primary loading cylinder 106, floating joint 107, threaded joint 108, third electromagnetic switch 201, fourth electromagnetic switch 202, secondary cylinder fixing plate 203, secondary loading cylinder 204, secondary cylinder moving plate 205, connecting plate 301, first bearing 302, cantilever pin 303, angle encoder 304, clamping bar block 305, guiding shaft 306, second bearing 401, grease bushing 402, guiding block 403, torque sensor support seat 501, flange 502, torque sensor 503, torsion bar test piece 504. Detailed implementation manners

[0037] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some but not all of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0038] In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0039] Embodiment:

[0040] Through the design of a split loading system, the present invention provides precise pre-torque loading by a primary loading system, and the secondary loading system performs periodic angular loading under the pre-torque state, significantly improving the accuracy and controllability of the loading process. The primary loading system is coupled with the secondary loading system through a floating joint, solving the stress concentration problem caused by non-concentric loading paths or component installation errors, thereby improving the stability and reliability of the loading. At the same time, the secondary loading system efficiently converts linear motion into rotational motion through a guide shaft, and cooperates with an angle encoder to achieve precise control of the loading angle, with the angle range adjustable between 5° and 30°, meeting the requirements of different types of fatigue tests. This device is particularly suitable for the fatigue performance test of the torsion bar of an aircraft cabin door, which can greatly improve the test efficiency and data repeatability.

[0041] Based on this, refer to Figure 1 - Figure 2 , Figure 1 which is a schematic structural diagram of the periodic loading device for the torsion bar of an aircraft cabin door provided by an embodiment of the present invention. Figure 2 which is a top view of the periodic loading device for the torsion bar of an aircraft cabin door provided by an embodiment of the present invention. Specifically,

[0042] A composite loading device for the torsion bar of an aircraft cabin door includes a primary loading system 1, a secondary loading system 2, which cooperates with the primary loading system 1 to realize the periodic rotational fatigue test of the torsion bar under the pre-torque loading state; a moving structure 3, which cooperates with the secondary loading system 2 to realize the conversion between linear motion and rotational motion; a control system, including a solenoid valve device, an electromagnetic switch device and a data acquisition module, which is used to control the loading process and collect loading data; a torsion bar support tooling 5, which is used to support each test equipment and test piece; the solenoid valve device includes a first solenoid valve 801 and a second solenoid valve 802; the electromagnetic switch device includes a first electromagnetic switch 201 and a second electromagnetic switch 202; wherein, the first solenoid valve 801 cooperates with the first electromagnetic switch 201 to control the loading state of the primary loading cylinder 106; the second solenoid valve 802 cooperates with the second electromagnetic switch 202 to control the loading state of the secondary loading cylinder 204.

[0043] The structure of the present invention is simple. Through the split control design, the loading stability and accuracy are improved: through the hierarchical loading design of the primary cylinder and the secondary cylinder, the present invention realizes the independent control of pre-torque loading and periodic angular loading, avoiding the moment superposition phenomenon during the loading process, and improving the stability of the loading action and the consistency of test data.

[0044] Refer to Figure 3 , Figure 3Schematic diagram of the first - stage loading system of the aircraft door torsion bar periodic loading device provided according to an embodiment of the present invention; specifically, the first - stage loading system 1 includes a first - stage loading cylinder 106, a floating joint 107, a sliding guide rail 103, a first - stage cylinder plate 101, and a support block 102. The first - stage cylinder plate 101 is used to fix the first - stage loading cylinder 106, the sliding guide rail 103, and the support block 102.

[0045] The first - stage loading cylinder 106 is connected to the floating joint 107 through a threaded joint 108, and the floating joint 107 is further connected to the second - stage cylinder plate 203, which is used to relieve the stress concentration caused by installation deviation or non - concentric movement, and improve the loading smoothness.

[0046] The first - stage cylinder plate 101 is fixedly installed on the floor iron 6. The surface of the first - stage cylinder plate 101 is provided with an installation reference surface for the sliding guide rail 103. The sliding guide rail 103 is used to guide the linear sliding movement of the second - stage cylinder plate 203. The first - stage loading cylinder 106 is used to provide pre - torque loading to the torsion bar. The torque sensor 503 real - time detects the loading torque value, and judges whether the pre - torque reaches the set value through the acquisition control computer 7.

[0047] When the first - stage loading system 1 is started, the first - stage loading cylinder 106 drives the second - stage cylinder plate 203 to move linearly along the sliding guide rail 103. When the loading torque reaches the set value, the torque sensor 503 sends a signal to the first electromagnetic switch 104 through the acquisition control computer 7, triggering the first solenoid valve 801 to switch to the pressure - maintaining state, and the first - stage loading cylinder 106 stops moving and maintains the loading state.

[0048] Refer to Figure 4 , Figure 4 Schematic diagram of the second - stage loading system of the aircraft door torsion bar periodic loading device provided according to an embodiment of the present invention. Specifically, the second - stage loading system 2 includes a second - stage loading cylinder 204, a second - stage cylinder fixing plate 203, and a second - stage cylinder moving plate 205. The second - stage loading cylinder 204 is fixedly installed on the second - stage cylinder plate 203. The second - stage cylinder plate 203 is connected to the first - stage cylinder plate 101 through the sliding guide rail 103. The piston rod of the second - stage loading cylinder 204 is connected to the moving structure 3 through the second - stage cylinder moving plate 205, which is used to realize the conversion between linear motion and rotational motion.

[0049] When the secondary loading system 2 is started, the secondary loading cylinder 204 pushes the secondary cylinder moving plate 205 to move along the sliding guide rail 103. The secondary cylinder moving plate 205 is connected to the cantilever pin 303 through the connecting plate 301, and the cantilever pin 303 is further connected to the guide shaft 306. The guide shaft 306 converts the linear motion of the secondary loading cylinder 204 into the rotational motion of the torsion bar, realizing the periodic angular loading of the torsion bar. When the rotation angle of the torsion bar test piece 504 reaches the set value, such as 22°, the angle encoder 304 sends a signal to the acquisition control computer 7 to control the third electromagnetic switch 201 to trigger the second solenoid valve 802 to switch directions, and the secondary loading cylinder 204 moves in the reverse direction to the initial position.

[0050] See Figure 5 , Figure 5 FIG. is a schematic diagram of the moving structure of the aircraft door torsion bar periodic loading device according to an embodiment of the present invention. Specifically, the moving structure 3 includes a connecting plate 301, a first bearing 302 and a cantilever pin 303. The secondary cylinder moving plate 205 is connected to the cantilever pin 303 through the connecting plate 301, and the smooth transmission of linear motion and rotational motion is realized through the first bearing 302 and the cantilever pin 303.

[0051] The first bearing 302 supports the entire moving structure to ensure the rotational stability during the loading process; the cantilever pin 303 is used to transmit the linear motion of the secondary loading cylinder 204 to the guide shaft 306.

[0052] See Figure 6 , Figure 6 FIG. is a schematic diagram of the guiding structure of the aircraft door torsion bar periodic loading device according to an embodiment of the present invention. Specifically, the guiding structure 4 is connected to the moving structure 3 for realizing the efficient conversion of linear motion and rotational motion; the guiding structure 4 includes a guide shaft 306, an angle encoder 304, a grease bushing 402, a guide block 403 and a second bearing 401. The second bearing 401 supports the grease bushing 402 and the guide block 403. The guide shaft 306 is connected to the secondary loading system 2 through the cantilever pin 303 for converting linear motion into rotational motion, and the angle encoder 304 is used to detect the rotation angle of the guide shaft 306. The guide shaft 306 reduces the friction force through the grease bushing 402 to improve the stability of the rotational motion. The present invention is ingeniously designed, with efficient motion conversion and accurate loading: through the precise cooperation design of the sliding guide rail and the guide shaft, the linear motion of the secondary cylinder is efficiently converted into the rotational motion of the test piece, supporting a fixed angle loading of 22°, and the angle range is flexibly adjustable from 5° to 30° to meet the requirements of different test conditions.

[0053] See Figure 7 , Figure 7Schematic structural diagram of the torsion bar support tooling for the aircraft cabin door torsion bar periodic loading device provided by the embodiment of the present invention; specifically, the torsion bar support tooling 5 includes a torque sensor 503, a support base 501, a flange 502, and a torsion bar test piece 504; the torque sensor 503 is used to detect the loading state of the primary loading cylinder 106 and feedback the signal to the electromagnetic switch device for switching the loading mode of the solenoid valve device to the pressure holding state, the support base 501 is used to fix the torque sensor 503, and the flange 502 is used to connect the torque sensor 503 and the torsion bar test piece 504.

[0054] The data acquisition module records the key data generated during the loading process, including the pre-torque value, rotation angle, and loading frequency, and supports the export and subsequent analysis of test data; the loading frequency range is from 0.1 Hz to 3 Hz, and dynamic adjustment can be achieved to meet the requirements of different frequency loadings in the fatigue performance test.

[0055] The operating principle of this embodiment is:

[0056] When the power is turned on, the primary loading system 1 starts, and a pre-torque is applied to the torsion bar through the primary loading cylinder 106. When the set pre-torque is reached, the primary loading cylinder 106 remains stationary and switches to the pressure holding state. At this time, the secondary loading system 2 starts to work. The secondary loading cylinder 204 pushes the guide shaft 306 through the moving plate 205, converting the linear motion into the rotational motion of the torsion bar. When the set rotation angle is reached, the first electromagnetic switch 201 controls the secondary loading cylinder 204 to move in the reverse direction, and so on, to achieve the periodic loading of the torsion bar under the condition of the existence of the pre-torque.

[0057] By providing high-precision pre-torque application through the primary loading system 1 and realizing independent control of periodic angle loading through the secondary loading system 2, this device effectively avoids the experimental errors caused by the superposition of loading torques in the traditional device, and significantly improves the stability and repeatability of the test results. The acquisition control computer 7 monitors and adjusts the loading process in real time, and can adjust the loading frequency (0.1 Hz to 3 Hz) and rotation angle (5° to 30°) according to different test requirements, and is widely applicable to the fatigue performance test of torsion bars.

[0058] Through the above embodiments, the present invention realizes the separate control of pre-torque loading and periodic angle loading, significantly improves the stability of the loading action and the accuracy of the loading process, and is applicable to the fatigue performance test of aircraft cabin door torsion bars with different test requirements.

[0059] The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0060] Although the terms such as the first-level loading system 1, the second-level loading system 2, the moving structure 3, the guiding structure 4, the torsion bar support tooling 5, the floor iron 6, the acquisition control computer 7, the first solenoid valve 801, the second solenoid valve 802, the first-level cylinder plate 101, the support block 102, the sliding guide rail 103, the first electromagnetic switch 104, the second electromagnetic switch 105, the first-level loading cylinder 106, the floating joint 107, the threaded joint 108, the third electromagnetic switch 201, the fourth electromagnetic switch 202, the second-level cylinder fixing plate 203, the second-level loading cylinder 204, the second-level cylinder moving plate 205, the connecting plate 301, the first bearing 302, the cantilever pin 303, the angle encoder 304, the clamping bar block 305, the guiding shaft 306, the second bearing 401, the grease bushing 402, the guiding block 403, the torque sensor support seat 501, the flange 502, the torque sensor 503, the torsion bar test piece 504 and so on are used more frequently herein, the possibility of using other terms is not excluded. These terms are only used to more conveniently describe and explain the essence of the present invention; any interpretation of them as any additional limitation is contrary to the spirit of the present invention.

Claims

1. A composite loading device for a torsion bar of an aircraft door, characterized in that: include Primary loading system (1); The secondary loading system (2) cooperates with the primary loading system (1) to implement a periodic rotation fatigue test of the torsion bar under a pre-torque loading state; The mobile structure (3) cooperates with the secondary loading system (2) to realize the conversion between linear motion and rotational motion; Torsion bar support fixture (5), used to support various test equipment and test pieces; The control system includes a solenoid valve device, an electromagnetic switch device and a data acquisition module, which are used to control the loading process and collect loading data.

2. The aircraft door torsion bar composite loading device according to claim 1, characterized in that: The primary loading system (1) comprises a primary loading cylinder (106), a floating joint (107), a sliding guide rail (103), a primary cylinder plate (101) and a support block (102); the primary cylinder plate (101) is used to fix the primary loading cylinder (106), the sliding guide rail (103) and the support block (102); the primary loading cylinder (106) is connected to the secondary loading system (2) via the floating joint (107) and is used to realize pre-torque loading on the torsion bar under the guidance of the sliding guide rail (103).

3. The aircraft door torsion bar composite loading device according to claim 2, characterized in that: The secondary loading system (2) comprises a secondary loading cylinder (204), a secondary cylinder fixed plate (203) and a secondary cylinder movable plate (205); the secondary loading cylinder (204) is fixedly mounted on the secondary cylinder plate (203), and the secondary cylinder plate (203) is connected to the primary cylinder plate (101) via a sliding guide rail (103); the piston rod of the secondary loading cylinder (204) is connected to the movable structure (3) via the secondary cylinder movable plate (205), so as to realize the conversion between linear motion and rotational motion.

4. The aircraft door torsion bar composite loading device according to claim 3, characterized in that: The moving structure (3) comprises a connecting plate (301), a first bearing (302) and a cantilever pin (303); the secondary cylinder moving plate (205) is connected to the cantilever pin (303) via the connecting plate (301); and the first bearing (302) and the cantilever pin (303) enable smooth transmission of linear motion and rotational motion.

5. The aircraft door torsion bar composite loading device according to any one of claims 1 to 4, characterized in that: It also includes a guide structure (4), which is connected to the moving structure (3) and is used to achieve efficient conversion between linear motion and rotational motion.

6. The aircraft door torsion bar composite loading device according to claim 5, characterized in that: The guide structure (4) comprises a guide shaft (306), an angle encoder (304), a grease bushing (402) and a guide block (403); the guide shaft (306) is connected to the secondary loading system (2) via a cantilever pin (303) and is used to convert linear motion into rotational motion; the angle encoder (304) is used to detect the rotation angle of the guide shaft (306); the guide shaft (306) reduces friction through the grease bushing (402) and improves the stability of the rotational motion.

7. The aircraft door torsion bar composite loading device according to claim 1, characterized in that: The torsion bar support tooling (5) comprises a torque sensor (503), a support seat (501), a flange (502) and a torsion bar test piece (504); the torque sensor (503) is used to detect the loading state of the first-stage loading cylinder (106), and feed back a signal to the electromagnetic switch device for the electromagnetic valve device to switch the loading mode to the pressure-maintaining state; the support seat (501) is used to fix the torque sensor (503); and the flange (502) is used to connect the torque sensor (503) and the torsion bar test piece (504).

8. The aircraft door torsion bar composite loading device according to claim 1 or 7, characterized in that: The electromagnetic valve device comprises a first electromagnetic valve (801) and a second electromagnetic valve (802); the electromagnetic switch device comprises a first electromagnetic switch (104), a second electromagnetic switch (105), a third electromagnetic switch (201), and a fourth electromagnetic switch (202); wherein the first electromagnetic switch (104), the second electromagnetic switch (105) and the first electromagnetic switch (201) are matched with each other to control the loading state of the first-stage loading cylinder (106); and the second electromagnetic valve (802) is matched with the third electromagnetic switch (201) and the fourth electromagnetic switch (202) to control the loading state of the second-stage loading cylinder (204).

9. The aircraft door torsion bar composite loading device according to claim 2, characterized in that: The first-stage cylinder plate (101) is fixedly mounted on the ground iron (6); a mounting reference surface of a sliding guide rail (103) is provided on the surface of the first-stage cylinder plate (101); the sliding guide rail (103) is used to guide the linear sliding motion of the second-stage cylinder plate (203); the first-stage loading cylinder (106) is used to provide pre-torque loading to the torsion bar; the torque sensor (503) detects the loading torque value in real time, and determines whether the pre-torque reaches a set value through an acquisition control computer (7).

10. The aircraft door torsion bar composite loading device according to claim 1, characterized in that: The data acquisition module records key data generated during the loading process, including pre-torque value, rotation angle, loading frequency, and supports the export and subsequent analysis of test data.

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