Aircraft simulation test system

Abstract

The present invention discloses a simulation test system for an aircraft, which relates to the field of aircraft and includes a test box, a horizontal mounting seat, a vertical mounting seat, an excitation transducer, a concentrated force simulation unit, a horizontal centering unit, a vertical centering unit, a temperature and humidity simulation unit, an acquisition module and an integrated control unit; a test piece is mounted on the excitation transducer, and the excitation transducer provides the test piece with high-frequency load excitation in the horizontal or vertical direction; the concentrated force simulation unit provides the test piece with concentrated force static loads in the horizontal and vertical directions; the horizontal centering unit and the vertical centering unit are respectively used to offset the concentrated forces acting on the excitation transducer in the horizontal and vertical directions, so that the vibration output end, the horizontal mounting seat and the vertical mounting seat of the excitation transducer are always in the working position and can be excited normally; the temperature and humidity simulation unit provides a temperature and humidity environment for the test piece; the integrated control unit coordinates and controls the above units to realize vibration-concentrated force-temperature composite control.

Description

Technical Field

[0001] The present invention relates to the field of aircraft, and in particular to a simulation test system for aircraft. Background Art

[0002] Aircraft may experience a combination of flight overload, vibration, and low temperatures during flight. To ensure that the aircraft maintains its functionality and performance in these combined environments, ground-based vibration, overload, and temperature combined environmental assessment tests are required to verify its functionality and performance. Vibrating centrifuges are typically used to simulate this combined vibration and overload environment. However, these tests are not practical for test pieces with large volumes and masses. Summary of the Invention

[0003] The purpose of the present invention is to design a simulation test system for an aircraft in order to solve the above problems.

[0004] The present invention achieves the above-mentioned purpose through the following technical solutions:

[0005] Aircraft simulation test system, including:

[0006] Test chamber;

[0007] Horizontal mounting bracket;

[0008] vertical mounting base;

[0009] Excitation transducer; the excitation transducer is used to provide horizontal or vertical high-frequency load excitation for the test piece, and the vibration output end of the excitation transducer acts on the horizontal mounting seat or the vertical mounting seat;

[0010] Concentrated force simulation unit; the concentrated force simulation unit is used to apply concentrated forces in the horizontal and vertical directions to the test piece to simulate the static load on the test piece. The concentrated force of the concentrated force simulation unit acts on the test piece;

[0011] Horizontal centering unit: The horizontal centering unit is used to control the vibration output element and the horizontal mounting seat of the excitation transducer to always be in the working position;

[0012] Vertical centering unit; the vertical centering unit is used to control the vibration output element and the vertical mounting seat of the excitation transducer to always be in the working position;

[0013] Temperature and humidity simulation unit: The temperature and humidity simulation unit is used to provide a temperature and humidity environment for the test piece;

[0014] Acquisition unit: The acquisition unit is used to collect test data of the test piece during the test process;

[0015] The integrated control unit is used to analyze the test data and control the working processes of the excitation transducer, the concentrated force simulation unit, and the temperature and humidity simulation unit. The control signal output end of the integrated control unit is connected to the control signal input end of the excitation transducer, the concentrated force simulation unit, and the temperature and humidity simulation unit, respectively. The data signal input end of the integrated control unit is connected to the data signal output end of the acquisition unit.

[0016] When conducting a horizontal high-frequency load excitation test, the test piece is fixedly mounted on a horizontal mounting seat, and both the horizontal mounting seat and the test piece are located inside the test chamber, which is in a sealed state. When conducting a vertical high-frequency load excitation test, the test piece is fixedly mounted on a vertical mounting seat, and both the vertical mounting seat and the test piece are located inside the test chamber, which is in a sealed state.

[0017] The beneficial effects of the present invention are: the test piece is installed on the excitation transducer, and the excitation transducer provides the test piece with horizontal or vertical high-frequency load excitation; the concentrated force simulation unit provides the test piece with horizontal and vertical static loads to simulate the overload situation of the aircraft flight; the horizontal centering unit is used to offset the horizontal concentrated force acting on the vibration output end of the excitation transducer and the horizontal mounting seat, and the vertical centering unit is used to offset the vertical concentrated force acting on the vibration output end of the excitation transducer and the vertical mounting seat, so that the vibration output end of the excitation transducer, the horizontal mounting seat and the vertical mounting seat are always in the working position and can be excited normally; the temperature and humidity simulation unit provides a temperature and humidity environment for the test piece; the acquisition unit is used to obtain the actual values ​​of various physical quantities of the simulated load in real time; the integrated control unit coordinates and controls the above units to achieve vibration-concentrated force-temperature composite control. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of a simulation test system for an aircraft of the present invention;

[0019] Figure 2 It is a schematic structural diagram of the simulation test system of the aircraft of the present invention;

[0020] Figure 3 Schematic diagram of the installation of an excitation transducer for vertical high-frequency load excitation in a simulation test system of an aircraft of the present invention;

[0021] Figure 4 It is a schematic diagram of the installation of an exciting transducer for horizontal high-frequency load excitation in a simulation test system of an aircraft of the present invention;

[0022] Figure 5 2. It is a schematic structural diagram of a concentrated force simulation unit in a simulation test system for an aircraft according to the present invention;

[0023] Figure 6It is a structural schematic diagram of the centering sub-component in the simulation test system of the aircraft of the present invention;

[0024] Figure 7 2. It is a schematic structural diagram of a temperature and humidity simulation unit in the aircraft simulation test system of the present invention;

[0025] The corresponding figures are as follows:

[0026] 1-test box, 2-horizontal mounting seat, 3-vertical mounting seat, 301-vertical mounting table, 302-support table, 303-pneumatic support assembly, 304-first connecting rod, 305-second connecting rod, 306-bearing, 4-excitation transducer, 401-vibration output element, 5-concentrated force simulation unit, 501-winch, 502-first steel wire rope, 503-second steel wire rope, 504-fixed pulley, 505-support frame, 506-spring, 6-horizontal centering unit, 7-vertical centering unit, 8-temperature and humidity simulation unit, 9-moving assembly, 10-box, 11-single-rod hydraulic excitation cylinder, 12-servo valve, 13-piston accumulator, 14-test piece. DETAILED DESCRIPTION

[0027] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be described clearly and completely below in conjunction with the accompanying drawings of the embodiments of the present invention. It should be understood that the described embodiments are only a portion of the embodiments of the present invention, not all of them. Generally, the components of the embodiments of the present invention described and illustrated in the drawings herein may be arranged and designed in a variety of different configurations.

[0028] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention as claimed, but rather merely represents selected embodiments of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort shall fall within the scope of protection of the present invention.

[0029] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0030] In the description of the present invention, it should be understood that the terms "upper", "lower", "inside", "outside", "left", "right", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, or are the orientations or positional relationships in which the inventive product is conventionally placed when in use, or are the orientations or positional relationships conventionally understood by those skilled in the art. These are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0031] Furthermore, the terms “first”, “second”, etc. are merely used for distinguishing descriptions and should not be understood as indicating or implying relative importance.

[0032] In the description of the present invention, it should also be noted that, unless otherwise expressly specified or limited, terms such as "disposed" and "connected" should be understood in a broad sense. For example, "connected" can mean a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can also mean internal communication between two components. Those skilled in the art will be able to understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0033] The specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0034] like Figure 1 、 Figure 2 As shown, the aircraft simulation test system includes:

[0035] Test chamber 1;

[0036] Horizontal mounting seat 2;

[0037] Vertical mounting base 3;

[0038] Excitation transducer 4; the excitation transducer 4 is used to provide horizontal or vertical high-frequency load excitation for the test piece 14, and the vibration output end of the excitation transducer 4 acts on the horizontal mounting seat 2 or the vertical mounting seat 3;

[0039] Concentrated force simulation unit 5; the concentrated force simulation unit is used to apply concentrated static loads in the horizontal and vertical directions to the test piece 14 to simulate the overload condition of the aircraft in flight, and the concentrated force of the concentrated force simulation unit acts on the test piece 14;

[0040] Horizontal centering unit 6; the horizontal centering unit 6 is used to control the vibration output member 401 of the excitation transducer 4 and the horizontal mounting base 2 to be always in the working position;

[0041] Vertical centering unit 7; vertical centering unit 7 is used to control the vibration output member 401 of the excitation transducer 4 and the vertical mounting base 3 to be always in the working position;

[0042] Temperature and humidity simulation unit 8; the temperature and humidity simulation unit 8 is used to provide a temperature and humidity environment for the test piece 14;

[0043] The acquisition unit is used to collect test data of the test piece 14 during the test process;

[0044] The integrated control unit is used to analyze the test data and control the working process of the excitation transducer 4, the concentrated force simulation unit 5, and the temperature and humidity simulation unit 8. The control signal output end of the integrated control unit is connected to the control signal input end of the excitation transducer 4, the concentrated force simulation unit 5, and the temperature and humidity simulation unit 8, respectively. The data signal input end of the integrated control unit is connected to the data signal output end of the acquisition unit;

[0045] like Figure 3 、 Figure 4 As shown, when the horizontal high-frequency load excitation test is performed, the test piece 14 is fixedly mounted on the horizontal mounting seat 2, the horizontal mounting seat 2 and the test piece 14 are both located in the test box 1, and the test box 1 is in a sealed state; when the vertical high-frequency load excitation test is performed, the test piece 14 is fixedly mounted on the vertical mounting seat 3, the vertical mounting seat 3 and the test piece 14 are both located in the test box 1, and the test box 1 is in a sealed state.

[0046] The test piece 14 is installed on the excitation transducer 4, and the excitation transducer 4 provides horizontal or vertical high-frequency load excitation for the test piece 14; the concentrated force simulation unit 5 provides horizontal or vertical concentrated force for the test piece 14; the vertical centering unit 7 is used to offset the vertical concentrated force acting on the vibration output end and the vertical mounting seat 3 in the excitation transducer 4, and the horizontal centering unit 6 is used to offset the horizontal concentrated force acting on the vibration output end and the horizontal mounting seat 2 in the excitation transducer 4, so that the vibration output end and the vertical mounting seat 3 and the horizontal mounting seat 2 in the excitation transducer 4 are still in the working position and can normally excite the test piece 14; the temperature and humidity simulation unit 8 provides a temperature and humidity environment for the test piece 14; the acquisition unit is used to obtain the actual values ​​of each physical quantity of the simulated load in real time; the integrated control unit coordinates and controls the above units to realize vibration-concentrated force-temperature composite control.

[0047] The integrated control unit includes an interaction module, a data communication module, an operation control module, and a safety protection module. The interaction module converts the input vibration simulation conditions, concentrated force simulation conditions, and temperature simulation conditions into a control loading curve; the data communication module is used to send control instructions and feedback test signals; the operation control module derives control instructions in real time based on the control target and test signals; and the safety protection module provides system safety protection. The output of the interaction module is connected to the input of the operation control module, which is in turn connected to the input of the communication module. The output of the communication module is respectively connected to the input of the excitation transducer 4, the input of the concentrated force simulation unit 5, the input of the horizontal centering unit 6 and the input of the vertical centering unit 7, the input of the temperature and humidity simulation unit 8, and the input of the safety protection module. The output of the safety protection module is respectively connected to the input of the interaction module and the input of the operation control module. The output of the excitation transducer 4, the output of the concentrated force simulation unit 5, the output of the horizontal centering unit 6, the input of the vertical centering unit 7, and the output of the temperature and humidity simulation unit 8 are respectively connected to the input of the acquisition unit. The output of the acquisition unit is connected to the input of the data communication module.

[0048] The acquisition unit includes an acceleration sensor, a static force sensor, a strain sensor, a temperature and humidity sensor, two displacement sensors, two pressure sensors and a data acquisition instrument. The data signal output ends of the acceleration sensor, static force sensor, strain sensor, temperature and humidity sensor, displacement sensor and pressure sensor are all connected to the data signal input end of the data acquisition instrument, and the data signal output end of the data acquisition instrument is connected to the data signal input end of the integrated control unit. The acceleration sensor, static force sensor and strain sensor are all installed on the test piece 14, and the temperature and humidity sensor is installed in the test box 1. The two pressure sensors are used to measure the output force of the horizontal centering unit 6 and the vertical centering unit 7 respectively. The two displacement sensors are used to measure the vibration displacement of the horizontal mounting seat 2 and the vertical mounting seat 3 respectively. The static force sensor is used to measure the concentrated force applied by the concentrated force simulation unit 5 to the test piece 14.

[0049] The excitation transducer 4 includes a controller, a power amplifier, and a moving part. The controller receives the vibration control instructions from the integrated control unit and the vibration acceleration test signal and force sensor signal from the test unit and performs calculations. After the calculations are completed, the analog signal is transmitted to the power amplifier. The power amplifier receives the signal sent by the controller and performs power amplification to drive the moving part (i.e., the vibration output part 401). The moving part converts the current excitation from the power amplifier into physical excitation (i.e., electromagnetic energy into mechanical energy), which can simulate the broadband random plus simple harmonic excitation conditions generated in the aircraft vibration environment, so that controlled complex multi-order resonance is generated inside the aircraft. It can be used to examine the dynamic stress generated by the complex effects such as superimposed excitation and the resonance of the internal structure of the aircraft, causing structural strength damage or unacceptable large deformation.

[0050] like Figure 5 As shown, the concentrated force simulation unit 5 includes a winch 501, a first steel wire rope 502, two groups of second steel wire ropes 503, two groups of fixed pulleys 504 assemblies and a support frame 505. The drum of the winch 501 is fixedly connected to the first end of the first steel wire rope 502, and the second ends of the first steel wire rope 502 are respectively connected to the first ends of the two groups of second steel wire ropes 503. The two groups of fixed pulleys 504 assemblies are respectively used to control the concentrated force directions of the two groups of second steel wire ropes 503 on the test piece 14 towards the horizontal and vertical directions. The two groups of fixed pulleys 504 are installed on the support frame 505.

[0051] The concentrated force simulation unit 5 also includes a spring 506. The second end of the first steel wire rope 502 is fixedly connected to the first end of the spring 506. The first ends of the two sets of second steel wire ropes 503 are respectively fixedly connected to the second ends of the spring 506. The maximum load-bearing value of the spring 506 should not be less than the maximum concentrated force required for the test. The maximum effective deformation of the spring 506 should be designed according to the loading accuracy requirements of the concentrated force. For example, if the fluctuation degree of the concentrated force is required to be constant and not more than 10% during the test, the maximum effective deformation of the spring 506 can be designed to be greater than 10 times the maximum excitation displacement of the excitation transducer 4. Due to the buffering effect of the spring 506, even if the active control of the concentrated force is not considered, the fluctuation of the concentrated force during the excitation process is not more than 10%. And the design of the concentrated force simulation unit 5 based on the spring 506 realizes the precise control of the concentrated force in all directions under the vibration environment.

[0052] During the test, the elongation of the spring 506 of the concentrated force simulation unit 5 changes dynamically with the vibration displacement of the exciting transducer 4, thereby eliminating the influence of the vibration displacement change on the concentrated force control accuracy and ensuring high control accuracy of the concentrated force.

[0053] The concentrated force simulation unit 5 also includes a servo controller and a driver. The control signal input end of the servo controller is connected to the control signal output end of the integrated control unit. The output end of the servo controller is connected to the input end of the driver. The output end of the driver is connected to the input end of the winch 501.

[0054] The servo controller receives the centralized force control instruction of the integrated control unit and the tension test signal of the test unit and performs calculations, and transmits the analog signal to the driver after the calculation is completed; the driver receives the control signal of the servo controller and amplifies it, thereby driving the winch 501 to move; the winch 501, the first steel wire rope 502, the spring 506, the second steel wire rope 503, the static force sensor, and the test piece 14 are connected in sequence, and the winch 501 pulls the first steel wire rope 502 by rotating the drum, and transmits the tension of the winch 501 to the test piece 14 through the spring 506 and the second steel wire rope 503.

[0055] The horizontal centering unit 6 is used to balance and offset the horizontal displacement of the horizontal mounting seat 2 under the action of the concentrated force, and the vertical centering unit 7 is used to balance and offset the vertical displacement of the vertical mounting seat 3 under the action of the concentrated force.

[0056] like Figure 6 As shown, the horizontal centering unit and the vertical centering unit each include at least one centering sub-component, each centering sub-component includes a single-rod hydraulic excitation cylinder 11, a servo valve 12 and a piston accumulator 13, one end of the single-rod hydraulic excitation cylinder 11 is fixedly connected to the horizontal mounting seat 2 or the vertical mounting seat 3, the piston accumulator 13 is connected to the upper chamber or the lower chamber in the cavity of the single-rod hydraulic excitation cylinder 11, and the servo valve 12 is installed on the connecting pipeline between the piston accumulator 13 and the single-rod hydraulic excitation cylinder 11.

[0057] Each set of centering components also includes a centering controller, which receives the vibration displacement signal and tensile test signal from the acquisition unit and performs calculations. The calculated signal is high-frequency filtered by the signal conditioning unit and then sent to the single-rod hydraulic excitation cylinder 11, the servo valve 12 and the piston accumulator 13. The hydraulic oil source provides the power source for the single-rod hydraulic excitation cylinder 11.

[0058] The single-rod hydraulic excitation cylinder 11 must utilize a hydrostatic bearing 306 sealing technology to ensure high-frequency follow-up excitation without damaging the piston and leaking oil. The low friction ensures good control accuracy. The piston accumulator 13 is connected to one of the upper or lower chambers of the single-rod hydraulic excitation cylinder 11, allowing the single-rod hydraulic excitation cylinder 11 to generate tension or pressure to offset the concentrated force. The centering controller outputs a current signal to the servo valve 12, which adjusts the servo opening size and direction based on the signal size, completing the oil filling and discharging process between the single-rod hydraulic excitation cylinder 11 and the piston accumulator 13, and completing the pressure change within the chamber. After being pre-charged with air pressure, the piston accumulator 13 forms a gas spring 506, which, on the one hand, achieves good vibration isolation for the excitation transducer 4, and also achieves decoupling control between dynamic excitation and static force regulation. This ensures that the excitation transducer 4 is not affected by the concentrated force and vibrates normally.

[0059] The centering component effectively solves the problem of the moving parts and table of the excitation transducer 4 being unable to vibrate due to the displacement of the working position caused by the concentrated force through force balance feedback control, moving parts position compensation and low-pass filtering signal processing.

[0060] The simulation test system also includes a moving component 9 and a lifting component. The moving component 9 is used to control the movement between the installation position of the test piece 14 and the test position; the moving end of the moving component 9 acts on the vibration output element 401 of the excitation transducer 4. The test box 1 includes a box 10, a first bottom plate and a second bottom plate. The lifting end of the lifting component acts on the box 10. The test position is located in the test box 1. When performing a horizontal high-frequency load excitation test, the lower end of the box 10 contacts the first bottom plate to form a sealed state. When performing a vertical high-frequency load excitation test, the lower end of the box 10 contacts the second bottom plate to form a sealed state. The box 10 is provided with a plurality of through-holes, which are used for passing the second steel wire rope 503 and the test cable through the cabin. The box 10 is sealed with the first and second bottom plates using a soft connection seal, and the through-holes are also sealed using a soft connection seal. The excitation transducer 4 is fixedly mounted on the moving end of the moving component 9. The moving component 9 is any one of a linear motor, a cylinder, and an oil cylinder. The lifting component is any one of a linear motor, a cylinder, and an oil cylinder.

[0061] like Figure 7 As shown, the temperature and humidity simulation unit 8 includes a temperature control component and a humidity control component. The temperature control component is used to control the temperature in the test box 1, and the humidity control component is used to control the humidity in the test box 1. The temperature control component can directly adopt cooling and heating equipment, or it can adopt cooling equipment plus heating equipment. The humidity control component includes a dryer and a humidifier. The control signal input ends of the temperature control component and the humidity control component are both connected to the control signal output end of the integrated control unit.

[0062] The vertical mounting seat 3 includes a vertical mounting platform 301, a support platform 302, a pneumatic support assembly 303 and an anti-overturning functional assembly. The two ends of the anti-overturning functional assembly are respectively fixedly connected to the support platform 302 and the vertical mounting platform 301. The two ends of the pneumatic support assembly 303 are respectively fixedly connected to the support platform 302 and the vertical mounting platform 301. The vibration output element 401 of the excitation transducer 4 is fixedly connected to the support platform 302.

[0063] The anti-overturning functional component includes multiple first connecting rods 304, multiple second connecting rods 305 and multiple bearings 306. The inner ring and outer ring of a bearing 306 are fixedly connected to a first connecting rod 304 and a second connecting rod 305 respectively. The upper end of the first connecting rod 304 is fixedly connected to the vertical mounting platform 301, and the lower end of the second connecting rod 305 is fixedly connected to the support platform 302.

[0064] The working principle of the aircraft simulation test system of the present invention is as follows:

[0065] The test piece 14 is mounted on the horizontal mounting base 2 or the vertical mounting base 3. Static force sensors, acceleration sensors, displacement sensors, strain sensors, etc. are mounted on the test piece 14. The excitation unit is moved to the test position using the moving assembly 9. The height of the box 10 is adjusted by the lifting mechanism to ensure that the test piece 14 is in the test box 1.

[0066] Pass the second wire rope 503 of the concentrated force simulation unit 5 through the penetration hole of the test chamber 1 and connect it to the static force sensor. Use the fixed pulley 504 to adjust the direction of the second wire rope 503 to horizontal, vertical, or a combination of horizontal and vertical directions, thereby applying concentrated force in any direction. Pass the cable of the acquisition unit through the penetration hole of the test chamber and connect it to the data acquisition instrument. Close the door of the test chamber 1 and seal the penetration hole. Start the integrated control unit and acquisition unit, and perform vibration-concentrated force-temperature composite control according to the test conditions.

[0067] The technical solution of the present invention is not limited to the above-mentioned specific embodiments. Any technical variations made according to the technical solution of the present invention fall within the protection scope of the present invention.

Claims

1. A simulation test system for an aircraft, characterized in that: include: Test chamber; Horizontal mounting bracket; vertical mounting base; Excitation transducer; The excitation transducer is used to provide horizontal or vertical high-frequency load excitation for the test piece, and the vibration output end of the excitation transducer acts on the horizontal mounting base or the vertical mounting base; A concentrated force simulation unit; the concentrated force simulation unit is used to apply concentrated forces in the horizontal and vertical directions to the test piece to simulate the static load on the test piece, and the concentrated force of the concentrated force simulation unit acts on the test piece; the concentrated force simulation unit includes a winch, a first steel wire rope, two sets of second steel wire ropes, two sets of fixed pulley assemblies and a support frame, the drum of the winch is fixedly connected to the first end of the first steel wire rope, the second end of the first steel wire rope is respectively connected to the first end of the two sets of second steel wire ropes, the two sets of fixed pulley assemblies are respectively used to control the direction of the concentrated forces of the two sets of second steel wire ropes on the test piece in the horizontal and vertical directions, and the two sets of fixed pulleys are installed on the support frame; Horizontal centering unit; the horizontal centering unit is used to control the vibration output of the excitation transducer and the horizontal mounting base to always be in the working position; the horizontal centering unit is used to balance and offset the horizontal displacement of the horizontal mounting base under the action of concentrated force; Vertical centering unit; the vertical centering unit is used to control the vibration output element and the vertical mounting seat of the excitation transducer to always be in the working position, and the vertical centering unit is used to balance and offset the vertical displacement of the vertical mounting seat under the action of concentrated force; the horizontal centering unit and the vertical centering unit each include at least one centering sub-component, each centering sub-component includes a single-rod hydraulic excitation cylinder, a servo valve and a piston accumulator, one end of the single-rod hydraulic excitation cylinder is fixedly connected to the horizontal mounting seat or the vertical mounting seat, the piston accumulator is connected to the upper chamber or the lower chamber in the cavity of the single-rod hydraulic excitation cylinder, and the servo valve is installed on the connecting pipeline between the piston accumulator and the single-rod hydraulic excitation cylinder; Temperature and humidity simulation unit: The temperature and humidity simulation unit is used to provide a temperature and humidity environment for the test piece. The temperature and humidity simulation unit includes a temperature control component and a humidity control component. The temperature control component is used to control the temperature inside the test chamber, and the humidity control component is used to control the humidity inside the test chamber. Acquisition unit: The acquisition unit is used to collect test data of the test piece during the test process; The integrated control unit is used to analyze the test data and control the working processes of the excitation transducer, the concentrated force simulation unit, and the temperature and humidity simulation unit. The control signal output end of the integrated control unit is connected to the control signal input end of the excitation transducer, the concentrated force simulation unit, and the temperature and humidity simulation unit, respectively. The data signal input end of the integrated control unit is connected to the data signal output end of the acquisition unit. When conducting a horizontal high-frequency load excitation test, the test piece is fixedly mounted on a horizontal mounting seat, and both the horizontal mounting seat and the test piece are located inside the test chamber, which is in a sealed state. When conducting a vertical high-frequency load excitation test, the test piece is fixedly mounted on a vertical mounting seat, and both the vertical mounting seat and the test piece are located inside the test chamber, which is in a sealed state.

2. The aircraft simulation test system according to claim 1, characterized in that: The acquisition unit includes an acceleration sensor, a static force sensor, a strain sensor, a temperature and humidity sensor, two displacement sensors, two pressure sensors and a data acquisition instrument. The data signal output ends of the acceleration sensor, static force sensor, strain sensor, temperature and humidity sensor, displacement sensor and pressure sensor are all connected to the data signal input end of the data acquisition instrument, and the data signal output end of the data acquisition instrument is connected to the data signal input end of the integrated control unit. The acceleration sensor, static force sensor and strain sensor are all installed on the test piece, and the temperature and humidity sensor is installed in the test box. The two pressure sensors are used to measure the output force of the horizontal centering unit and the vertical centering unit respectively. The two displacement sensors are used to measure the vibration displacement of the horizontal mounting seat and the vertical mounting seat respectively. The static force sensor is used to measure the concentrated force applied by the concentrated force simulation unit to the test piece.

3. The aircraft simulation test system according to claim 1, characterized in that: The concentrated force simulation unit also includes a spring, the second end of the first steel wire rope is fixedly connected to the first end of the spring, and the first ends of the two groups of second steel wire ropes are respectively fixedly connected to the second ends of the spring.

4. The aircraft simulation test system according to claim 1, characterized in that: The simulation test system also includes a moving component and a lifting component. The moving component is used for controlling the movement between the test piece installation position and the test position; the moving action end of the moving component acts on the vibration output member of the exciting transducer, the test box includes a box, a first bottom plate and a second bottom plate, the lifting action end of the lifting component acts on the box, and the test position is located in the test box. When performing a horizontal high-frequency load excitation test, the lower end of the box contacts the first bottom plate to form a sealed state. When performing a vertical high-frequency load excitation test, the lower end of the box contacts the second bottom plate to form a sealed state.

5. The aircraft simulation test system according to claim 1, characterized in that: The vertical mounting seat includes a vertical mounting platform, a support platform, a pneumatic support assembly and an anti-overturning functional assembly. The two ends of the anti-overturning functional assembly are respectively fixedly connected to the support platform and the vertical mounting platform. The two ends of the pneumatic support assembly are respectively fixedly connected to the support platform and the vertical mounting platform. The vibration output component of the excitation transducer is fixedly connected to the support platform.

6. The aircraft simulation test system according to claim 1, characterized in that: The anti-overturning functional component includes multiple first connecting rods, multiple second connecting rods and multiple bearings. The inner ring and outer ring of a bearing are fixedly connected to a first connecting rod and a second connecting rod respectively. The upper end of the first connecting rod is fixedly connected to the vertical mounting platform, and the lower end of the second connecting rod is fixedly connected to the support platform.

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