An auxiliary system and test method for aircraft system-level lightning and HIRF tests

Abstract

The present invention relates to the technical field of aircraft system testing, and discloses an auxiliary system and test method for aircraft system-level lightning and HIRF tests, wherein the auxiliary test system includes a simulation load mechanism, a data monitoring system, and a test product; the test product is a landing gear retraction and extension system, which is set up on a test bench for testing, and the simulation load mechanism will connect the processed signal to the data monitoring system through an A429 communication interface and a discrete quantity interface, and at the same time, the analog switch will adjust the working condition according to different test requirements, and the data monitoring system will analyze and record the collected data. The present invention simplifies the difficulty of platform cross-linking construction of system tests by simulating external equipment of the aircraft system, improves the integrity of the test, and reduces the test cost. At the same time, the test method can effectively judge the operating status of the solenoid valve and the oil circuit of the system during the experiment, so as to be able to comprehensively evaluate the stability of the system under HIRF and IEL environments.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft system testing, and more particularly to an auxiliary system and a testing method for aircraft system-level lightning and HIRF testing. Background Art

[0002] During flight, an aircraft will inevitably be subject to interference from high-intensity radiation fields (HIRF) and indirect lightning effects (IEL). The aircraft's avionics system, landing gear retraction system, power supply system and other electronic and electrical systems are more susceptible to their influence, which will seriously threaten the aircraft's take-off and landing safety. Therefore, the stability of each aircraft system in HIRF and IEL environments is particularly important for the safe flight of the aircraft.

[0003] For example, the landing gear retraction and extension system on the aircraft has a complex peripheral system interconnection environment and has functions such as position indication and alarm, and retraction and extension control that need to meet Class A requirements.

[0004] The position detection and retraction and extension control unit collects signals from various landing gear position sensors, receives the retraction and extension control signals from the control handle and the hydraulic source switching, low oil level alarm and other signals sent by the data interface unit, and drives the retraction and extension solenoid valves of the landing gear after internal logic calculation to realize the retraction and extension control function of the landing gear.

[0005] At the same time, the retraction and extension system controller sends signals such as system status, landing gear position and discrete quantity obtained by internal logic solution to the data interface unit and other systems on the aircraft to realize functions such as landing gear position indication and alarm.

[0006] Therefore, it is generally difficult to fully simulate the cross-linking environment of the actual aircraft system when conducting HIRF and IEL tests on aircraft systems. This application proposes an auxiliary system and testing method suitable for aircraft system-level tests, aiming to solve the above problems. Summary of the invention

[0007] The present invention provides an auxiliary system and a test method for aircraft system-level lightning and HIRF tests, which solve the technical problems in related technologies.

[0008] The present invention provides an auxiliary system for aircraft system-level lightning and HIRF tests, including a simulation load mechanism, a data monitoring system and a tested product;

[0009] The product under test is a landing gear retraction and extension system, which is set up on a test bench for testing. The landing gear retraction and extension system includes a main landing gear retraction and extension hydraulic rod, a front lift retraction and extension hydraulic rod and a redundant swing hydraulic rod. The moving ends of the front lift retraction and extension hydraulic rod and the redundant swing hydraulic rod are respectively connected to the two ends of the rear matching frame in the landing gear retraction and extension system. The bottom end of the main landing gear retraction and extension hydraulic rod is connected to the landing gear assembly. The main landing gear retraction and extension hydraulic rod, the front lift retraction and extension hydraulic rod and the redundant swing hydraulic rod are all provided with a solenoid valve connection port for matching test;

[0010] The simulated load mechanism includes the first, second and third data interface unit adapter interfaces, the switching control component adapter interface, the turning control box adapter interface, the first, second, third, fourth and fifth lightning protection and signal processing boards, the middle oil level low simulation switch, the right oil level low simulation switch, the first liquid level switching simulation switch, the second liquid level switching simulation switch, the A429 communication interface, the discrete quantity interface and the power supply interface;

[0011] After the wiring harness of the first data interface unit adapter interface enters, it passes through the first lightning protection and signal processing board to be connected to the pin in the A429 communication interface, and is also connected to the middle low oil level analog switch. After the wiring harness of the second data interface unit adapter interface enters, it passes through the second lightning protection and signal processing board to be connected to the pin in the A429 communication interface, and is also connected to the right low oil level analog switch. After the wiring harness of the third data interface unit adapter interface enters, it passes through the lightning protection and signal processing board to be connected to the pin in the A429 communication interface. After the wiring harness of the switching control component adapter interface enters, it passes through the fourth lightning protection and signal processing board to be connected to the liquid level switching analog switch and the pin of the liquid level switching analog switch. After the wiring harness of the turning control box adapter interface enters, it passes through the fifth lightning protection and signal processing board to be connected to the pin in the A429 communication interface, and is also connected to the discrete quantity interface. The power supply interface provides the required working power for the simulation load mechanism.

[0012] Data monitoring system: The simulated load mechanism will connect the processed signal to the data monitoring system through the A429 communication interface and the discrete quantity interface. At the same time, the analog switch will adjust the working conditions according to different test requirements. The data monitoring system will analyze and record the collected data.

[0013] Furthermore, the main landing gear retraction and extension hydraulic rod is a hydraulic component that controls the vertical movement of the landing gear assembly, and the front retraction and extension hydraulic rod and the redundant swing hydraulic rod are hydraulic components that collaboratively control the landing gear assembly to switch from horizontal / vertical to vertical / horizontal and vice versa.

[0014] Furthermore, the main landing gear retraction and extension hydraulic rod includes a main landing gear retraction and extension solenoid valve connection port and a main lifting and lowering retraction and extension solenoid valve connection port, and the main landing gear retraction and extension solenoid valve connection port and the main lifting and lowering retraction and extension solenoid valve connection port are both connected to the adapter interface of the simulated load mechanism through a test piece.

[0015] Furthermore, the front lifting and retracting hydraulic rod includes a front lifting and retracting solenoid valve connection port and a front lower lifting and retracting solenoid valve connection port, and the front lifting and retracting solenoid valve connection port and the front lower lifting and retracting solenoid valve connection port are both connected to the adapter interface of the simulated load mechanism through a test piece.

[0016] Furthermore, the redundant swing hydraulic rod includes a first solenoid valve connection port and a second solenoid valve connection port, and both the first solenoid valve connection port and the second solenoid valve connection port are connected to an adapter interface of the simulated load mechanism through a test piece.

[0017] Furthermore, the landing gear assembly includes a landing wheel and a wheel frame, the landing wheel is mounted on the wheel frame, and the top end of the wheel frame is connected to the door connecting frame and the rear matching frame through an axis.

[0018] Furthermore, the rear mating frame includes a Y-shaped frame, an angle sensor and a landing gear connector. The bottom end of the landing gear connector is connected to the wheel frame through an axis. The angle sensor is installed on the connecting axis between the Y-shaped frame and the landing gear connector. The angle sensor is used to test the retraction and extension angle of the landing gear assembly when the redundant swing hydraulic rod and the front retraction and extension hydraulic rod work together.

[0019] Furthermore, the data monitoring system is also connected to the angle sensor by telecommunication to record the working angle of the landing gear retraction and extension system collected by the angle sensor.

[0020] The present invention also proposes a testing method, which is based on the aforementioned auxiliary testing system suitable for aircraft system-level testing and includes the following steps:

[0021] S1: Arrange the tested product on the test bench in the effective test area, and use the test cable of the tested product to connect the controllers of each component;

[0022] S2: Connect the simulated load mechanism to the product under test, the peripheral equipment of the simulation system, including the first data interface unit, the second data interface unit, the third data interface unit, the turning control box and the landing gear switching control assembly, connect the A429 communication interface and the discrete quantity interface of the simulated load mechanism to the data monitoring system, and introduce the working power of each component to the power interface of the simulated load mechanism;

[0023] S3: Connect the oil outlet 1 of the hydraulic oil source vehicle to the P1 port of the landing gear hydraulic source switching master valve, the oil inlet 1 to the O1 port, the oil outlet 2 to the P2 port, and the oil inlet 2 to the O2 port. Install a liquid flow meter at the outlet of the oil outlet 1 and the oil outlet 2. The liquid flow meter is used to observe the flow change, obtain the oil circuit status and the working status of the landing gear hydraulic source switching master valve;

[0024] S4: Connect the landing gear hydraulic source switching master valve A port in parallel to the main landing gear retraction and extension solenoid valve O port, the main lifting lower position retraction and extension solenoid valve O port, the front lift door retraction and extension solenoid valve O port, and the front lift retraction and extension solenoid valve O port; connect the landing gear hydraulic source switching master valve B port in parallel to the main landing gear retraction and extension solenoid valve P port, the main lifting lower position retraction and extension solenoid valve P port, the front lift door retraction and extension solenoid valve P port, and the front lift retraction and extension solenoid valve P port;

[0025] S5: Connect the A port of the main landing gear retraction and extension solenoid valve to the inlet of the stop valve and the B port to the outlet of the stop valve. Install a pressure gauge to observe the pressure changes at both ends, so as to determine the status of the system oil circuit and the solenoid valve.

[0026] The testing process of S1-S5 also includes the following steps:

[0027] S6: Control the landing gear retraction and extension system through the middle oil level low simulation switch, the right oil level low simulation switch, the first liquid level switching simulation switch, and the second liquid level switching simulation switch on the simulation load mechanism to achieve the operating state under the test requirements;

[0028] S7: During the test, the data monitoring system collects various data indicators of the landing gear retraction and extension system in real time through the simulated load, including the retraction and extension angle, operation delay, and analyzes and records them;

[0029] S8: During the test, the oil circuit forms a closed-loop circulation, and the working status of the landing gear hydraulic source switching main valve can be effectively observed through the liquid flow meter. At the same time, by observing the rear end pressure gauge values ​​of the main landing gear retraction and extension solenoid valve, the main lift lower retraction and extension solenoid valve, the front lift door retraction and extension solenoid valve, and the front lift retraction and extension solenoid valve, the working status of each actuator valve and the direction of the oil circuit can be determined.

[0030] The beneficial effects of the present invention are:

[0031] The present invention greatly simplifies the difficulty of platform cross-linking construction of system tests by simulating external equipment of the aircraft system, greatly improves the integrity of the test, and reduces the test cost. At the same time, the test method proposed in the present invention can effectively determine the operating status of the solenoid valve and the oil circuit of the system during the experiment, thereby being able to comprehensively evaluate the stability of the system under HIRF and IEL environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 is a front view of the tested product of the present invention;

[0033] Figure 2 is a schematic structural diagram of another viewing angle of the test product of the present invention;

[0034] Figure 3 is a schematic diagram of the on-site arrangement of the test system of the present invention;

[0035] Figure 4 It is a schematic diagram of the oil circuit connection of the solenoid valve of the present invention;

[0036] Figure 5 is a front view of the simulated load mechanism of the present invention;

[0037] Figure 6 is a structural schematic diagram of the simulation load mechanism of the present invention from another viewing angle;

[0038] Figure 7 It is the data monitoring system software interface of the present invention.

[0039] In the figure: 100, main landing gear retracting and extending hydraulic rod; 110, main landing gear retracting and extending solenoid valve connection port; 120, main lifting lower position retracting and extending solenoid valve connection port; 200, front lifting and extending hydraulic rod; 210, front lifting and extending solenoid valve connection port; 220, front lifting lower position retracting and extending solenoid valve connection port; 300, redundant swing hydraulic rod; 310, first solenoid valve connection port; 320, second solenoid valve connection port; 330, connecting rod; 400, simulation load mechanism; 401, first data interface unit adapter interface; 402, second data interface unit adapter interface; 403, third data interface unit adapter interface; 404, switching control component adapter interface; 405, turning control box adapter interface; 406, 6. First lightning protection and signal processing board; 407. Second lightning protection and signal processing board; 408. Third lightning protection and signal processing board; 409. Fourth lightning protection and signal processing board; 410. Fifth lightning protection and signal processing board; 411. Middle oil level low analog switch; 412. Right oil level low analog switch; 413. First liquid level switching analog switch; 414. Second liquid level switching analog switch; 415. A429 communication interface; 416. Discrete quantity interface; 417. Power supply interface; 500. Landing gear assembly; 510. Landing wheel; 520. Wheel frame; 600. Door connecting frame; 700. Rear matching frame; 710. Y-shaped frame; 720. Angle sensor; 730. Landing gear connector. DETAILED DESCRIPTION

[0040] The subject matter described herein will now be discussed with reference to example implementations. It should be understood that the discussion of these implementations is only to enable those skilled in the art to better understand and implement the subject matter described herein, and the functions and arrangements of the elements discussed may be changed without departing from the scope of protection of the present specification. Various examples may omit, replace, or add various processes or components as needed. In addition, the features described in some examples may also be combined in other examples.

[0041] See also Figure 1-7As shown, at least one embodiment of the present invention discloses an auxiliary system for aircraft system-level lightning and HIRF tests, the auxiliary test system is used to test the landing gear retraction and extension system, that is, the test product in the landing gear retraction and extension system test, wherein the test product includes a main landing gear retraction and extension hydraulic rod 100, a front retraction and extension hydraulic rod 200 and a redundant swing hydraulic rod 300, the moving end of the redundant swing hydraulic rod 300 is connected to the rear matching frame 700 in the landing gear retraction and extension system, the bottom end of the main landing gear retraction and extension hydraulic rod 100 is connected to the landing gear assembly 500, and the simulation The load mechanism 400 is connected to the hydraulic test ends of the main landing gear retraction and extension hydraulic rod 100, the front lift retraction and extension hydraulic rod 200 and the redundant swing hydraulic rod 300 through an adapter interface. At the same time, the data monitoring system is connected to the simulation load mechanism 400 through telecommunications. The simulation load mechanism 400 is controlled by the control end on the data monitoring system to simulate different working conditions of the main landing gear retraction and extension hydraulic rod 100, the front lift retraction and extension hydraulic rod 200 and the redundant swing hydraulic rod 300, and the different working conditions of the three are combined to test the operating status of the landing gear retraction and extension system under HIRF and IEL environments.

[0042] It should be noted that the main landing gear retracting and extending hydraulic rod 100 is a hydraulic component that controls the landing gear assembly 500 to move in the vertical direction, and the front retracting and extending hydraulic rod 200 and the redundant swing hydraulic rod 300 are hydraulic components that cooperate to control the landing gear assembly 500 to switch from the horizontal state / vertical state to the vertical state / horizontal state and vice versa.

[0043] It should be noted that the main landing gear retracting and extending hydraulic rod 100 includes a main landing gear retracting and extending solenoid valve connection port 110 and a main lifting and lowering retracting and extending solenoid valve connection port 120, and both the main landing gear retracting and extending solenoid valve connection port 110 and the main lifting and lowering retracting and extending solenoid valve connection port 120 are connected to the adapter interface of the simulation load mechanism 400 through the test piece;

[0044] It should be noted that the front lifting and retracting hydraulic rod 200 includes a front lifting and retracting electromagnetic valve connection port 210 and a front lifting and lowering electromagnetic valve connection port 220, and both the front lifting and retracting electromagnetic valve connection port 210 and the front lifting and lowering electromagnetic valve connection port 220 are connected to the adapter interface of the simulation load mechanism 400 through the test piece;

[0045] It should be supplemented that the redundant swing hydraulic rod 300 includes a first solenoid valve connection port 310 and a second solenoid valve connection port 320, and both the first solenoid valve connection port 310 and the second solenoid valve connection port 320 are connected to the adapter interface of the simulation load mechanism 400 through the test piece;

[0046] It should be noted that the landing gear assembly 500 includes a landing wheel 510 and a wheel frame 520. The landing wheel 510 is mounted on the wheel frame 520. The top of the wheel frame 520 is connected to the door connecting frame 600 and the rear matching frame 700 through an axis. The door connecting frame 600 is used to connect the door structure of the landing gear compartment under the cabin. The rear matching frame 700 includes a Y-shaped frame 710, an angle sensor 720 and a landing gear connecting piece 730. The bottom end of the landing connecting piece is connected to the wheel frame 520 through an axis. 0, the angle sensor 720 is installed on the connecting shaft of the Y-shaped frame 710 and the landing connection member, and is used to test the retracting angle of the landing gear assembly 500 when the redundant swing hydraulic rod 300 and the front lifting and retracting hydraulic rod 200 work together. The retracting angle of the landing gear assembly 500 can correspond to the process of the landing gear switching from the horizontal state / vertical state to the vertical state / horizontal state in the actual working condition. The top end of the Y-shaped frame 710 is connected to the moving end of the redundant swing hydraulic rod 300 through the connecting rod 330;

[0047] The data monitoring system is also connected to the angle sensor 720 by telecommunication, and is used to reflect the stability of the landing gear retracting and extending system under the simulated load mechanism 400 by recording the deviation between the working angle of the landing gear retracting and extending system collected by the angle sensor 720 and the actual working angle;

[0048] In one embodiment of the present invention, the auxiliary system of the test includes a simulated load mechanism 400, a data monitoring system, and an electromagnetic valve oil circuit connecting the two and the product under test;

[0049] Specifically, the simulation load mechanism 400 includes a first data interface unit adapter interface 401, a second data interface unit adapter interface 402, a third data interface unit adapter interface 403, a switching control component adapter interface 404, a turning control box adapter interface 405, a first lightning protection and signal processing board 406, a second lightning protection and signal processing board 407, a third lightning protection and signal processing board 408, a fourth lightning protection and signal processing board 409, a fifth lightning protection and signal processing board 410, a middle oil level low analog switch 411, a right oil level low analog switch 412, a first liquid level switching analog switch 413, a second liquid level switching analog switch 414, an A429 communication interface 415, a discrete quantity interface 416 and a power supply interface 417;

[0050] In one embodiment of the present invention, the simulated load mechanism 400 is equipped with a first data interface unit adapter interface 401, a second data interface unit adapter interface 402, a third data interface unit adapter interface 403, a switching control component adapter interface 404, and a turning control box adapter interface 405. After the wiring harness of the first data interface unit adapter interface 401 enters, it is connected to the pin in the A429 communication interface 415 through the lightning protection and signal processing board, and is connected to the medium oil level low simulation switch 411. After the wiring harness of the second data interface unit adapter interface 402 enters, it is connected to the A429 communication interface 415 through the lightning protection and signal processing board. 5, and is connected to the right low oil level simulation switch 412 at the same time; the third data interface unit adapter interface 403 wiring harness enters and is connected to the pin in the A429 communication interface 415 through the lightning protection and signal processing board; the switching control component adapter interface 404 wiring harness enters and is connected to the liquid level switching simulation switch and the liquid level switching simulation switch pin through the lightning protection and signal processing board; the turning control box adapter interface 405 wiring harness enters and is connected to the pin in the A429 communication interface 415 through the lightning protection and signal processing board, and is connected to the discrete quantity interface 416 at the same time; the power supply interface 417 provides the required working power for the simulated load mechanism 400.

[0051] The simulated load mechanism 400 will connect the processed signal to the data monitoring system through the A429 communication interface 415 and the discrete quantity interface 416. At the same time, the analog switch will adjust the working conditions according to different test requirements, and the data monitoring system will analyze and record the collected data.

[0052] In one embodiment of the present invention, a test method of an auxiliary test system applied to an aircraft system-level test comprises the following steps:

[0053] S1: Arrange the tested product on the test bench in the effective area of ​​the test room, and use the test cable of the tested product to connect the controllers of each component;

[0054] S2: Connect the simulated load mechanism 400 to the product under test and the peripheral devices of the simulation system, including the first data interface unit (RDIU1), the second data interface unit (RDIU2), the third data interface unit (RDIU3), the turning control box (SCU) and the landing gear switching control assembly (KZH43), connect the A429 communication interface 415 and the discrete quantity interface 416 of the simulated load mechanism 400 to the data monitoring system, and introduce the working power of each component to the power interface 417 of the simulated load mechanism 400;

[0055] S3: Connect the oil outlet 1 of the hydraulic oil source vehicle to the P1 port of the landing gear hydraulic source switching master valve, the oil inlet 1 to the O1 port, the oil outlet 2 to the P2 port, and the oil inlet 2 to the O2 port, and install a liquid flow meter at the outlet of the oil outlet 1 and the oil outlet 2 to observe the flow change and judge the oil circuit state and the working state of the landing gear hydraulic source switching master valve;

[0056] S4: Connect the landing gear hydraulic source switching master valve A port in parallel to the main landing gear retraction and extension solenoid valve O port, the main lifting lower position retraction and extension solenoid valve O port, the front lift door retraction and extension solenoid valve O port, and the front lift retraction and extension solenoid valve O port; connect the landing gear hydraulic source switching master valve B port in parallel to the main landing gear retraction and extension solenoid valve P port, the main lifting lower position retraction and extension solenoid valve P port, the front lift door retraction and extension solenoid valve P port, and the front lift retraction and extension solenoid valve P port;

[0057] S5: Connect the A port of the main landing gear retraction and extension solenoid valve to the inlet of the stop valve, and the B port to the outlet of the stop valve. Install a pressure gauge to observe the pressure changes at both ends, so as to judge the status of the system oil circuit and the solenoid valve. The connections of other solenoid valves are the same as above.

[0058] The testing process of S1-S5 also includes the following steps:

[0059] S6: Control the landing gear retraction and extension system through the middle oil level low simulation switch 411, the right oil level low simulation switch 412, the first liquid level switching simulation switch 413, and the second liquid level switching simulation switch 414 on the simulation load mechanism 400 to achieve the operating state required by the test;

[0060] S7: During the test, the data monitoring system collects various data indicators of the landing gear retraction and extension system in real time through the simulated load, such as the retraction and extension angle, operation delay and other parameters, and analyzes and records them;

[0061] S8: During the test, the oil circuit forms a closed-loop circulation, and the working status of the landing gear hydraulic source switching main valve can be effectively observed through the liquid flow meter. At the same time, by observing the rear end pressure gauge values ​​of the main landing gear retraction and extension solenoid valve, the main lift lower retraction and extension solenoid valve, the front lift door retraction and extension solenoid valve, and the front lift retraction and extension solenoid valve, the working status of each actuator valve and the direction of the oil circuit can be determined.

[0062] The above test method simulates and designs some peripheral equipment of the aircraft system. In order to observe the data changes and function execution of the system in real time during the test, a data monitoring system is added to collect and analyze discrete quantities and A429 communication data. At the same time, an effective test method is proposed for the external solenoid valve and oil circuit status of the landing gear retraction and extension system.

[0063] The above describes an embodiment of the present invention, but this embodiment is not limited to the above-mentioned specific implementation mode. The above-mentioned specific implementation mode is merely illustrative and not restrictive. Under the guidance of this embodiment, ordinary technicians in this field can also make more forms of equivalent embodiments, all of which are within the protection of this embodiment.

Claims

1. An auxiliary system for aircraft system-level lightning and HIRF testing, characterized in that: include: The test product is set up on a test bench for testing, wherein the front lifting and retracting hydraulic rod (200) and the redundant swinging hydraulic rod (300) in the test product are respectively connected to the two ends of the rear matching frame (700) in the test product, the main landing gear retracting and extending hydraulic rod (100) in the test product is connected to the landing gear assembly (500), and the hydraulic rods in the test product are all provided with electromagnetic valve connection ports for matching testing; the simulated load mechanism (400), wherein the first, second, and third data interface unit adapter interfaces and the turning control box adapter interface (405) are all connected to the A429 communication interface (415), and the first data The interface unit adapter interface is also connected to the middle oil level low analog switch (411), the second data interface unit adapter interface (402) is also connected to the right oil level low analog switch (412), the switch control component adapter interface (404) is also connected to the first and second liquid level switch analog switches, the turning control box adapter interface (405) is also connected to the discrete quantity interface (416), and the power supply interface (417) provides the required working power; the data monitoring system is connected to the processed signal in the simulation load mechanism (400) through the A429 communication interface (415) and the discrete quantity interface (416); The rear coordination frame (700) comprises a Y-shaped frame (710), an angle sensor (720) and a landing gear connecting piece (730); the bottom end of the landing gear connecting piece is connected to the wheel frame (520) via a shaft; the angle sensor (720) is installed on the connecting shaft between the Y-shaped frame (710) and the landing gear connecting piece; the angle sensor (720) is used to test the retraction angle of the landing gear assembly (500) when the redundant swing hydraulic rod (300) and the front retraction hydraulic rod (200) work in coordination; The data monitoring system is also connected to the angle sensor (720) by telecommunication, and records the working angle of the landing gear retraction and extension system collected by the angle sensor (720).

2. The auxiliary system for aircraft system-level lightning and HIRF testing according to claim 1, characterized in that: The main landing gear retraction and extension hydraulic rod (100) is a hydraulic component that controls the landing gear assembly (500) to move in the vertical direction, and the front retraction and extension hydraulic rod (200) and the redundant swing hydraulic rod (300) are hydraulic components that cooperatively control the landing gear assembly (500) to switch from a horizontal state / vertical state to a vertical state / horizontal state and vice versa.

3. The auxiliary system for aircraft system-level lightning and HIRF testing according to claim 2, characterized in that: The main landing gear retraction and extension hydraulic rod (100) comprises a main landing gear retraction and extension solenoid valve connection port (110) and a main lift-down retraction and extension solenoid valve connection port (120), and both the main landing gear retraction and extension solenoid valve connection port (110) and the main lift-down retraction and extension solenoid valve connection port (120) are connected to an adapter interface of the simulation load mechanism (400) through a test piece.

4. The auxiliary system for aircraft system-level lightning and HIRF testing according to claim 3, characterized in that: The front lifting and retracting hydraulic rod (200) comprises a front lifting and retracting electromagnetic valve connection port (210) and a front lifting and lowering electromagnetic valve connection port (220), and both the front lifting and retracting electromagnetic valve connection port (210) and the front lifting and lowering electromagnetic valve connection port (220) are connected to an adapter interface of the simulation load mechanism (400) through a test piece.

5. The auxiliary system for aircraft system-level lightning and HIRF testing according to claim 4, characterized in that: The redundant swing hydraulic rod (300) comprises a first solenoid valve connection port (310) and a second solenoid valve connection port (320); the first solenoid valve connection port (310) and the second solenoid valve connection port (320) are both connected to an adapter interface of the simulated load mechanism (400) through a test piece.

6. The auxiliary system for aircraft system-level lightning and HIRF testing according to claim 5, characterized in that: The landing gear assembly (500) comprises a landing wheel (510) and a wheel frame (520). The landing wheel (510) is mounted on the wheel frame (520). The top end of the wheel frame (520) is connected to a door connecting frame (600) and a rear matching frame (700) via a shaft.

7. A test method, based on the auxiliary system for aircraft system-level lightning and HIRF tests as described in any one of claims 1 to 6, characterized in that: The following steps are involved: S1: Arrange the tested product on the test bench in the effective test area, and use the test cable of the tested product to connect the controllers of each component; S2: Connecting the simulated load mechanism (400) to the product under test, the peripheral equipment of the simulation system, including a first data interface unit, a second data interface unit, a third data interface unit, a turning control box, and a landing gear switching control component, connecting the A429 communication interface (415) and the discrete quantity interface (416) of the simulated load mechanism to the data monitoring system, and introducing the working power supply of each component to the power supply interface (417) of the simulated load mechanism (400); S3: Connect the oil outlet 1 of the hydraulic oil source vehicle to the P1 port of the landing gear hydraulic source switching master valve, the oil inlet 1 to the O1 port, the oil outlet 2 to the P2 port, and the oil inlet 2 to the O2 port. Install a liquid flow meter at the outlet of the oil outlet 1 and the oil outlet 2. The liquid flow meter is used to observe the flow change, obtain the oil circuit status and the working status of the landing gear hydraulic source switching master valve; S4: Connect the landing gear hydraulic source switching master valve A port in parallel to the main landing gear retraction and extension solenoid valve O port, the main lift lower retraction and extension solenoid valve O port, the front lift door retraction and extension solenoid valve O port, and the front lift retraction and extension solenoid valve O port; connect the landing gear hydraulic source switching master valve B port in parallel to the main landing gear retraction and extension solenoid valve P port, the main lift lower retraction and extension solenoid valve P port, the front lift door retraction and extension solenoid valve P port, and the front lift retraction and extension solenoid valve P port; S5: Connect the A port of the main landing gear retraction and extension solenoid valve to the inlet of the stop valve and the B port to the outlet of the stop valve. Install a pressure gauge to observe the pressure changes at both ends to determine the status of the system oil circuit and the solenoid valve.

8. A testing method according to claim 7, characterized in that: The testing process of S1-S5 also includes the following steps: S6: controlling the landing gear retraction and extension system through the middle oil level low simulation switch (411), the right oil level low simulation switch (412), the first liquid level switching simulation switch (413), and the second liquid level switching simulation switch (414) on the simulation load mechanism (400) so that the system reaches the operating state required by the test; S7: During the test, the data monitoring system collects various data indicators of the landing gear retraction and extension system in real time through the simulated load, including the retraction and extension angle, operation delay, and analyzes and records them; S8: During the test, the oil circuit forms a closed-loop circulation, and the working status of the landing gear hydraulic source switching main valve can be effectively observed through the liquid flow meter. At the same time, by observing the rear end pressure gauge values ​​of the main landing gear retraction and extension solenoid valve, the main lift lower retraction and extension solenoid valve, the front lift door retraction and extension solenoid valve, and the front lift retraction and extension solenoid valve, the working status of each actuator valve and the direction of the oil circuit can be determined.

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