An aircraft engine nozzle control accessory testing system and method

Abstract

The application discloses an aero-engine nozzle control accessory test system and method, comprising: a simulation actuator, which is internally provided with a plurality of independent hydraulic cavities, for simulating the volume characteristics of a real engine guide vane actuator cylinder; a displacement detection assembly, comprising a linear displacement sensor and an angular displacement sensor arranged on the simulation actuator; an electronic control unit, which is signal-connected with the displacement detection assembly; a hydraulic control module, comprising a pressure regulating unit and an oil path switching unit, which are communicated with each cavity of the simulation actuator; wherein the electronic control unit is configured to apply controllable hydraulic pressure to the corresponding cavity of the simulation actuator by controlling the pressure regulating unit, and selectively guide the hydraulic oil output by the test piece to the simulation actuator or the flow monitoring unit by the oil path switching unit, while receiving the feedback signal of the displacement detection assembly to form a closed-loop control.

Description

Technical Field

[0001] This invention belongs to the field of aviation industry testing, and relates to a test system and method for aviation engine nozzle control accessories. Background Technology

[0002] In the aviation industry, the performance testing and verification of aero-engines are crucial for ensuring flight safety and improving flight efficiency. Among these components, the nozzle control accessories, as vital parts for adjusting engine thrust and direction, directly impact the operational efficiency of the engine and the entire flight system. Therefore, comprehensive testing is essential during the development of nozzle control accessories to verify whether their design specifications meet the requirements of actual operating conditions.

[0003] Traditionally, testing of aero-engine nozzle control accessories has relied on two main methods: one is the dead-cavity pressure measurement method, which assesses accessory performance by measuring pressure changes in a closed system. However, this method cannot realistically simulate the dynamic environment of accessories during actual operation. The other is simulation testing under selected conditions after open-loop calibration of the equivalent actuator. While this can simulate actual operating conditions to some extent, its open-loop nature makes it difficult to comprehensively and accurately reflect the behavior of accessories in a real closed-loop control system, especially for accessories under development, where a comprehensive assessment of their true capabilities is impossible. Specifically, existing testing technologies have the following shortcomings: First, the dead-cavity pressure measurement method lacks dynamic simulation capabilities and cannot reflect the real-time response of accessories under different operating conditions. Second, although the open-loop calibration test of the equivalent actuator can simulate some operating conditions, its open-loop control makes it difficult to accurately reproduce the complex behavior of accessories in a real closed-loop system, such as the control and feedback of key parameters like pressure fluctuations and flow rate changes. Finally, existing testing methods, when simulating the actions of real engine nozzles, cannot achieve comprehensive testing that matches the actual engine nozzle, leading to discrepancies between test results and practical applications. Summary of the Invention

[0004] The purpose of this invention is to provide a test system and method for aero-engine nozzle control accessories, so as to overcome the shortcomings of the prior art.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows: According to a first aspect of the present invention, a test system for an aircraft engine nozzle control accessory is provided, comprising: The simulated actuator has multiple independent hydraulic cavities inside, which are used to simulate the volumetric characteristics of the guide vane actuator of a real engine. The displacement detection assembly includes a linear displacement sensor and an angular displacement sensor disposed on the simulated actuator; The electronic control unit is connected to the displacement detection component via signal transmission. The hydraulic control module includes a pressure regulating unit and an oil circuit switching unit that are connected to each cavity of the simulated actuator; The electronic control unit is configured to apply controllable hydraulic pressure to the corresponding cavity of the simulated actuator by controlling the pressure regulating unit, and selectively guide the hydraulic oil output by the test piece to the simulated actuator or the flow monitoring unit through the oil circuit switching unit, while receiving feedback signals from the displacement detection component to form closed-loop control.

[0006] In one possible implementation of the first aspect, the simulated actuator is an equivalent actuator cylinder, which has a loading chamber, a rodless chamber and a rod chamber arranged sequentially from left to right inside the equivalent actuator cylinder, and each chamber is provided with an independent oil supply port.

[0007] In one possible implementation of the first aspect, the linear displacement sensor is a linear displacement sensor and is disposed at one end of the loading chamber of the equivalent actuator piston rod; the angular displacement sensor is disposed at one end of the rod chamber of the equivalent actuator and converts the linear displacement of the piston rod into angular displacement through a linkage mechanism.

[0008] In one possible implementation of the first aspect, the pressure regulating unit includes a pressure regulating valve, the inlet of which is connected to an oil supply pump, the outlet of which is connected to the oil supply port of the loading chamber of the equivalent actuator, and the control terminal of which is connected to the electrical control unit.

[0009] In one possible implementation of the first aspect, the oil circuit switching unit includes a first two-position three-way solenoid valve and a second two-position three-way solenoid valve. The inlets of the first two-position three-way solenoid valve and the second two-position three-way solenoid valve are used to connect to the oil port of the test piece. The working outlets of the first two-position three-way solenoid valve and the second two-position three-way solenoid valve are respectively connected to the oil supply ports of the rodless chamber and the rod chamber of the equivalent actuator. The return oil outlets of the first two-position three-way solenoid valve and the second two-position three-way solenoid valve are connected to the flow meter.

[0010] In one possible implementation of the first aspect, a first choke nozzle and a second choke nozzle for buffering and reducing pressure are respectively provided in the oil line between the return oil outlet of the first two-position three-way solenoid valve and the second two-position three-way solenoid valve and the flow meter.

[0011] In one possible implementation of the first aspect, a third shut-off nozzle is provided between the oil supply port of the rodless chamber of the equivalent actuator and the connecting oil passage.

[0012] In one possible implementation of the first aspect, a two-position two-way solenoid valve is also included, one end of which is connected to the oil supply line of the rod chamber of the equivalent actuator, and the other end returns oil through a fourth throttle nozzle.

[0013] In one possible implementation of the first aspect, the electronic control unit is an electronic controller, the signal acquisition terminal of the electronic controller is connected to the angular displacement sensor and the linear displacement sensor, and the control output terminal of the electronic controller is connected to the control terminal of the test piece.

[0014] According to a second aspect of the present invention, a test method for an aircraft engine nozzle control accessory is provided, employing the aforementioned aircraft engine nozzle control accessory test system, comprising: The voltage regulating unit is controlled by the electronic control unit to apply dynamic pressure to a specific cavity of the analog actuator. The electronic control unit sends commands to the test piece to control the output of hydraulic oil. The displacement signal of the simulated actuator is detected in real time by a displacement detection component; The detected displacement signal is fed back to the electronic control unit; The electronic control unit adjusts the control commands to the voltage regulating unit and the test piece based on the feedback signal, forming a closed-loop control.

[0015] Compared with the prior art, the present invention has the following beneficial technical effects: The aero-engine nozzle control accessory testing system provided by this invention, by setting up a simulated actuator with multiple independent hydraulic cavities, can accurately simulate the volumetric and load characteristics of the guide vane actuator cylinder of a real engine, effectively reproducing the installation and working environment of the test piece on a real engine, overcoming the shortcomings of traditional dead-cavity pressure measurement methods that cannot simulate dynamic environments. By integrating linear and angular displacement sensors, and cooperating with an electronic control unit and hydraulic control module, a closed-loop control system is constructed to collect motion feedback in real time and dynamically adjust the load and control signals, thereby comprehensively evaluating the dynamic response, pressure-flow characteristics, and control accuracy of the test piece in the closed-loop state, solving the problem that open-loop calibration tests cannot simulate complex closed-loop behavior. The oil circuit switching unit enables flexible switching of testing functions, allowing for dynamic performance testing with simulated loads or switching to pure flow testing, expanding the testing range and improving equipment utilization. By integrating the control pressure regulating unit, test piece, and oil circuit switching unit through the electronic control unit, the testing process is automated and precisely adjusted, reducing human intervention and making the test results more reliable.

[0016] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the specific embodiments of the present invention, the drawings used in the description of the specific embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of a test system for an aircraft engine nozzle control accessory according to an embodiment of the present invention.

[0019] In the figure, 1-equivalent actuator, 2a-first two-position three-way solenoid valve, 2b-second two-position three-way solenoid valve, 3-angular displacement sensor, 4-test piece, 5-electronic controller, 6a-third shut-off nozzle, 6b-fourth shut-off nozzle, 6c-first shut-off nozzle, 6d-second shut-off nozzle, 7-pressure regulating valve, 8-flow meter, 9-two-position two-way solenoid valve, 10-linear displacement sensor. Detailed Implementation

[0020] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0021] The testing system provided by this invention is mainly used to perform performance tests on aero-engine nozzle control accessories (hereinafter referred to as test components). It can simulate the load characteristics and motion state of the real engine guide vane actuator and realize full closed-loop control, thereby accurately reproducing the dynamic behavior of the accessories in the real working environment.

[0022] like Figure 1 As shown, the system mainly consists of four parts: a simulated actuator, a displacement detection component, an electrical control unit, and a hydraulic control module. The simulated actuator uses an equivalent actuator cylinder 1, which has a loading chamber, a rodless chamber, and a rod chamber arranged sequentially from left to right. Each chamber is equipped with an independent hydraulic oil interface, which can accept pressurized oil and be controlled independently to accurately simulate the multi-chamber volume characteristics of a real actuator cylinder.

[0023] The displacement detection assembly includes a linear displacement sensor 10 (LVDT) and an angular displacement sensor 3 (RVDT). The linear displacement sensor 10 is mounted on one side of the loading chamber of the piston rod in the equivalent actuator 1, and is used to directly detect the linear displacement of the piston rod. The angular displacement sensor 3 is located at one end of the rod chamber and converts the linear motion of the piston rod into rotational motion through a linkage mechanism, thereby outputting an angular displacement signal. The displacement detection assembly can simultaneously acquire both linear and rotational displacement parameters, comprehensively reflecting the motion state of the actuator.

[0024] The electronic control unit uses an electronic controller 5 (ECC), whose signal acquisition end is connected to the linear displacement sensor 10 and the angular displacement sensor 3 to receive displacement signals in real time; its control output end is connected to the control interfaces of various valves in the hydraulic control module and the test piece 4.

[0025] The hydraulic control module mainly includes a pressure regulating unit and an oil circuit switching unit. The pressure regulating unit includes a pressure regulating valve 7, whose inlet is connected to an external oil supply pump, and whose outlet is connected to the oil supply port of the loading chamber of the equivalent actuator 1. The control end is regulated by an electronic controller 5 and is used to apply a dynamically adjustable hydraulic load to the loading chamber.

[0026] The oil circuit switching unit consists of a first two-position three-way solenoid valve 2a and a second two-position three-way solenoid valve 2b. The inlets of both valves are connected to the oil outlet of the test piece 4, and their working outlets are respectively connected to the oil supply ports of the rodless and rod chambers of the equivalent actuator 1. The return oil outlets are connected to a flow meter 8. The flow meter 8 is used to monitor the oil flow rate at the outlet of the test piece 4. In the oil circuit between the return oil outlets of the first two-position three-way solenoid valve 2a and the second two-position three-way solenoid valve 2b and the flow meter 8, a first choke nozzle 6c and a second choke nozzle 6d are connected in series, serving to buffer and reduce oil pressure.

[0027] To further simulate the characteristics of the oil circuit under real working conditions, a third shut-off nozzle 6a is also provided between the oil supply port of the rodless chamber of the equivalent actuator 1 and the connecting oil circuit. In addition, a two-position two-way solenoid valve 9 is connected in parallel to the oil supply line of the rod chamber of the equivalent actuator 1. The other end of the valve is connected to the return oil circuit via a fourth shut-off nozzle 6b, which is used to provide a bypass return oil path when the rod chamber oil circuit needs to be depressurized or regulated.

[0028] The working process of the testing system provided in this embodiment is as follows: The voltage regulating unit is controlled by the electronic control unit to apply dynamic pressure to a specific cavity of the analog actuator. The electronic control unit sends commands to the test piece to control the output of hydraulic oil. The displacement signal of the simulated actuator is detected in real time by a displacement detection component; The detected displacement signal is fed back to the electronic control unit; The electronic control unit adjusts the control commands to the voltage regulating unit and the test piece based on the feedback signal, forming a closed-loop control.

[0029] Specifically, according to the preset test program, the electronic controller 5 first controls the pressure regulating valve 7 to apply a certain initial pressure to the loading chamber of the equivalent actuator 1, simulating the load of the real actuator. Then, the electronic controller 5 sends a control command to the test piece 4, causing it to output pressurized oil. Guided by the switching of the first two-position three-way solenoid valve 2a and the second two-position three-way solenoid valve 2b, the oil selectively enters either the rodless or rod chamber of the equivalent actuator 1, driving the piston rod. The movement of the piston rod is detected in real time by the linear displacement sensor 10 and the angular displacement sensor 3 converted through the linkage mechanism, and fed back to the electronic controller 5. The electronic controller 5 compares the received displacement feedback signal with the preset ideal displacement curve and adjusts two outputs in real time according to the deviation value: one is the command sent to the test piece 4 to change the pressure or flow rate of its output oil; the other is the command sent to the pressure regulating valve 7 to dynamically adjust the pressure in the loading chamber. Through this dual-loop adjustment, the system forms a closed-loop control, enabling the movement of the equivalent actuator 1 to closely follow the preset pattern, thereby achieving a comprehensive and accurate test of the performance of the test piece 4 under simulated real working conditions. During flow testing, the electronic controller 5 can control the first two-position three-way solenoid valve 2a and the second two-position three-way solenoid valve 2b to switch to the oil return position, so that the oil output from the test piece 4 does not enter the actuator but flows directly to the flow meter 8 after being buffered by the throttle nozzle, thus realizing the measurement of the output flow of the test piece.

[0030] In one embodiment, more specifically, such as Figure 1 As shown, a test system for the nozzle control accessories of an aero-engine mainly includes an equivalent actuator 1, a first two-position three-way solenoid valve 2a, a second two-position three-way solenoid valve 2b, an angular displacement sensor 3, an electronic controller 5, a pressure regulating valve 7, a flow meter 8, a linear displacement sensor 10, and multiple shut-off nozzles, etc.

[0031] The equivalent actuator 1 serves as the simulated actuator of the test system. Internally, from left to right, it comprises three independent hydraulic chambers: a loading chamber, a rodless chamber, and a rod chamber. Each chamber has an independent oil supply port, and its volume is calculated to accurately simulate the volumetric characteristics of a real engine guide vane actuator. A linear displacement sensor 10 is installed at one end of the piston rod in the loading chamber of the equivalent actuator 1 to detect the linear displacement of the piston rod in real time. A connecting rod mechanism is installed at one end of the rod chamber of the equivalent actuator 1 to convert the linear displacement of the piston rod into angular displacement. An angular displacement sensor 3 is installed at the hinge point of this connecting rod mechanism to detect the converted angular displacement.

[0032] The inlet of the pressure regulating valve 7 is connected to an external oil supply pump, and the outlet is connected to the oil supply port of the loading chamber of the equivalent actuator cylinder 1. The control terminal of the pressure regulating valve 7 is connected to the electronic controller 5, receiving command signals from the electronic controller 5 and dynamically adjusting the oil pressure in the loading chamber.

[0033] The inlets of the first two-position three-way solenoid valve 2a and the second two-position three-way solenoid valve 2b are connected to the oil ports C1 and C2 of the test piece 4, respectively. The working outlets of the first two-position three-way solenoid valve 2a and the second two-position three-way solenoid valve 2b are connected to the oil supply ports of the rodless chamber and the rod chamber of the equivalent actuator 1, respectively, and the return oil outlets are connected to the flow meter 8. In the oil line between the return oil outlets of the first two-position three-way solenoid valve 2a and the second two-position three-way solenoid valve 2b and the flow meter 8, a first choke nozzle 6c and a second choke nozzle 6d are respectively provided to buffer the oil and reduce the pressure, simulating the back pressure of the system.

[0034] A pressure measuring unit is also installed on the outlet connecting pipes of oil port C1 and oil port C2 of test piece 4 to monitor the pressure of the oil output from test piece 4.

[0035] A third shut-off nozzle 6a is installed between the oil supply port of the rodless chamber of the equivalent actuator 1 and the connecting oil circuit. In addition, the test system is also equipped with a one-position, two-position, two-way solenoid valve 9, one end of which is connected to the oil supply line of the rod chamber of the equivalent actuator 1, and the other end returns oil through the fourth shut-off nozzle 6b, which is used to eliminate oil shock during actual operation and to simulate on / off control.

[0036] The signal output terminals of angular displacement sensor 3 and linear displacement sensor 10 are connected to the signal acquisition terminal of electronic controller 5 via communication cables. The control output terminal of electronic controller 5 is connected to the control terminal of test piece 4, forming a complete closed-loop control circuit.

[0037] During operation, the electronic controller 5 first applies a set dynamic pressure to the loading chamber of the equivalent actuator 1 via the pressure regulating valve 7. Then, the electronic controller 5 sends a control command to the test piece 4, which outputs hydraulic oil according to the command. The hydraulic oil is distributed by the first two-position three-way solenoid valve 2a and the second two-position three-way solenoid valve 2b, entering the rodless chamber and the rod chamber of the equivalent actuator 1 respectively, thus driving the piston rod.

[0038] The movement of the piston rod is detected in real time by the linear displacement sensor 10 and the angular displacement sensor 3, and the detected displacement signals are fed back to the electronic controller 5. The electronic controller 5 compares the feedback signal with the expected signal, and dynamically adjusts the control commands to the pressure regulating valve 7 and the test piece 4 according to the comparison result, so as to realize the closed-loop dynamic test of the performance of the test piece 4.

[0039] When an open-loop flow test is required, the oil from the test piece 4 can be directly directed to the flow meter 8 by controlling the first two-position three-way solenoid valve 2a and the second two-position three-way solenoid valve 2b, so that the flow can be measured.

[0040] In the description of this invention, it should be understood that the terms "upper", "lower", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0041] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0042] In this invention, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0043] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0044] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0045] Finally, it should be noted that the above-described embodiments are merely specific implementations of the present invention, used to illustrate the technical solutions of the present invention, and not to limit them. The scope of protection of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that any person skilled in the art can still modify or easily conceive of changes to the technical solutions described in the foregoing embodiments within the scope of the technology disclosed in the present invention, or make equivalent substitutions for some of the technical features; and these modifications, changes, or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be covered within the scope of protection of the present invention.

Claims

1. A test system for an aircraft engine nozzle control accessory, characterized in that, include: The simulated actuator has multiple independent hydraulic cavities inside, which are used to simulate the volumetric characteristics of the guide vane actuator of a real engine. The displacement detection assembly includes a linear displacement sensor and an angular displacement sensor disposed on the simulated actuator; The electronic control unit is connected to the displacement detection component via signal transmission. The hydraulic control module includes a pressure regulating unit and an oil circuit switching unit that are connected to each cavity of the simulated actuator; The electronic control unit is configured to apply controllable hydraulic pressure to the corresponding cavity of the simulated actuator by controlling the pressure regulating unit, and selectively guide the hydraulic oil output by the test piece to the simulated actuator or the flow monitoring unit by the oil circuit switching unit, while receiving feedback signals from the displacement detection component to form closed-loop control. The simulated actuator is an equivalent actuator cylinder (1). The equivalent actuator cylinder (1) has a loading chamber, a rodless chamber and a rod chamber arranged from left to right inside. Each chamber is provided with an independent oil supply interface. The pressure regulating unit includes a pressure regulating valve (7), the inlet of which is used to connect to the oil supply pump, the outlet of which is connected to the oil supply port of the loading chamber of the equivalent actuator (1), and the control end of which is connected to the electrical control unit. The oil circuit switching unit includes a first two-position three-way solenoid valve (2a) and a second two-position three-way solenoid valve (2b). The inlets of the first two-position three-way solenoid valve (2a) and the second two-position three-way solenoid valve (2b) are used to connect to the oil port of the test piece (4). The working outlets of the first two-position three-way solenoid valve (2a) and the second two-position three-way solenoid valve (2b) are respectively connected to the oil supply ports of the rodless chamber and the rod chamber of the equivalent actuator (1). The return oil outlets of the first two-position three-way solenoid valve (2a) and the second two-position three-way solenoid valve (2b) are connected to the flow monitoring unit.

2. The test system for aero-engine nozzle control accessories according to claim 1, characterized in that, The linear displacement sensor is a linear displacement sensor (10), which is set at one end of the loading chamber of the piston rod of the equivalent actuator (1); the angular displacement sensor (3) is set at one end of the rod chamber of the equivalent actuator (1), and converts the linear displacement of the piston rod into angular displacement through the linkage mechanism.

3. The test system for aero-engine nozzle control accessories according to claim 1, characterized in that, A first choke nozzle (6c) and a second choke nozzle (6d) are respectively installed on the oil line between the return oil outlet of the first two-position three-way solenoid valve (2a) and the second two-position three-way solenoid valve (2b) and the flow monitoring unit for buffering and reducing pressure.

4. The test system for aero-engine nozzle control accessories according to claim 1, characterized in that, A third shut-off nozzle (6a) is provided between the oil supply port of the rodless cavity of the equivalent actuator (1) and the connecting oil circuit.

5. The test system for aero-engine nozzle control accessories according to claim 1, characterized in that, It also includes a two-position two-way solenoid valve (9), one end of which is connected to the oil supply line of the rod chamber of the equivalent actuator (1), and the other end returns oil through the fourth choke nozzle (6b).

6. The test system for aero-engine nozzle control accessories according to claim 1, characterized in that, The electronic control unit is an electronic controller (5). The signal acquisition terminal of the electronic controller (5) is connected to the angular displacement sensor (3) and the linear displacement sensor (10). The control output terminal of the electronic controller (5) is connected to the control terminal of the test piece (4).

7. A test method for an aircraft engine nozzle control accessory, characterized in that, The test system for aero-engine nozzle control accessories as described in any one of claims 1-6 includes: The voltage regulating unit is controlled by the electronic control unit to apply dynamic pressure to a specific cavity of the analog actuator. The electronic control unit sends commands to the test piece to control the output of hydraulic oil. The displacement signal of the simulated actuator is detected in real time by a displacement detection component; The detected displacement signal is fed back to the electronic control unit; The electronic control unit adjusts the control commands to the voltage regulating unit and the test piece based on the feedback signal, forming a closed-loop control.

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