Remote control system for aero-engine test

Abstract

The invention provides a remote control system for an aero-engine test, and the system comprises a rack control and communication device which comprises a first network switch, an airborne sensor parameter obtaining module, an engine throttle lever solver, and a first signal transmission extender group; the electrical test communication device comprises a second network switch; the second network switch is connected with the first network switch through a second optical fiber; the remote measurement and control device comprises a third network switch, a control master station and an engine throttle lever control module; the third network switch is connected with the second network switch through a third optical fiber; the third network switch is also directly connected with the first network switch through a fourth optical fiber; wherein the engine throttle lever control module is directly connected with the engine throttle lever solver through a first optical fiber; the airborne sensor parameter acquisition module is connected with the first network switch through a network cable; and airborne sensor parameters are transmitted to the third network switch through the second optical fiber and the third optical fiber.

Description

Technical Field

[0001] The present invention mainly relates to the field of aero-engines, and in particular to an aero-engine test remote control system. Background Art

[0002] Aircraft engines are the core power source of aircraft and are very complex aerodynamic and thermal rotating machines. Aircraft engines have many parts, and many of them work under high temperature, high pressure, high-speed rotation, strong vibration and complex and changing environmental conditions. They need to frequently withstand high loads and thermal shocks, and the working environment is extremely harsh.

[0003] The design and manufacture of aircraft engines require a large number of different types of tests, such as core engines, complete engines, high-altitude platforms and open-air platforms. Testers need to pay close attention to the various state parameters of the engine during the test. But under normal circumstances, the test control room is usually close to the test engine, sometimes only separated by a wall. If the engine catches fire or has a non-contained failure, it will pose an extremely huge safety risk to the test personnel and related test equipment. Non-contained failures include, for example, broken blades or damaged casings. Based on this, how to provide a remote control system for aircraft engine testing is a topic that needs to be addressed. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide an aero-engine test remote control system to achieve safe and efficient aero-engine test.

[0005] In order to solve the above technical problems, the present invention provides an aero-engine test remote control system, comprising: a control and communication device at a test bench, comprising a first network switch, an airborne sensor parameter acquisition module, an engine throttle lever resolver and a first signal transmission extender group; an electrical test communication device, comprising a second network switch; the second network switch and the first network switch are connected through a second optical fiber; a remote measurement and control device, comprising a third network switch, a control master station and an engine throttle lever control module; the third network switch and the second network switch are connected through a third optical fiber; the third network switch is also directly connected to the first network switch through a fourth optical fiber; Among them, the engine throttle lever control module is directly connected to the engine throttle lever resolver through a first optical fiber; the airborne sensor parameter acquisition module is connected to the first network switch through a network cable; the airborne sensor parameters are transmitted to the third network switch through a second optical fiber and a third optical fiber; the first connection end of the first signal transmission extender group is connected to the operation interface corresponding to the airborne sensor parameter acquisition module through a universal serial bus connection line; the second connection end of the first signal transmission extender group is connected to the first network switch through a network cable; the operation interface signal corresponding to the airborne sensor parameter acquisition module is transmitted to the third network switch through a fourth optical fiber.

[0006] In one embodiment of the present invention, the onboard sensor parameter acquisition module includes a host computer corresponding to the engine electronic control unit, a host computer corresponding to the engine health monitoring unit, and a data conversion host computer; the operation interface corresponding to the onboard sensor parameter acquisition module includes the keyboard, mouse and / or display interface of the host computer corresponding to the engine electronic control unit, the host computer corresponding to the engine health monitoring unit, and the data conversion host computer; the first signal transmission extender group correspondingly includes a keyboard, mouse and / or display signal transmission extender group.

[0007] In one embodiment of the present invention, the host computer corresponding to the engine electronic control unit and the host computer corresponding to the engine health monitoring unit are used to continuously store the onboard sensor parameters; the data conversion host computer is used to convert and send the onboard sensor parameters.

[0008] In one embodiment of the present invention, the airborne sensor parameter acquisition module and the engine throttle lever resolver are connected to corresponding interfaces of the aircraft engine via aviation cables.

[0009] In one embodiment of the present invention, the aircraft engine test remote control system also includes a first test auxiliary electrical device and a second test auxiliary sensor device; the control and communication device at the test bench includes a first test auxiliary control cabinet corresponding to the first test auxiliary electrical device; the electrical test communication device includes a second test auxiliary control cabinet corresponding to the second test auxiliary sensor device; the first test auxiliary electrical device and the second test auxiliary sensor device are respectively connected to the first test auxiliary control cabinet and the second test auxiliary control cabinet through aviation cables; the first test auxiliary control cabinet and the second test auxiliary control cabinet are connected through a network cable; the second test auxiliary control cabinet and the second network switch are connected through a network cable.

[0010] In one embodiment of the present invention, the aircraft engine test remote control system also includes an engine control cabinet; the engine control cabinet is connected to the corresponding interface of the aircraft engine through an aviation cable; the engine control cabinet is also connected to the first network switch through a network cable; the switch status signal of the engine control cabinet is transmitted to the third network switch through the second optical fiber and the third optical fiber.

[0011] In one embodiment of the present invention, the control master station is connected to the third network switch and the engine throttle lever control module via a network cable.

[0012] In one embodiment of the present invention, the engine throttle lever control module includes an engine throttle lever control console and an engine throttle lever controller; the engine throttle lever control console and the engine throttle lever controller are connected via an aviation cable; the engine throttle lever controller is connected to the engine throttle lever resolver via the first optical fiber.

[0013] In one embodiment of the present invention, the remote control device also includes a second signal transmission extender group; the first end of the second signal transmission extender group is connected to the third network switch via a network cable, and the second end of the second signal transmission extender group is connected to the host computer corresponding to the engine electronic control unit, the host computer corresponding to the engine health monitoring unit, and the keyboard, mouse and / or display corresponding to the data conversion host computer via an external connection line.

[0014] In an embodiment of the present invention, the remote control device further includes a data acquisition and storage module connected to the third network switch via a network cable.

[0015] In one embodiment of the present invention, the control master station is configured to perform the following operations: debug the engine remote communication and remote electrical control system; when the debugging is completed, test the engine according to the test spectrum of the aircraft engine test; determine whether a hazardous fault has occurred based on the sensing data fed back by the onboard sensor parameter acquisition module; when it is determined that a hazardous fault has occurred, reduce the aircraft engine speed by sending a first control signal to the engine throttle lever control module, and cut off the fuel and stop the aircraft engine by sending an engine fuel switch control signal.

[0016] In one embodiment of the present invention, the engine electronic control unit regulates and controls the operation process of the engine based on the engine throttle lever resolver signal, the engine fuel switch signal and the engine ignition / switch signal sent by the control master station and the onboard sensor sensing signal.

[0017] In one embodiment of the present invention, the remote control device also includes a fourth monitoring host computer, which is connected to the third network switch via a network cable; the fourth monitoring host computer is used to receive and analyze the sensing parameters of the first test auxiliary electrical device and the second test auxiliary sensor device.

[0018] Compared with the prior art, the present invention has the following advantages: through the application of the remote control system for aircraft engine tests, it can effectively solve the safety hazards to test personnel and equipment during aircraft engine tests, and at the same time can effectively solve the data delay caused by remote control, and achieve stable and reliable control and testing effects. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying drawings are provided to provide a further understanding of the present application. They are included in and constitute a part of the present application. The accompanying drawings illustrate embodiments of the present application and together with the description serve to explain the principles of the present application.

[0020] In the attached figure:

[0021] Figure 1 It is a schematic diagram of the composition of an aviation engine test remote control system according to an embodiment of the present application.

[0022] Figure 2 It is a schematic diagram of some components of an aero-engine test remote control system according to one embodiment of the present application.

[0023] Figure 3 It is a flow chart of the operation process of the control master station of the aircraft engine test remote control system according to one embodiment of the present application. DETAILED DESCRIPTION

[0024] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for the description of the embodiments. Obviously, the drawings described below are only some examples or embodiments of the present application. For ordinary technicians in this field, the present application can also be applied to other similar scenarios based on these drawings without creative work. Unless it is obvious from the language environment or otherwise explained, the same reference numerals in the figures represent the same structure or operation.

[0025] As shown in this application and claims, unless the context clearly indicates an exception, the words "a", "an", "an" and / or "the" do not refer to the singular and may also include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0026] Unless otherwise specifically stated, the relative arrangement of the components and steps described in these embodiments, numerical expressions and numerical values ​​do not limit the scope of the present application. Meanwhile, it should be understood that for ease of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship.

[0027] In addition, it should be noted that the use of words such as "first" and "second" to define components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above words have no special meaning and cannot be understood as limiting the scope of protection of this application. In addition, although the terms used in this application are selected from well-known and commonly used terms, some terms mentioned in the specification of this application may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this article. In addition, it is required to understand this application not only by the actual terms used, but also by the meaning implied by each term.

[0028] Flowcharts are used in this application to illustrate the operations performed according to the implementation system of this application. It should be understood that the preceding or following operations are not necessarily performed precisely in order. Instead, various steps may be processed in reverse order or simultaneously. At the same time, other operations may be added to these processes, or one or more operations may be removed from these processes.

[0029] The embodiment of the present application describes an aircraft engine test remote control system.

[0030] Figure 1 It is a schematic diagram of the composition of an aviation engine test remote control system according to an embodiment of the present application. Figure 2 This is a schematic diagram of the partial components of an aircraft engine test remote control system according to an embodiment of the present application. Figure 1and Figure 2 The aircraft engine test remote control system 100 includes a control and communication device 131 at the test bench, an electrical test communication device 132 and a remote measurement and control device 133.

[0031] In some embodiments, the control and communication device 131 at the test bench includes a first network switch 151, an airborne sensor parameter acquisition module 141, an engine throttle lever resolver 111, and a first signal transmission extender group 112. The electrical test communication device 132 includes a second network switch 152. The second network switch 152 and the first network switch 151 are connected via a second optical fiber 182.

[0032] The remote measurement and control device 133 includes a third network switch 153, a control master station 161 and an engine throttle lever control module 162. The third network switch 153 is connected to the second network switch 152 via a third optical fiber 183. The third network switch 153 is also directly connected to the first network switch 151 via a fourth optical fiber 184.

[0033] In some embodiments, the engine throttle lever control module 162 is directly connected to the engine throttle lever resolver 111 through the first optical fiber 181. The airborne sensor parameter acquisition module 141 is connected to the first network switch 151 through the network cable 194. The airborne sensor parameters (or control signal parameters) are transmitted to the third network switch 153 through the second optical fiber 182 and the third optical fiber 183. The first connection end of the first signal transmission extender group 112 is connected to the operation interface corresponding to the airborne sensor parameter acquisition module 141 through the universal serial bus connection line 193. The second connection end of the first signal transmission extender group 112 is connected to the first network switch 151 through the network cable 192. The operation interface signal corresponding to the airborne sensor parameter acquisition module 141 is transmitted to the third network switch 153 through the fourth optical fiber 184. The operation interface corresponding to the airborne sensor parameter acquisition module 141 includes, for example, a universal serial bus interface (or USB interface).

[0034] In some embodiments, the airborne sensor parameter acquisition module 141 includes a host computer 201 corresponding to the engine electronic control unit, a host computer 202 corresponding to the engine health monitoring unit, and a data conversion host computer 203 .

[0035] The operation interface corresponding to the airborne sensor parameter acquisition module 141 includes the host computer 201 corresponding to the engine electronic control unit, the host computer 202 corresponding to the engine health monitoring unit, and the keyboard, mouse and / or display interface of the data conversion host computer 203. The first signal transmission extender group 112 correspondingly includes a keyboard, mouse and / or display signal transmission extender group (also known as a KVM extender, Keyboard, Video and Mouse extender). The keyboard, mouse and display signal transmission extender can maintain signal strength, avoid or reduce signal attenuation after long-distance transmission, and maintain signal strength.

[0036] The airborne sensor parameter acquisition module 141 and the engine throttle lever resolver 111 are connected to corresponding interfaces of the aircraft engine 101 via an aviation cable 191 .

[0037] In some embodiments, the host computer 201 corresponding to the engine electronic control unit and the host computer 202 corresponding to the engine health monitoring unit are used to continuously store the airborne sensor parameters. The data conversion host computer 203 is used to convert and send the airborne sensor parameters.

[0038] In some embodiments, the aircraft engine test remote control system 100 further includes a first test auxiliary electrical device 121 and a second test auxiliary sensor device 122. The control and communication device 131 at the test bench includes a first test auxiliary control cabinet 143 corresponding to the first test auxiliary electrical device 121. The electrical test communication device 132 includes a second test auxiliary control cabinet 144 corresponding to the second test auxiliary sensor device 122.

[0039] The first test auxiliary electrical device 121 and the second test auxiliary sensor device 122 are respectively connected to the first test auxiliary control cabinet 143 and the second test auxiliary control cabinet 144 through an aviation cable 191. The first test auxiliary control cabinet 143 and the second test auxiliary control cabinet 144 are connected through a network cable 192.

[0040] The second test auxiliary control cabinet 144 is connected to the second network switch 152 via a network cable 192 .

[0041] In some embodiments, the aircraft engine test remote control system 100 further includes an engine control cabinet 142. The engine control cabinet 142 is connected to the corresponding interface of the aircraft engine 101 via an aviation cable 191. The engine control cabinet 142 is also connected to the first network switch 151 via a network cable 192. The switch state signal of the engine control cabinet 142 is transmitted to the third network switch 153 via the second optical fiber 182 and the third optical fiber 183.

[0042] In some embodiments, the control master station 161 is connected to the third network switch 153 and the engine throttle lever control module 162 via a network cable 192. The engine throttle lever control module 162 includes an engine throttle lever console 171 and an engine throttle lever controller 172. The engine throttle lever console 171 and the engine throttle lever controller 172 are connected via an aviation cable 191. The engine throttle lever controller 172 is connected to the engine throttle lever resolver 111 via a first optical fiber 181.

[0043] In some embodiments, the remote measurement and control device 133 further includes a second signal transmission extender group 175. The first end of the second signal transmission extender group 175 is connected to the third network switch 153 via a network cable 192, and the second end of the second signal transmission extender group 175 is connected to a host computer 201 corresponding to the engine electronic control unit, a host computer 202 corresponding to the engine health monitoring unit, and a keyboard 221, a mouse 223 and / or a display 222 corresponding to the data conversion host computer 203 via a universal peripheral connection line 195.

[0044] The remote measurement and control device 133 also includes a fourth monitoring host computer 174, which is connected to the third network switch 153 via a network cable 192. The fourth monitoring host computer 174 is used to receive and analyze the sensing parameters of the first test auxiliary electrical device 121 and the second test auxiliary sensor device 122. The remote measurement and control device 133 also includes a data acquisition and storage module 173, which is connected to the third network switch 153 via a network cable 192.

[0045] In some embodiments, the aviation cable includes, for example, AFPF-200 series aviation cables, and the cable may be equipped with an HTPQ wave-proof sleeve. The network cable includes, for example, a Category 6 network cable, a twisted pair shielded cable, or a four-core shielded cable. In some cases, the network cable may be matched with an RJ45 interface.

[0046] Figure 3 is a flowchart of the operation process of the control master station of the aircraft engine test remote control system according to an embodiment of the present application. Figure 3 , the control main station 161 is configured to perform the following operations: Step 301, debug the remote communication and remote electrical control system of the engine. Step 302, after the debugging is completed, test the engine according to the test spectrum of the aircraft engine test. Step 303, determine whether a hazardous fault occurs based on the sensing data fed back by the onboard sensor parameter acquisition module 141. Step 304, when it is determined that a hazardous fault occurs, the speed of the aircraft engine 101 is reduced by sending a first control signal to the engine throttle lever control module 162, and the aircraft engine 101 is cut off from fuel and stopped by sending an engine fuel switch control signal (or called a fuel cut signal).

[0047] The test spectrum of aircraft engine testing includes, for example, different regulation methods, control laws and control modes for engine operation.

[0048] In some embodiments, the engine electronic control unit (EEC) adjusts and controls the operation of the engine according to different control laws and control modes based on the engine throttle lever resolver 111 signal, the engine fuel switch signal and the engine ignition / switch signal sent by the control main station 161, and the onboard sensor sensing signal. The control mode includes, for example, a low-speed operation state, a high-speed operation state, etc. The required fuel flow rate and the distribution and classification requirements of the fuel in the combustion chamber and different nozzles, as well as the control target value of the actuating component are obtained according to different adjustment methods, control laws and control modes of the engine operation.

[0049] The Engine Monitor Unit (EMU) is used to collect, record and process data generated during the operation of the aircraft engine, such as during flight or ground testing, to assist in engine design, manufacturing, safe use and maintenance. The engine electronic control unit and the engine health monitoring unit are both installed on the engine.

[0050] The aviation engine test remote control system of the present application can effectively solve the safety hazards posed to test personnel and equipment during aviation engine testing through the installation and application of control and communication devices, electrical test communication devices and remote measurement and control devices at the test bench. At the same time, it can effectively solve the data delay caused by remote control and improve the efficiency of calibration and inspection of various sensor devices before engine testing, thereby achieving stable and reliable control and testing effects.

[0051] The basic concepts have been described above. Obviously, for those skilled in the art, the above invention disclosure is only used as an example and does not constitute a limitation of the present application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements and amendments to the present application. Such modifications, improvements and amendments are suggested in the present application, so such modifications, improvements and amendments still belong to the spirit and scope of the exemplary embodiments of the present application.

[0052] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0053] Some aspects of the present application can be performed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The above hardware or software can all be referred to as "data blocks", "modules", "engines", "units", "components" or "systems". The processor can be one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or combinations thereof. In addition, various aspects of the present application may be expressed as a computer product located in one or more computer-readable media, which includes computer-readable program code.

[0054] Similarly, it should be noted that in order to simplify the description of the disclosure of this application and thus help understand one or more embodiments of the invention, in the above description of the embodiments of this application, multiple features are sometimes combined into one embodiment, figure or description thereof. However, this disclosure method does not mean that the features required by the object of this application are more than the features mentioned in the claims. In fact, the features of the embodiments are less than all the features of the single embodiment disclosed above.

[0055] Although the present application has been described with reference to the current specific embodiments, ordinary technicians in this technical field should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or substitutions may be made without departing from the spirit of the present application. Therefore, as long as the changes and modifications to the above embodiments are within the essential spirit of the present application, they will fall within the scope of the claims of the present application.

Claims

1. An aircraft engine test remote control system, comprising: A control and communication device at the test bench, including a first network switch, an airborne sensor parameter acquisition module, an engine throttle lever resolver and a first signal transmission extender group; The electrical test communication device comprises a second network switch; the second network switch and the first network switch are connected via a second optical fiber; The remote measurement and control device comprises a third network switch, a control master station and an engine throttle lever control module; the third network switch is connected to the second network switch via a third optical fiber; the third network switch is also directly connected to the first network switch via a fourth optical fiber; Among them, the engine throttle lever control module is directly connected to the engine throttle lever resolver through a first optical fiber; the airborne sensor parameter acquisition module is connected to the first network switch through a network cable; the airborne sensor parameters are transmitted to the third network switch through a second optical fiber and a third optical fiber; the first connection end of the first signal transmission extender group is connected to the operation interface corresponding to the airborne sensor parameter acquisition module through a universal serial bus connection line; the second connection end of the first signal transmission extender group is connected to the first network switch through a network cable; the operation interface signal corresponding to the airborne sensor parameter acquisition module is transmitted to the third network switch through a fourth optical fiber.

2. The aircraft engine test remote control system according to claim 1, characterized in that: The airborne sensor parameter acquisition module includes a host computer corresponding to the engine electronic control unit, a host computer corresponding to the engine health monitoring unit, and a data conversion host computer; The operation interface corresponding to the onboard sensor parameter acquisition module includes the keyboard, mouse and / or display interface of the host computer corresponding to the engine electronic control unit, the host computer corresponding to the engine health monitoring unit and the data conversion host computer; the first signal transmission extender group correspondingly includes a keyboard, mouse and / or display signal transmission extender group.

3. The aircraft engine test remote control system according to claim 2, characterized in that: The host computer corresponding to the engine electronic control unit and the host computer corresponding to the engine health monitoring unit are used to continuously store the airborne sensor parameters; the data conversion host computer is used to convert and send the airborne sensor parameters.

4. The aircraft engine test remote control system according to claim 1, characterized in that: The airborne sensor parameter acquisition module and the engine throttle lever resolver are connected to corresponding interfaces of the aircraft engine via aviation cables.

5. The aircraft engine test remote control system according to claim 1, characterized in that: Also includes a first test auxiliary electrical device and a second test auxiliary sensor device; The control and communication device at the test bench includes a first test auxiliary control cabinet corresponding to the first test auxiliary electrical device; the electrical test communication device includes a second test auxiliary control cabinet corresponding to the second test auxiliary sensor device; The first test auxiliary electrical device and the second test auxiliary sensing device are respectively connected to the first test auxiliary control cabinet and the second test auxiliary control cabinet through aviation cables; the first test auxiliary control cabinet and the second test auxiliary control cabinet are connected through a network cable; the second test auxiliary control cabinet and the second network switch are connected through a network cable.

6. The aircraft engine test remote control system according to claim 1, characterized in that: It also includes an engine control cabinet; the engine control cabinet is connected to the corresponding interface of the aircraft engine through an aviation cable; the engine control cabinet is also connected to the first network switch through a network cable; The switch status signal of the engine control cabinet is transmitted to the third network switch through the second optical fiber and the third optical fiber.

7. The aircraft engine test remote control system according to claim 1, characterized in that: The control master station is connected to the third network switch and the engine throttle lever control module via a network cable.

8. The aircraft engine test remote control system according to claim 1, characterized in that: The engine throttle lever control module includes an engine throttle lever control console and an engine throttle lever controller; The engine throttle lever control console and the engine throttle lever controller are connected via an aviation cable; the engine throttle lever controller is connected to the engine throttle lever resolver via the first optical fiber.

9. The aircraft engine test remote control system according to claim 2, characterized in that: The remote control device also includes a second signal transmission extender group; The first end of the second signal transmission extender group is connected to the third network switch via a network cable, and the second end of the second signal transmission extender group is connected to the host computer corresponding to the engine electronic control unit, the host computer corresponding to the engine health monitoring unit, and the keyboard, mouse and / or display corresponding to the data conversion host computer via a peripheral connection line.

10. The aircraft engine test remote control system according to claim 1, characterized in that: The remote control device also includes a data acquisition and storage module, which is connected to the third network switch via a network cable.

11. The aircraft engine test remote control system according to claim 1, characterized in that: The control master station is configured to perform the following operations: Debug the engine remote communication and remote electrical control systems; When debugging is completed, the engine is tested according to the test spectrum of aircraft engine testing; Determining whether a hazardous fault occurs based on the sensing data fed back by the airborne sensor parameter acquisition module; When it is determined that a hazardous fault occurs, a first control signal is sent to the engine throttle lever control module to reduce the aircraft engine speed, and an engine fuel switch control signal is sent to cut off the fuel of the aircraft engine and stop the aircraft engine.

12. The aircraft engine test remote control system according to claim 2, characterized in that: The engine electronic control unit regulates and controls the operation process of the engine based on the engine throttle lever resolver signal, the engine fuel switch signal and the engine ignition / switch signal sent by the control master station and the onboard sensor sensing signal.

13. The aircraft engine test remote control system according to claim 5, characterized in that: The remote control device also includes a fourth monitoring host computer, which is connected to the third network switch via a network cable; the fourth monitoring host computer is used to receive and analyze the sensing parameters of the first test auxiliary electrical device and the second test auxiliary sensor device.

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