Aero-engine test remote control system

Abstract

The application 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 is connected with the first network switch 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 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 resolver through a first optical fiber; the airborne sensor parameter acquisition module is connected with the first network switch through a network cable; airborne sensor parameters are transmitted to the third network switch through the second optical fiber and the third optical fiber.

Description

Technical Field

[0001] This invention relates primarily to the field of aero-engines, and more particularly to a remote control system for aero-engine testing. Background Technology

[0002] Aero engines are the core power source of aircraft, and they are highly complex aerodynamic and thermodynamic rotating machines. Aero engines have numerous components, many of which operate under conditions of high temperature, high pressure, high speed rotation, strong vibration, and complex and variable environments. They must frequently endure high loads and thermal shocks, making their working environment extremely harsh.

[0003] The design and manufacture of aero-engines require numerous tests of various types, including core engine, complete engine, high-altitude test, and open-air test. Test personnel must closely monitor all engine parameters during these tests. However, test control rooms are typically located close to the test engine, sometimes separated only by a wall. If an engine catches fire or experiences a non-containment failure, it poses an extremely high safety risk to test personnel and related testing equipment. Non-containment failures include, for example, blade breakage or casing damage. Therefore, providing a remote control system for aero-engine testing is a crucial issue that needs to be addressed. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a remote control system for aero-engine testing, so as to realize the safe and efficient conduct of aero-engine testing.

[0005] To address the aforementioned technical problems, this invention provides a remote control system for aero-engine testing, comprising: a test bench control and communication device, including a first network switch, an airborne sensor parameter acquisition module, an engine throttle lever solver, and a first signal transmission extender group; an electrical test communication device, including a second network switch; the second network switch and the first network switch are connected via a second optical fiber; a remote measurement and control device, including 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 via a third optical fiber; the third network switch is also directly connected to the first network switch via a fourth optical fiber. The engine throttle control module and the engine throttle solver are directly connected via a first optical fiber; the airborne sensor parameter acquisition module is connected to the first network switch via a network cable; the airborne sensor parameters are transmitted to the third network switch via a second and a third optical fiber; the first connection end of the first signal transmission extender group is connected to the corresponding operation interface of the airborne sensor parameter acquisition module via a universal serial bus connection line; the second connection end of the first signal transmission extender group is connected to the first network switch via a network cable; and the operation interface signal corresponding to the airborne sensor parameter acquisition module is transmitted to the third network switch via a fourth optical fiber.

[0006] In one embodiment of the present invention, 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 airborne sensor parameter acquisition module includes a 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 airborne sensor parameters; the data conversion host computer is used to convert and send the airborne sensor parameters.

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

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

[0010] In one embodiment of the present invention, the remote control system for aero-engine testing further includes an engine control cabinet; the engine control cabinet is connected to the corresponding interface of the aero-engine via an aviation cable; the engine control cabinet is also connected to the first network switch via a network cable; the switch status signal of the engine control cabinet is transmitted to the third network switch via 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 control module via a network cable.

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

[0013] In one embodiment of the present invention, the remote control device further 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 peripheral connection cables.

[0014] In one embodiment of the present invention, the remote control device further includes a data acquisition and storage module, which is 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; after debugging, test the engine according to the test spectrum of the aero-engine test; determine whether a hazardous fault has occurred based on the sensing data fed back by the airborne sensor parameter acquisition module; when a hazardous fault is determined to have occurred, reduce the speed of the aero-engine by sending a first control signal to the engine throttle control module, and shut down the aero-engine by sending an engine fuel switch control signal.

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

[0017] In one embodiment of the present invention, the remote control device further 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 sensing device.

[0018] Compared with the prior art, the present invention has the following advantages: by applying the remote control system for aero-engine testing, the safety hazards to test personnel and equipment during aero-engine testing can be effectively solved, and the data delay caused by remote control can be effectively solved, so as to achieve stable and reliable control and testing results. Attached Figure Description

[0019] The accompanying drawings are included to provide a further understanding of this application and form part of this application. The drawings illustrate embodiments of this application and, together with this specification, serve to explain the principles of this application.

[0020] In the attached image:

[0021] Figure 1 This is a schematic diagram of the composition of an aircraft engine test remote control system according to an embodiment of this application.

[0022] Figure 2 This is a schematic diagram of part of the components of an aircraft engine test remote control system according to an embodiment of this application.

[0023] Figure 3 This is a flowchart illustrating the operation process of the control master station of an aero-engine test remote control system according to an embodiment of this application. Detailed Implementation

[0024] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are merely some examples or embodiments of this application. For those skilled in the art, these drawings can be applied to other similar scenarios without creative effort. Unless obvious from the context or otherwise specified, the same reference numerals in the drawings represent the same structures or operations.

[0025] As indicated in this application and claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not specifically singular and may include plural forms. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0026] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of this application. It should also be understood that, for ease of description, the dimensions of the various parts shown in the accompanying drawings are not drawn to actual scale.

[0027] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, these terms have no special meaning and therefore should not be construed as limiting the scope of protection of this application. In addition, although the terminology used in this application is selected from commonly known and used terms, some terms mentioned in this application's specification may have been chosen by the applicant according to his or her judgment, and their detailed meanings are explained in the relevant sections of this description. Moreover, this application should be understood not only through the actual terms used, but also through the meaning implied by each term.

[0028] This application uses flowcharts to illustrate the operations performed by the system implemented according to this application. It should be understood that the preceding or following operations are not necessarily performed precisely in sequence. Instead, various steps can be processed in reverse order or simultaneously. Furthermore, other operations may be added to these processes, or one or more steps may be removed from these processes.

[0029] The embodiments of this application describe a remote control system for aircraft engine testing.

[0030] Figure 1 This is a schematic diagram of the composition of an aircraft engine test remote control system according to an embodiment of this application. Figure 2 This is a schematic diagram of some components of a remote control system for aircraft engine testing according to an embodiment of this application. (Reference) Figure 1and Figure 2 The aircraft engine test remote control system 100 includes a test bench control and communication device 131, an electrical test and communication device 132, and a remote measurement and control device 133.

[0031] In some embodiments, the test bench control and communication device 131 includes a first network switch 151, an airborne sensor parameter acquisition module 141, an engine throttle lever solver 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 monitoring and control device 133 includes a third network switch 153, a control master station 161, and an engine throttle 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 control module 162 and the engine throttle solver 111 are directly connected via a first optical fiber 181. The airborne sensor parameter acquisition module 141 is connected to a first network switch 151 via a network cable 194. Airborne sensor parameters (or control signal parameters) are transmitted to a third network switch 153 via a second optical fiber 182 and a third optical fiber 183. The first connection end of the first signal transmission extender group 112 is connected to the corresponding operation interface of the airborne sensor parameter acquisition module 141 via a universal serial bus connection cable 193. The second connection end of the first signal transmission extender group 112 is connected to the first network switch 151 via a network cable 192. The operation interface signal corresponding to the airborne sensor parameter acquisition module 141 is transmitted to the third network switch 153 via a 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 operating interfaces corresponding to the airborne sensor parameter acquisition module 141 include keyboard, mouse, and / or monitor interfaces for the host computer 201 corresponding to the engine electronic control unit, the host computer 202 corresponding to the engine health monitoring unit, and the data conversion host computer 203. The first signal transmission extender group 112 correspondingly includes a keyboard, mouse, and / or monitor signal transmission extender group (also known as a KVM extender, Keyboard, Video, and Mouse extender). The keyboard, mouse, and monitor 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 solver 111 are connected to the corresponding interface of the aircraft engine 101 via 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 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 sensing device 122. The test bench control and communication device 131 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 sensing device 122.

[0039] The first test auxiliary electrical device 121 and the second test auxiliary sensing device 122 are respectively connected to the first test auxiliary control cabinet 143 and the second test auxiliary control cabinet 144 via aviation cables 191. The first test auxiliary control cabinet 143 and the second test auxiliary control cabinet 144 are connected via network cables 192.

[0040] The second test auxiliary control cabinet 144 is connected to the second network switch 152 via 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 a first network switch 151 via a network cable 192. The on / off status signals of the engine control cabinet 142 are transmitted to the third network switch 153 via a second optical fiber 182 and a 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 control module 162 via a network cable 192. The engine throttle control module 162 includes an engine throttle console 171 and an engine throttle controller 172. The engine throttle console 171 and the engine throttle controller 172 are connected via an aviation cable 191. The engine throttle controller 172 is connected to the engine throttle solver 111 via a first optical fiber 181.

[0043] In some embodiments, the remote monitoring 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 the keyboard 221, mouse 223, and / or monitor 222 corresponding to the host computer 201 corresponding to the engine electronic control unit, the host computer 202 corresponding to the engine health monitoring unit, and the data conversion host computer 203 via a universal peripheral connection cable 195.

[0044] The remote monitoring 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 sensing device 122. The remote monitoring 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, aviation cables include, for example, AFPF-200 series aviation cables, and the cable exterior may also be fitted with an HTPQ anti-surge sleeve. Network cables include, for example, Cat6e cables, twisted-pair shielded cables, or four-core shielded cables, and in some cases, network cables may be compatible with RJ45 interfaces.

[0046] Figure 3 This is a flowchart illustrating the operation of the control master station of an aircraft engine test remote control system according to an embodiment of this application. In some embodiments, refer to... Figure 3 The control master station 161 is configured to perform the following operations: Step 301, debug the engine remote communication and remote electrical control system. Step 302, after debugging, test the engine according to the test spectrum of the aero-engine test. Step 303, determine whether a hazardous fault has occurred based on the sensing data fed back by the airborne sensor parameter acquisition module 141. Step 304, when a hazardous fault is determined to have occurred, reduce the speed of the aero-engine 101 by sending a first control signal to the engine throttle control module 162, and shut down the aero-engine 101 by sending an engine fuel switch control signal (or fuel cut-off signal).

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

[0048] In some embodiments, the Electronic Engine Control Unit (EEC) adjusts and controls the engine operation based on signals from the engine throttle lever resolver 111, engine fuel switch signals and engine ignition / switching signals from the control master station 161, and signals sensed by onboard sensors, according to different control laws and control modes. Control modes include, for example, low-speed operation and high-speed operation. Different adjustment methods, control laws, and control modes for engine operation result in the required fuel flow rate and fuel distribution grading requirements in the combustion chamber and at different nozzles, as well as the target control values ​​for the actuating components.

[0049] The Engine Monitor Unit (EMU) is used to collect, record, and process data generated during the operation of an aircraft engine, such as during flight or ground testing, to assist in engine design, manufacturing, safe use, and maintenance. Both the Engine Electronic Control Unit (ECU) and the Engine Monitor Unit are typically mounted on the engine itself.

[0050] The remote control system for aero-engine testing disclosed in this application, through the setup and application of control and communication devices at the test bench, electrical test and communication devices, and remote measurement and control devices, can effectively solve the safety hazards to test personnel and equipment during aero-engine testing. It can also effectively solve the data delay caused by remote control and improve the efficiency of calibration and inspection of various sensors before engine testing, thereby achieving stable and reliable control and testing results.

[0051] The basic concepts have been described above. Obviously, for those skilled in the art, the above disclosure is merely illustrative and does not constitute a limitation of this application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are suggested in this application, and therefore remain within the spirit and scope of the exemplary embodiments of this application.

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

[0053] Some aspects of this application may be executed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The aforementioned hardware or software may be referred to as a "data block," "module," "engine," "unit," "component," or "system." The processor may 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. Furthermore, aspects of this application may be manifested as a computer product located on one or more computer-readable media, including computer-readable program code.

[0054] Similarly, it should be noted that, in order to simplify the description of the present application and thus aid in the understanding of one or more embodiments of the invention, the foregoing description of the embodiments of the present application sometimes combines multiple features into a single embodiment, drawing, or description thereof. However, this disclosure method does not imply that the subject matter of the application requires more features than those mentioned in the claims. In fact, the embodiments contain fewer features than all the features of the single embodiments disclosed above.

[0055] Although this application has been described with reference to specific embodiments, those skilled in the art should recognize that the above embodiments are only used to illustrate this application, and various equivalent changes or substitutions can be made without departing from the spirit of this application. Therefore, any changes or modifications to the above embodiments within the essential spirit of this application will fall within the scope of the claims of this application.

Claims

1. A remote control system for aircraft engine testing, comprising: The control and communication device at the test bench includes a first network switch, an airborne sensor parameter acquisition module, an engine throttle lever solver, and a first signal transmission extender group; An electrical testing and communication device includes a second network switch; the second network switch and the first network switch are connected via a second optical fiber. The remote monitoring and control device includes 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. The engine throttle control module and the engine throttle solver are directly connected via a first optical fiber; the airborne sensor parameter acquisition module is connected to the first network switch via a network cable; the airborne sensor parameters are transmitted to the third network switch via a second and a third optical fiber; the first connection end of the first signal transmission extender group is connected to the corresponding operation interface of the airborne sensor parameter acquisition module via a universal serial bus connection line; the second connection end of the first signal transmission extender group is connected to the first network switch via a network cable; and the operation interface signal corresponding to the airborne sensor parameter acquisition module is transmitted to the third network switch via a fourth optical fiber. 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 host computers corresponding to the engine electronic control unit and the engine health monitoring unit are used to continuously store airborne sensor parameters; the data conversion host computer is used to convert and send the airborne sensor parameters.

2. The remote control system for aero-engine testing according to claim 1, characterized in that, The operation interface corresponding to the airborne sensor parameter acquisition module includes 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 interface of the data conversion host computer; the first signal transmission extender group correspondingly includes the keyboard, mouse, and / or display signal transmission extender group.

3. The remote control system for aero-engine testing according to claim 1, characterized in that, The airborne sensor parameter acquisition module and the engine throttle lever solver are connected to the corresponding interface of the aircraft engine via aviation cables.

4. The remote control system for aero-engine testing according to claim 1, characterized in that, It also includes a first test auxiliary electrical device and a second test auxiliary sensing 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 sensing 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 via aviation cables; the first test auxiliary control cabinet and the second test auxiliary control cabinet are connected via network cables; the second test auxiliary control cabinet is connected to the second network switch via network cables.

5. The remote control system for aero-engine testing 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 via an aviation cable; the engine control cabinet is also connected to the first network switch via a network cable; The on / off status signal of the engine control cabinet is transmitted to the third network switch via the second and third optical fibers.

6. The remote control system for aero-engine testing according to claim 1, characterized in that, The control master station is connected to the third network switch and the engine throttle control module via a network cable.

7. The remote control system for aero-engine testing according to claim 1, characterized in that, The engine throttle control module includes an engine throttle control panel and an engine throttle controller. The engine throttle control panel and the engine throttle controller are connected by an aviation cable; the engine throttle controller is connected to the engine throttle solver via the first optical fiber.

8. The remote control system for aero-engine testing according to claim 2, characterized in that, The remote monitoring and 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 monitor corresponding to the data conversion host computer via peripheral connection cables.

9. The remote control system for aero-engine testing according to claim 1, characterized in that, The remote monitoring and control device also includes a data acquisition and storage module, which is connected to the third network switch via a network cable.

10. The remote control system for aircraft engine testing according to claim 1, characterized in that, The control master station is configured to perform the following operations: Debugging of the engine's remote communication and remote electrical control systems; After the commissioning is completed, the engine is tested according to the test run spectrum of the aero-engine test. Based on the sensing data fed back by the airborne sensor parameter acquisition module, it is determined whether a hazardous malfunction has occurred; When a hazardous malfunction is detected, the engine speed is reduced by sending a first control signal to the engine throttle control module, and the engine fuel switch control signal is sent to shut down the engine by cutting off fuel.

11. The remote control system for aircraft engine testing according to claim 2, characterized in that, The engine electronic control unit adjusts and controls the engine operation process based on the engine throttle lever resolver signal, the engine fuel switch signal and engine ignition / switch signal issued by the control master station, and the sensing signals from the airborne sensors.

12. The remote control system for aircraft engine testing according to claim 4, characterized in that, The remote monitoring and 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 sensing device.

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