Analog control platform and system for aviation turboshaft engine

Abstract

The application provides an aviation turboshaft engine simulation measurement and control platform and system, and belongs to the technical field of aviation engines, and specifically comprises a total distance control module, which is used for taking the state of a total distance lever as a target value, controlling the power of an electric eddy current brake by adopting a closed loop control method, and sending the signal of the total distance lever to an ECU; a throttle control module, which is used for controlling the state of a throttle and sending the signal of the throttle to the ECU; an atmospheric data module, which is used for transmitting the flight height and flight speed to the ECU; an engine control module, which is used for controlling the starting, false starting and stopping of a turboshaft engine; a data monitoring module, which is used for acquiring the data of test sensors, the ECU and a torque speed sensor; and a data display module, which is used for displaying the data acquired by the data monitoring module. Through the processing scheme, the problem that the power of the electric eddy current brake cannot be automatically controlled and the problem that there is no total distance lever in the existing measurement and control platform are solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, and particularly relates to an aero-turboshaft engine simulation measurement and control platform and system. BACKGROUND

[0002] Based on a certain turboshaft engine research project, the existing turboshaft test bench has the following deficiencies: there is no total distance lever, only a throttle lever; the control parameters of the electric eddy current brake cannot be automatically controlled and adjusted; the data acquisition system, the control system and the power feedback system are independently designed and have no correlation with each other, and data cannot be synchronized. SUMMARY

[0003] Therefore, the embodiments of the present application provide an aero-turboshaft engine simulation measurement and control platform and system, which at least partially solve the problems that the existing turboshaft engine test bench lacks a total distance lever and the control parameters of the electric eddy current brake cannot be automatically adjusted.

[0004] In a first aspect, the embodiments of the present application provide an aero-turboshaft engine simulation measurement and control platform, which is used for controlling an aero-turboshaft engine test bench, the test bench comprising an electric eddy current brake, a torque and speed sensor and a turboshaft engine connected in sequence, the electric eddy current brake being used for simulating a propeller load, and the turboshaft engine being provided with an ECU and test sensors.

[0005] The simulation measurement and control platform comprises:

[0006] a total distance control module, which takes the state of the total distance lever as a target value, controls the power of the electric eddy current brake by using a closed-loop control method, and sends the signal of the total distance lever to the ECU;

[0007] a throttle control module, which controls the state of the throttle and sends the signal of the throttle to the ECU;

[0008] an atmospheric data module, which transmits the flight height and flight speed to the ECU;

[0009] an engine control module, which controls the start, false start and shutdown of the turboshaft engine;

[0010] a data monitoring module, which acquires the data of the test sensors, the ECU and the torque and speed sensor; and

[0011] a data display module, which displays the data acquired by the data monitoring module.

[0012] According to a specific implementation manner of the embodiment of the present application, the simulation test and control platform further comprises a linkage control module, which is connected with the throttle control module and linked with the total distance control module; when the throttle is opened and the total distance lever is pushed, the linkage control module calculates the corresponding throttle opening degree to control the linkage of the throttle and the total distance lever.

[0013] According to a specific implementation manner of the embodiment of the present application, the simulation test and control platform further comprises a parameter setting module, which is used for parameter setting of the linkage control module, parameter setting of the closed-loop control function of the total distance control module and parameter setting of the control function of the ECU.

[0014] According to a specific implementation manner of the embodiment of the present application, the angle design range of the total distance lever is 0°-123°, the angle of the total distance lever corresponding to the maximum power state is 120°-123°, the angle of the total distance lever corresponding to the slow vehicle power state is 27°-30°, and the angle of the total distance lever corresponding to the parking state is 0°-3°.

[0015] According to a specific implementation manner of the embodiment of the present application, the angle design range of the throttle is 0°-90°, the 0° position corresponds to the minimum control rotating speed, and the 90° position corresponds to the maximum control rotating speed.

[0016] According to a specific implementation manner of the embodiment of the present application, the simulation test and control platform further comprises a data calibration module, which is used for calibrating the data of the test sensor obtained by a multi-point calibration method.

[0017] According to a specific implementation manner of the embodiment of the present application, the simulation test and control platform further comprises an automatic data recording module, which is used for automatically recording and storing the data obtained by the data monitoring module.

[0018] In the second aspect, the embodiment of the present application further provides an aviation turboshaft engine simulation system, which comprises an aviation turboshaft engine test bench and the simulation test and control platform of the aviation turboshaft engine as described in any of the embodiments of the first aspect.

[0019] According to a specific implementation manner of the embodiment of the present application, the system further comprises a program-controlled loading power supply, a torque rotating speed power acquisition instrument and a turboshaft engine data acquisition cabinet,

[0020] The total distance control module controls the power of the eddy current brake by controlling the increase and decrease of the output current of the program-controlled loading power supply.

[0021] The torque rotating speed power acquisition instrument is connected with the torque rotating speed sensor, and the data monitoring module obtains the data of the torque rotating speed sensor through the torque rotating speed power acquisition instrument.

[0022] The turbo-shaft engine data acquisition cabinet is connected with the test sensor, and the data monitoring module acquires data of the test sensor through the turbo-shaft engine data acquisition cabinet.

[0023] According to a specific implementation manner of the embodiment of the application, the data collected by the test sensor includes exhaust temperature, engine rotating speed, engine output rotating speed, compressor outlet pressure, total inlet temperature, vibration, fuel pump outlet flow, fuel pump outlet pressure, fuel return flow, fuel return pressure, lubricating oil flow, lubricating oil pressure, lubricating oil inlet temperature, lubricating oil outlet temperature, engine output torque and engine output power.

[0024] Advantages

[0025] The aviation turbo-shaft engine simulation measurement and control platform in the embodiment of the application solves the problem of running of the simulation unmanned helicopter flight control system by arranging the total distance control module, the throttle control module, the atmospheric data module, the engine control module, the data monitoring module and the data display module, solves the data fusion problem of the data acquisition system, the control system and the power feedback system, and solves the problem of automatic control of the power of the electric eddy current brake and the problem of no total distance lever. BRIEF DESCRIPTION OF DRAWINGS

[0026] In order to more clearly illustrate the technical solutions of the embodiments of the application, the following will briefly introduce the drawings needed to be used in the embodiments. Obviously, the drawings in the following description are only some embodiments of the application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.

[0027] Figure 1 It is a structural diagram of the aviation turbo-shaft engine test bed according to an embodiment of the application;

[0028] Figure 2 It is a frame diagram of the aviation turbo-shaft engine simulation measurement and control platform according to an embodiment of the application;

[0029] Figure 3 It is a frame diagram of the aviation turbo-shaft engine simulation measurement and control platform according to another embodiment of the application;

[0030] Figure 4 It is a structural diagram of the aviation turbo-shaft engine simulation system according to an embodiment of the application;

[0031] Figure 5 It is a software plan of the aviation turbo-shaft engine simulation measurement and control platform according to an embodiment of the application.

[0032] In the figure: 1, turbo-shaft engine; 2, torque and rotating speed sensor; 3, electric eddy current brake. DETAILED DESCRIPTION

[0033] The embodiments of the present application will be described below in detail with reference to the accompanying drawings.

[0034] The above and other aspects of the present application will become more apparent by describing in detail the embodiments thereof with reference to the attached drawings in which:

[0035] It is to be understood that the embodiments described herein are merely examples of embodiments of the application and that a wide variety of changes and modifications of the embodiments described herein can be made by those skilled in the art without departing from the spirit and scope of the application. For example, the order in which some or all of the described operations are performed can be changed, and / or two or more operations can be performed at the same time.

[0036] It is also noted that the embodiments provided in the following description are only illustrative of the principles of the present application. Other arrangements, which are presently deemed best embodying the principles of the present application, can be made by those skilled in the art without departing from the spirit and scope of the application. Accordingly, reference should be made to the following drawings that form a part of this disclosure, wherein:

[0037] Further, in the following description, numerous specific details are provided in order to provide a thorough understanding of the examples. However, one skilled in the relevant art will recognize that the disclosure can be practiced without these specific details.

[0038] In the prior art, the patent application number 201710212766.X discloses an aviation turboshaft engine test bed, which is characterized by comprising a driving system, a control system, an engine, a support structure and a control room. The patent mainly describes the structural design scheme of the test bed, accessories and control room, and adds an engine load propeller; the control room working mode includes three modes of hot test, cold water test and simulation test. The patent does not elaborate the specific control method of hot test, cold water test and simulation test and the adjustment method of load power. To solve the above problems, the present application proposes a test bed modification scheme for simulating unmanned helicopter flight control system, atmospheric data, propeller and its control system, which can solve the problem that turboshaft engine cannot simulate actual working condition operation.

[0039] The following refers to the accompanying Figure 1 to the accompanying Figure 5 The aviation turboshaft engine simulation measurement and control platform and system of the present application are described in detail.

[0040] In the first aspect, the embodiments of the present application provide an aviation turboshaft engine simulation measurement and control platform for controlling an aviation turboshaft engine test bed. The structure of the aviation turboshaft engine test bed is shown in Figure 1 The test bed comprises an electric eddy current brake 3, a torque speed sensor 2 and a turboshaft engine 1 connected in sequence. The electric eddy current brake 3 is used to simulate the propeller load. The turboshaft engine 1 is provided with a total pitch rod, an ECU (electronic control unit of the turboshaft engine 1) and a test sensor. The ECU is used to control the turboshaft engine 1, and the test sensor is used to detect the speed, temperature and pressure parameters of the turboshaft engine 1.

[0041] The components of the simulation measurement and control platform are described in detail below, referring to Figure 2 The simulation measurement and control platform specifically comprises the following modules:

[0042] The total pitch control module is used to take the state of the total pitch rod as a target value, control the power of the electric eddy current brake 3 by closed loop control method, and send the signal of the total pitch rod to the ECU. The total pitch rod refers to the control rod for controlling the pitch of the propeller. In the present patent, the total pitch rod in the simulation measurement and control platform software is used to simulate the total pitch rod in the helicopter cockpit. The total pitch rod signal is also sent to the ECU to control the output power of the turboshaft engine 1, which is used to match the power required by the propeller. Therefore, the total pitch control module controls the power of the electric eddy current brake 3 according to the state of the total pitch rod to simulate the propeller load.

[0043] Throttle control module, for controlling the state of the throttle, and sending the throttle signal to the ECU, and then controlling the engine speed through the throttle. The throttle lever is used to control the speed of the turboshaft engine 1. As the speed of the turboshaft engine 1 increases, the output power increases. In this patent, the throttle lever in the test and control platform software is used to simulate the throttle signal in the helicopter. When the throttle lever is pushed forward, the turbine speed will increase, thereby increasing the engine output power. Conversely, when the throttle lever is pulled backward, the turbine speed will decrease, and the engine output power will also decrease. The throttle control module has two operating states: when the throttle is in the open state, the ECU is only controlled by the throttle lever; when the throttle is in the closed state, the ECU is only controlled by the total distance lever.

[0044] Atmospheric data module, for transmitting the flight height and flight speed to the ECU.

[0045] Engine control module, for controlling the start, false start and stop of the turboshaft engine 1.

[0046] Data monitoring module, for obtaining the data of the test sensor, ECU and torque speed sensor 2, specifically, reading the data through the serial port.

[0047] And the data display module, for real-time display of the data obtained by the data monitoring module.

[0048] In specific implementation, the data display module includes a data value display module and a data curve display module, the data value display module is used to display the test data value in real time, and the data curve display module is used to display the test data value as a curve.

[0049] In one embodiment, the simulation test and control platform further includes a linkage control module, referring to Figure 3 The throttle control module reserves a linkage control interface, the linkage control module is connected with the throttle control module and is linked with the total distance control module; when the throttle is in the open state and the total distance lever is in the pushing process, the corresponding throttle opening degree is calculated through the linkage control module, and the throttle and the total distance lever are linked.

[0050] In this embodiment, the simulation test and control platform has three working modes:

[0051] Working mode 1: the linkage mode of the linkage control module is in the closed state, the throttle control module controls the throttle to be in the open state, the total distance control module controls the electric eddy current brake 3, and the throttle controls the engine speed.

[0052] Working mode 2: the linkage mode of the linkage control module is in the open state, the throttle control module controls the throttle to be in the open state, the total distance control module controls the electric eddy current brake 3, the total distance control module calculates the corresponding throttle opening degree through the linkage control module, controls the throttle to act, and the throttle controls the engine speed. Description: when the linkage mode is in the open state, the throttle is automatically set to the open state.

[0053] Working mode 3: the linkage mode of the linkage control module is in the closed state, the throttle control module controls the throttle to be in the closed state, the total distance control module controls the electric eddy current brake 3 and the engine output speed.

[0054] Further, the linkage control module also has a throttle protection function.

[0055] In one embodiment, the simulation test and control platform further comprises a parameter setting module, which is used for parameter setting of the linkage control module, parameter setting of the closed loop control function of the total distance control module, and parameter setting of the control function of the ECU.

[0056] In specific implementation, the total distance lever signal is sent to the electronic control unit (ECU) of the turboshaft engine 1 through a serial port, the angle of the total distance lever is designed to be 0°-123°, the angle of the total distance lever corresponding to the maximum power state is 120°-123°, the angle of the total distance lever corresponding to the slow vehicle power state is 27°-30°, and the angle of the total distance lever corresponding to the parking state is 0°-3°. The angle of each state domain is 3°±0.25°.

[0057] In specific implementation, the throttle control module has two operating states, when the throttle is in the open state, the ECU is controlled only by the throttle lever, and when the throttle is in the closed state, the ECU is controlled only by the total distance lever. When the throttle is in the open state, the throttle signal is sent to the ECU through a serial port to control the engine speed, and the angle of the throttle is designed to be 0°-90°, 0° position corresponding to the minimum control speed, and 90° position corresponding to the maximum control speed.

[0058] In one embodiment, the simulation test and control platform further comprises a data calibration module, which is used for calibrating the obtained data of the turboshaft engine 1 through a multi-point calibration method, so as to realize more accurate test data.

[0059] In one embodiment, the simulation test and control platform further comprises an automatic data recording module for automatically recording and storing the data obtained by the data monitoring module, including the data of the test sensor, the ECU and the torque speed sensor 2. Specifically, the data collected by the test sensor includes exhaust temperature, engine speed, engine output speed, compressor outlet pressure, intake total temperature, vibration, fuel pump outlet flow, fuel pump outlet pressure, fuel return flow, fuel return pressure, lubricating oil flow, lubricating oil pressure, lubricating oil inlet temperature, lubricating oil outlet temperature, engine output torque, engine output power, etc.

[0060] The simulation test and control platform of the aero turboshaft engine in the above embodiment solves the problem of simulating the operation of the unmanned helicopter flight control system, solves the data fusion problem of the data acquisition system, the control system and the power feedback system, and at the same time solves the problem of automatic control of the power of the electric eddy current brake 3 and the problem of no total distance lever.

[0061] In a second aspect, the embodiments of the present application also provide an aero turboshaft engine simulation system, referring to Figure 4 , comprising an aero turboshaft engine test bench and an aero turboshaft engine simulation test and control platform according to any one of the above first aspect, the aero turboshaft engine simulation test and control platform is used for controlling the aero turboshaft engine test bench, the test bench comprises an electric eddy current brake 3, a torque speed sensor 2 and a turboshaft engine 1 connected in sequence, the electric eddy current brake 3 is used for simulating the propeller load, and the turboshaft engine 1 is provided with an ECU and a test sensor.

[0062] In one embodiment, the system further comprises a program-controlled loading power supply, a torque speed power acquisition instrument and a turboshaft engine data acquisition cabinet, referring to Figure 4 , the total distance control module controls the power of the electric eddy current brake 3 by controlling the increase and decrease of the output current of the program-controlled loading power supply; the torque speed power acquisition instrument is connected with the torque speed sensor 2, and the data monitoring module obtains the data of the torque speed sensor 2 through the torque speed power acquisition instrument; the turboshaft engine data acquisition cabinet is connected with the test sensor, and the data monitoring module obtains the data of the test sensor through the turboshaft engine data acquisition cabinet.

[0063] The program-controlled loading power supply, the torque speed power acquisition instrument and the turboshaft engine data acquisition cabinet are in communication connection with the serial port gateway, and are connected with the simulation test and control platform through the industrial computer for data transmission. The program-controlled loading power supply, the torque speed power acquisition instrument, the turboshaft engine data acquisition cabinet, the serial port gateway, the industrial computer and the simulation test and control platform constitute an operation table, which is operated by a test personnel to control the aero turboshaft engine test bench to perform a test.

[0064] In the embodiment, the aviation turboshaft engine simulation system has four working paths, which are as follows:

[0065] Working path 1: the simulation control platform (control software) controls the power increase and decrease of the electric eddy current brake 3 by controlling the current increase and decrease of the program-controlled power supply through the gateway.

[0066] Working path 2: the torque and speed sensor 2 measures the speed, torque and power data through the torque and speed power acquisition instrument, and the speed, torque and power data are transmitted to the simulation control platform for reading, display and recording through the gateway.

[0067] Working path 3: the test sensors of the aviation turboshaft engine test bench, such as vibration, fuel flow, fuel pressure, oil flow, oil pressure, oil temperature and the like, measure the data through the turboshaft engine data acquisition cabinet. The above data are transmitted to the simulation control platform for reading, display and recording through the gateway.

[0068] Working path 4: the ECU interacts with the simulation control platform through the gateway.

[0069] In specific implementation, the data collected by the test sensors include exhaust temperature, engine speed, engine output speed, compressor outlet pressure, total inlet air temperature, vibration, fuel pump outlet flow, fuel pump outlet pressure, fuel return flow, fuel return pressure, oil flow, oil pressure, oil inlet temperature, oil outlet temperature, engine output torque and engine output power.

[0070] The software main interface of the turboshaft engine comprehensive simulation control platform is shown in Figure 5 From left to right, they are a data curve display area, a data value display area and a turboshaft engine control area. The functions of the data value display area include real-time display of exhaust temperature, engine speed, engine output speed, compressor outlet pressure, total inlet air temperature, vibration, fuel pump outlet flow, fuel pump outlet pressure, fuel return flow, fuel return pressure, oil flow, oil pressure, oil inlet temperature, oil outlet temperature, engine output torque and engine output power. The functions of the turboshaft engine control area include parameter, flight height, flight speed, total distance lever angle display, throttle lever angle display, total distance lever, throttle, starting, stopping, linkage switch and throttle switch.

[0071] The software of the turboshaft engine comprehensive simulation control platform is developed by using VC++ language, and is developed in a modular manner and designed in a layered architecture.

[0072] The aviation turboshaft engine simulation system provided by the application can simulate the system environment composed of the unmanned helicopter flight control system, atmospheric data, propeller and control system, and solves the problem that the turboshaft engine cannot simulate actual working conditions.

[0073] The above description is only specific embodiments of the present application, but the protection scope of the present application is not limited thereto, any changes or replacements within the technical scope disclosed by the present application can be easily thought by those skilled in the art, and should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An aero turboshaft engine simulation test control platform for controlling an aero turboshaft engine test bench, characterized in that, The test bench comprises an electric eddy current brake (3), a torque speed sensor (2) and a turboshaft engine (1) connected in sequence, the electric eddy current brake (3) is used for simulating propeller load, and the turboshaft engine (1) is provided with an ECU and test sensors; The simulation measurement and control platform comprises: A total distance control module, which takes the state of the total distance lever as a target value, controls the power of the electric eddy current brake (3) by adopting a closed loop control method, and sends the signal of the total distance lever to the ECU; An oil control module, which controls the state of the oil and sends the signal of the oil to the ECU; An atmospheric data module, which transmits the flight height and flight speed to the ECU; An engine control module, which controls the start, false start and stop of the turboshaft engine (1); A data monitoring module, which acquires the data of the test sensors, the ECU and the torque speed sensor (2); and A data display module, which displays the data acquired by the data monitoring module; The simulation measurement and control platform further comprises a linkage control module, which is connected with the oil control module and linked with the total distance control module; when the oil is in the open state and the total distance lever is in the pushing process, the corresponding oil opening degree is calculated through the linkage control module to control the linkage of the oil and the total distance lever; The simulation measurement and control platform has three working modes: Working mode 1: the linkage mode of the linkage control module is in the closed state, the oil control module controls the oil to be in the open state, the total distance control module controls the electric eddy current brake (3), and the oil controls the engine speed; working mode 2: the linkage mode of the linkage control module is in the open state, the oil control module controls the oil to be in the open state, the total distance control module controls the electric eddy current brake (3), the total distance control module calculates the corresponding oil opening degree through the linkage control module to control the action of the oil, the oil controls the engine speed, and the linkage mode is automatically set to the open state when the linkage mode is in the open state; working mode 3: the linkage mode of the linkage control module is in the closed state, the oil control module controls the oil to be in the closed state, the total distance control module controls the electric eddy current brake (3) and the engine output speed.

2. The simulation and control platform for aero turboshaft engines according to claim 1, characterized in that, The simulation measurement and control platform further comprises a parameter setting module, which is used for parameter setting of the linkage control module, parameter setting of the closed loop control function of the total distance control module and parameter setting of the control function of the ECU.

3. The simulation and control platform for aero turboshaft engines according to claim 1, characterized in that, The angle design range of the total distance lever is 0°-123°, the angle of the total distance lever corresponding to the maximum power state is 120°-123°, the angle of the total distance lever corresponding to the slow vehicle power state is 27°-30°, and the angle of the total distance lever corresponding to the parking state is 0°-3°.

4. The simulation and control platform for aero turboshaft engines according to claim 1, characterized in that, The angle design range of the oil is 0°-90°, and the 0° position corresponds to the minimum control speed and the 90° position corresponds to the maximum control speed.

5. The simulation and control platform for aero turboshaft engines according to claim 1, characterized in that, The simulation measurement and control platform further comprises a data calibration module, which is used for calibrating the data of the test sensors by a multi-point calibration method.

6. The simulation and control platform for aero turboshaft engines according to claim 1, characterized in that, The simulation test and control platform further comprises an automatic data recording module for automatically recording and storing the data obtained by the data monitoring module.

7. An aviation turboshaft engine simulation system, characterized by, The simulation test and control platform of the aviation turboshaft engine according to any one of claims 1-6.

8. The aerospace turboshaft engine simulation system of claim 7, wherein, The system further comprises a program-controlled loading power source, a torque speed power acquisition instrument and a turboshaft engine data acquisition cabinet, The total distance control module controls the power of the eddy current brake (3) by controlling the increase and decrease of the output current of the program-controlled loading power source; The torque speed power acquisition instrument is connected with the torque speed sensor (2), and the data monitoring module obtains the data of the torque speed sensor (2) through the torque speed power acquisition instrument; The turboshaft engine data acquisition cabinet is connected with the test sensor, and the data monitoring module obtains the data of the test sensor through the turboshaft engine data acquisition cabinet.

9. The aerospace turboshaft engine simulation system of claim 7, wherein, The data collected by the test sensor includes exhaust temperature, engine speed, engine output speed, compressor outlet pressure, inlet total temperature, vibration, fuel pump outlet flow, fuel pump outlet pressure, fuel return flow, fuel return pressure, oil flow, oil pressure, oil inlet temperature, oil outlet temperature, engine output torque and engine output power.

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