CN104765281A - Simulated interface adapter of aircraft engine control system - Google Patents
Simulated interface adapter of aircraft engine control system Download PDFInfo
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- CN104765281A CN104765281A CN201510164943.2A CN201510164943A CN104765281A CN 104765281 A CN104765281 A CN 104765281A CN 201510164943 A CN201510164943 A CN 201510164943A CN 104765281 A CN104765281 A CN 104765281A
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Abstract
The invention discloses a simulated interface adapter of an aircraft engine control system. The simulated interface adapter comprises an interface configuration management and signal monitoring module, a signal switching module, a signal wiring module, a fault injection module, a signal conditioning module and an interface control module. The interface configuration management and signal monitoring module is connected with the signal switching module, the signal wiring module, the fault injection module, the signal conditioning module and the interface control module. The signal switching module, the signal wiring module, the fault injection module, the signal conditioning module and the interface control module are sequentially connected. The signal switching module is connected with a controller of the aircraft engine control system. The interface control module is connected with an external real-time hardware platform. The open and modularized overall simulated structure is adopted for separating all the modules from one another, the real-time simulated platform of various interfaces is supported, and expansibility and maintainability are remarkably improved.
Description
Technical field
The present invention relates to Simulation of Aeroengine Control System field, particularly relate to a kind of Simulation of Aeroengine Control System interface adapter.
Background technology
Along with the progress of Aeroengine control technology, control variable constantly increases and controlling functions requirement improves constantly, and this makes the development difficulty of aeroengine control system and cycle increase.In order to reduce costs, the shortening cycle, in the development flow process of aeroengine control system, hardware becomes in loop (HIL) emulation and semi-physical simulation and carries out the extremely important of Control System Design and checking and efficient approach.The important step of carrying out HIL emulation is Simulation of Aeroengine Control System interface adapter, and carries out semi-physical simulation and will increase the physical simulation such as fuel system and power system interfacing equipment on this basis.
The purposes of Simulation of Aeroengine Control System interface establishing device comprises:
1. at the reseach of engine initial stage for verifying the General layout Plan of engine total control plan and aeroengine control system;
2. at the normal of development phase analog control system and fault-signal interface, checking and assess the steering logic of aeroengine control system, control algolithm, the BIT of EEC and fault-tolerant ability comprehensively;
3., as a utility appliance in aeroengine control system upgrading, maintenance process, improve upgrading, maintenance efficiency.In a word, Simulation of Aeroengine Control System interface adapter is a key equipment indispensable in aeroengine control system design system, be the roll booster of aeroengine control system development process, greatly can improve development efficiency, reduce development cost and maintenance cost.
At present, the advanced technology countries such as the U.S. and Britain all have employed the emulation interface equipment of function advanced person in aeroengine control system design process, and such as GE company just adopted its aeroengine control system of such equipment development before 20 years.Through technology upgrading for many years and experience accumulation, correlation technique is comparative maturity, and most is representational is the real-time simulation platform of ADI company of the U.S., German dSPACE company, Britain ADS2 and Canadian RT-LAB.The real-time emulation system Simulator of dSPACE company of Germany is used widely in the complex embedded system exploitation of aerospace field.The compatible MATLAB/SIMULINK of dSPACE, can directly download on real-time simulation platform by generating code, its hardware platform provides the simulation hardware board of various types of signal and corresponding real-time interface software.In addition, all right config failure of dSPACE emulator injects the fault simulation that board is used for sensor and topworks and circuit thereof.ADI company of the U.S. is conceived to as the user in the fields such as automobile, nuclear power station, Aero-Space, defence and military provides real-time (semi physical) artificial product of complex control system always, its AD10, AD100 analogue system just enjoys great prestige real-time simulation field in the 1980s to the nineties, and has led the development of AD RTS system, RTX system afterwards.ADI provides brand-new emulation platform and friendly simulated environment, for carrying out quick principle prototype, the design of various embedded system and the ground integration testing of l-G simulation test and large scale system and emulation.RTX and the RTS serial emulation platform of ADI has the functional characteristics of a series of uniqueness: have the interruption board of direct fault location function, have self-inspection and self-correcting ability and can the interface panel of quick reconfiguration.
Have although domestic shutout successively introduced the real-time simulation platform of the company such as German dSPACE and U.S. ADI with extremely expensive price, but the inside realization mechanism not opening of these products, the interface emulates fidelity of part signal is undesirable, is difficult to direct use, poor effect.Therefore, be badly in need of development a kind of multi-functional, high-performance, easily extensible, easy of integration there is Simulation of Aeroengine Control System interface adapter that is open, modular system structure.
Summary of the invention
Technical matters to be solved by this invention is for defect involved in background technology, a kind of Simulation of Aeroengine Control System interface adapter is provided, solve existing equipment because interface is opaque, function imperfection and expand limited and use difficult problem that is that cause, drastically increase l-G simulation test efficiency.
The present invention is for solving the problems of the technologies described above by the following technical solutions:
Simulation of Aeroengine Control System interface adapter, comprises interface configuration management and signal monitoring module, signal converting module, signal wiring module, direct fault location module, Signal-regulated kinase and interface control module;
Described interface configuration management is connected with signal converting module, signal wiring module, direct fault location module, Signal-regulated kinase, interface control module respectively with signal monitoring module; Described signal converting module, signal wiring module, direct fault location module, Signal-regulated kinase, interface control module are connected successively; Described signal converting module is connected with the controller of aeroengine control system; Described interface control module is connected with outside Real-time hardware platform;
Described interface configuration management is used for control signal I/O, signal scaling, communication, direct fault location and Experiment Data Records with signal monitoring module and manages;
Described signal converting module is used for concentrating the sort interface providing aeroengine control system controller input/output signal;
Described signal wiring module for providing the patch panels of aeroengine control system controller input/output signal, with manual ON, disconnection, overlap joint signal path;
Described direct fault location module is for simulating and injecting the short circuit of sensor and operator signals interface, open circuit, overlap joint rigid line fault;
Described Signal-regulated kinase is used for the electric current exported from direct fault location module, pulsewidth and switching signal to nurse one's health into normal voltage that interface control module can gather, pulse and level signal, the normal voltage of interface control module output, frequency signal is changed into sensor analog signals corresponding to aeroengine control system controller simultaneously;
Described interface control module is used for normal voltage that collection signal conditioning module enters, pulse, level signal export outside Real-time hardware platform to, converts the signal of outside Real-time hardware platform feedback to outputting standard voltage simultaneously, frequency signal passes to Signal-regulated kinase.
As the further prioritization scheme of Simulation of Aeroengine Control System interface adapter of the present invention, described interface control module adopts board, and this board is based on the one in pci bus, PXI bus or vxi bus.
As the further prioritization scheme of Simulation of Aeroengine Control System interface adapter of the present invention, described interface control module adopts the CRIO module architectures based on spi bus.
As the further prioritization scheme of Simulation of Aeroengine Control System interface adapter of the present invention, described interface control module adopts independently embedded system module.
As the further prioritization scheme of Simulation of Aeroengine Control System interface adapter of the present invention, the controller of described aeroengine control system is engine electronic control.
As the further prioritization scheme of Simulation of Aeroengine Control System interface adapter of the present invention, the controller of described aeroengine control system is rapid prototyping controller.
The present invention adopts above technical scheme compared with prior art, has following technique effect:
1. the present invention adopts a kind of open, modular emulation interface outfit of equipment framework, Interface Controller, signal condition, direct fault location, signal wiring and signal converting module are separated from each other, and each unit also takes grouping, modular organization.This framework had both been applicable to the HIL l-G simulation test of controller, also the semi-physical simulation of control system is applicable to, only need " HIL/ semi physical " be selected to carry out easy configuration by short-circuit block on the panel of block, drastically increase the dirigibility of system; Due to being separated from each other of interface control module and Signal-regulated kinase, interface control module allows to adopt the board based on pci bus, PXI bus, vxi bus or the CRIO module architectures based on spi bus, even can adopt independently embedded system module, open fabulous, be convenient to upgrading.And being separated from each other of signal condition, direct fault location, signal wiring and signal converting module, make again the expanded configuration of emulation interface more flexible, working service is also convenient;
2. the present invention comprises interface emulates function, and embeds sensor and topworks's model at Real-time hardware platform, realizes the high-precision analog of engine control system medium speed signal, temperature signal and pressure signal and electro-hydraulic servo valve actuating mechanism;
3. the program of simulator of the present invention adopts multi-threaded parallel framework, and engine mockup embeds real-time platform, and real-time reaches ms level, the model running of minor loop is in fast platform, also directly can run on FPGA platform, reach Microsecond grade real-time accuracy, thus ensure that the real-time of system.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Embodiment
Below in conjunction with accompanying drawing, technical scheme of the present invention is described in further detail:
As shown in Figure 1, the invention discloses a kind of Simulation of Aeroengine Control System interface adapter, comprise interface configuration management and signal monitoring module, signal converting module, signal wiring module, direct fault location module, Signal-regulated kinase and interface control module;
Described interface configuration management is connected with signal converting module, signal wiring module, direct fault location module, Signal-regulated kinase, interface control module respectively with signal monitoring module; Described signal converting module, signal wiring module, direct fault location module, Signal-regulated kinase, interface control module are connected successively; Described signal converting module is connected with the controller of aeroengine control system; Described interface control module is connected with outside Real-time hardware platform;
Described interface configuration management is used for control signal I/O, signal scaling, communication, direct fault location and Experiment Data Records with signal monitoring module and manages;
Described signal converting module is used for concentrating the sort interface providing aeroengine control system controller input/output signal;
Described signal wiring module for providing the patch panels of aeroengine control system controller input/output signal, with manual ON, disconnection, overlap joint signal path;
Described direct fault location module is for simulating and injecting the short circuit of sensor and operator signals interface, open circuit, overlap joint rigid line fault;
Described Signal-regulated kinase is used for the electric current exported from direct fault location module, pulsewidth and switching signal to nurse one's health into normal voltage that interface control module can gather, pulse and level signal, the normal voltage of interface control module output, frequency signal is changed into sensor analog signals corresponding to aeroengine control system controller simultaneously;
Described interface control module is used for normal voltage that collection signal conditioning module enters, pulse, level signal export outside Real-time hardware platform to, converts the signal of outside Real-time hardware platform feedback to outputting standard voltage simultaneously, frequency signal passes to Signal-regulated kinase.
Described interface control module can adopt board, based on the CRIO module architectures of spi bus or independently embedded system module, when adopting board, board adopts based on the one in pci bus, PXI bus or vxi bus.
The controller of described aeroengine control system is engine electronic control or rapid prototyping controller.
In the present invention, Interface Controller, signal condition, direct fault location, to be separated from each other between signal wiring and signal converting module, and each module also takes grouping, modular organization.This framework had both been applicable to the HIL l-G simulation test of controller, was also applicable to the semi-physical simulation of control system, only need " HIL/ semi physical " be selected to carry out easy configuration by short-circuit block on the panel of block.
Compared to existing emulation interface platform, the present invention does not need special hardware platform, significantly enhances extendability and maintainability.Due to being separated from each other of interface control module and Signal-regulated kinase, interface control module allows to adopt the board based on pci bus, PXI bus, vxi bus or the CRIO module architectures based on spi bus, even can adopt independently embedded system module, open fabulous, be convenient to upgrading.And being separated from each other of signal condition, direct fault location, signal wiring and signal converting module, make again the expanded configuration of emulation interface more flexible, working service is also convenient.
The myRIO-1900 of what Real-time hardware platform herein adopted is NI company, its embedded Xilinx Zynq chip, real-time handling property and the Xilinx FPGA customizable I/O of double-core ARM Cortex-A9 can be utilized, and provide abundant peripheral I/O interface, comprise 10 road analog inputs (AI), 6 road analog outputs (AO), 40 railway digital constrained input (DIO).Aeroengine Real Time Model runs in myRIO-1900 platform, and real-time reaches ms level, and minor loop model directly runs on FPGA end, and real-time reaches Microsecond grade real-time accuracy.Meanwhile, platform embedded in pressure drag, thermal resistance, thermocouple and electro-hydraulic servo valve actuating mechanism dynamic model, and takes multi-threaded parallel framework, drastically increases the real-time of simulation system.
Interface configuration management and signal monitoring module develop according to the demand of FADEC Simulation Test and advanced Software for Design theory, the I/O of primary responsibility signal, signal scaling, communication, direct fault location and Experiment Data Records management etc. are the bridges of emulation interface adapter and engine Real time mathematical model.
The kind of aeroengine control system topworks mainly contains electrohydraulic servo valve, high-speed electromagnetic valve etc., and interface emulates is relatively simple, only need gather the width of corresponding electric current or PWM.
The sensor that aeroengine control system is commonly used comprises magnetic induction speed transducer, thermal resistance temperature sensor, thermocouple temperature sensor, piezoresistive pressure sensor, LVDT/RVDT formula displacement transducer.Signal-regulated kinase is taked " electronic synthesis ", and technology realizes the simulation of sensor signal, namely by control to electronic circuit, make its electric characteristic and actual sensor similar.
For magnetic induction speed transducer, the square wave of frequency change is produced by high speed DO, control its amplitude, low-pass filter simulation sinusoidal wave through DA successively, thus realize the electronic synthesis of the signals of rotational speed sensor that frequency and amplitude change along with rotating speed size.
For thermocouple temperature sensor, form attenuator circuit based on high-precision operational amplifier, obtain the thermocouple voltages signal of mV level.The magnitude of voltage of thermopair is converted to by temperature value based on corresponding phasing meter in model program, and considers cold junction signal compensation.
For LVDT/RVDT formula displacement transducer, using the reference of the pumping signal of LVDT/RVDT demodulator circuit as gain control circuit, the controlled alternating signal of amplitude is obtained by ride gain size, thus the characteristic that simulation LVDT/RVDT secondary side signal amplitude changes with displacement size.
For thermal resistance temperature sensor, flow through the electric current of measuring resistance by DA control circui, thus the simulation of relational implementation resistance change based on voltage, electric current and resistance three.The resistance of thermal resistance is converted to by temperature value based on corresponding phasing meter in model program.
For piezoresistive pressure sensor, first build four limit resistance bridges, one of them brachium pontis realizes the simulation of change in resistance by electronic synthesis method, thus makes electric bridge produce mV level unbalance voltage, achieves the simulation of piezoresistive pressure sensor signal.The mV value of electric bridge is converted to from force value according to Sensor's Static characteristic data in model program.
The present invention possesses automatic fault function of injecting, automatic fault injection module is serially connected between interface adapter Signal-regulated kinase and tested controller, automatic fault injection module designs based on relay array, for analog sensor and between topworks and electronic controller signaling interface short circuit, short circuit, build rigid line fault.
Those skilled in the art of the present technique are understandable that, unless otherwise defined, all terms used herein (comprising technical term and scientific terminology) have the meaning identical with the general understanding of the those of ordinary skill in field belonging to the present invention.Should also be understood that those terms defined in such as general dictionary should be understood to have the meaning consistent with the meaning in the context of prior art, unless and define as here, can not explain by idealized or too formal implication.
Above-described embodiment; object of the present invention, technical scheme and beneficial effect are further described; be understood that; the foregoing is only the specific embodiment of the present invention; be not limited to the present invention; within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (6)
1. Simulation of Aeroengine Control System interface adapter, is characterized in that, comprises interface configuration management and signal monitoring module, signal converting module, signal wiring module, direct fault location module, Signal-regulated kinase and interface control module;
Described interface configuration management is connected with signal converting module, signal wiring module, direct fault location module, Signal-regulated kinase, interface control module respectively with signal monitoring module; Described signal converting module, signal wiring module, direct fault location module, Signal-regulated kinase, interface control module are connected successively; Described signal converting module is connected with the controller of aeroengine control system; Described interface control module is connected with outside Real-time hardware platform;
Described interface configuration management is used for control signal I/O, signal scaling, communication, direct fault location and Experiment Data Records with signal monitoring module and manages;
Described signal converting module is used for concentrating the sort interface providing aeroengine control system controller input/output signal;
Described signal wiring module for providing the patch panels of aeroengine control system controller input/output signal, with manual ON, disconnection, overlap joint signal path;
Described direct fault location module is for simulating and injecting the short circuit of sensor and operator signals interface, open circuit, overlap joint rigid line fault;
Described Signal-regulated kinase is used for the electric current exported from direct fault location module, pulsewidth and switching signal to nurse one's health into normal voltage that interface control module can gather, pulse and level signal, the normal voltage of interface control module output, frequency signal is changed into sensor analog signals corresponding to aeroengine control system controller simultaneously;
Described interface control module is used for normal voltage that collection signal conditioning module enters, pulse, level signal export outside Real-time hardware platform to, converts the signal of outside Real-time hardware platform feedback to outputting standard voltage simultaneously, frequency signal passes to Signal-regulated kinase.
2. Simulation of Aeroengine Control System interface adapter according to claim 1, is characterized in that, described interface control module adopts board, and this board is based on the one in pci bus, PXI bus or vxi bus.
3. Simulation of Aeroengine Control System interface adapter according to claim 1, is characterized in that, described interface control module adopts the CRIO module architectures based on spi bus.
4. Simulation of Aeroengine Control System interface adapter according to claim 1, is characterized in that, described interface control module adopts independently embedded system module.
5. Simulation of Aeroengine Control System interface adapter according to claim 1, is characterized in that, the controller of described aeroengine control system is engine electronic control.
6. Simulation of Aeroengine Control System interface adapter according to claim 1, is characterized in that, the controller of described aeroengine control system is rapid prototyping controller.
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| CN107444673A (en) * | 2017-07-12 | 2017-12-08 | 南京航空航天大学 | The control noise reduction test platform that is synchronised based on small propeller fixed-wing unmanned plane |
| CN107703443A (en) * | 2017-09-30 | 2018-02-16 | 北京电子工程总体研究所 | A kind of vxi bus signal control module, equipment and system comprising the module |
| CN108120606A (en) * | 2018-01-29 | 2018-06-05 | 吉林大学 | Commercial car electric brake system hardware-in-the-loop test platform and test method based on PXI and cRIO controllers |
| CN108334060A (en) * | 2018-03-15 | 2018-07-27 | 北京润科通用技术有限公司 | A kind of bus failure injection device |
| CN108491330A (en) * | 2018-04-02 | 2018-09-04 | 上海微小卫星工程中心 | A kind of verification experimental verification system and method applied to the in-orbit reconstruct of satellite CPU software |
| CN109709935A (en) * | 2018-12-21 | 2019-05-03 | 中国航发控制系统研究所 | A kind of pressure sensor signal analog circuit and test device |
| CN110674582A (en) * | 2019-09-29 | 2020-01-10 | 中仿智能科技（上海）股份有限公司 | Simulation model and method for simulating aircraft fuel system |
| CN110879584A (en) * | 2019-09-29 | 2020-03-13 | 北京动力机械研究所 | Turbofan engine comprehensive simulation test and fault injection platform for unmanned aerial vehicle |
| CN111696690A (en) * | 2020-06-22 | 2020-09-22 | 中国核动力研究设计院 | Wide-temperature radiation-resistant adjuster for detecting acoustic emission signals of reactor |
| CN113358366A (en) * | 2021-06-07 | 2021-09-07 | 南京航空航天大学 | Aircraft engine fault simulation system and control method |
| CN113759809A (en) * | 2021-09-29 | 2021-12-07 | 中国航发动力股份有限公司 | Calibration instrument for calibrating adjusting mechanism and calibrating method of adjusting mechanism |
| CN114217871A (en) * | 2021-12-14 | 2022-03-22 | 中国航发控制系统研究所 | Multi-computer cluster parallel simulation method and multi-computer cluster system |
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| CN105675925A (en) * | 2016-01-20 | 2016-06-15 | 中国航空综合技术研究所 | Cascade fault injection interface adapter of single-stage switch suitable for electronic product |
| CN105675925B (en) * | 2016-01-20 | 2018-07-24 | 中国航空综合技术研究所 | A kind of Mono-pole switch cascading failure grouting socket adapter suitable for electronic product |
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| CN107444673A (en) * | 2017-07-12 | 2017-12-08 | 南京航空航天大学 | The control noise reduction test platform that is synchronised based on small propeller fixed-wing unmanned plane |
| CN107703443A (en) * | 2017-09-30 | 2018-02-16 | 北京电子工程总体研究所 | A kind of vxi bus signal control module, equipment and system comprising the module |
| CN108120606A (en) * | 2018-01-29 | 2018-06-05 | 吉林大学 | Commercial car electric brake system hardware-in-the-loop test platform and test method based on PXI and cRIO controllers |
| CN108334060A (en) * | 2018-03-15 | 2018-07-27 | 北京润科通用技术有限公司 | A kind of bus failure injection device |
| CN108491330A (en) * | 2018-04-02 | 2018-09-04 | 上海微小卫星工程中心 | A kind of verification experimental verification system and method applied to the in-orbit reconstruct of satellite CPU software |
| CN109709935A (en) * | 2018-12-21 | 2019-05-03 | 中国航发控制系统研究所 | A kind of pressure sensor signal analog circuit and test device |
| CN110674582A (en) * | 2019-09-29 | 2020-01-10 | 中仿智能科技（上海）股份有限公司 | Simulation model and method for simulating aircraft fuel system |
| CN110879584A (en) * | 2019-09-29 | 2020-03-13 | 北京动力机械研究所 | Turbofan engine comprehensive simulation test and fault injection platform for unmanned aerial vehicle |
| CN110674582B (en) * | 2019-09-29 | 2023-08-25 | 中仿智能科技（上海）股份有限公司 | Simulation model for simulating fuel system of aircraft and method thereof |
| CN111696690A (en) * | 2020-06-22 | 2020-09-22 | 中国核动力研究设计院 | Wide-temperature radiation-resistant adjuster for detecting acoustic emission signals of reactor |
| CN113358366A (en) * | 2021-06-07 | 2021-09-07 | 南京航空航天大学 | Aircraft engine fault simulation system and control method |
| CN113759809A (en) * | 2021-09-29 | 2021-12-07 | 中国航发动力股份有限公司 | Calibration instrument for calibrating adjusting mechanism and calibrating method of adjusting mechanism |
| CN113759809B (en) * | 2021-09-29 | 2023-07-11 | 中国航发动力股份有限公司 | Calibrating instrument for calibrating adjusting mechanism and calibrating method of adjusting mechanism |
| CN114217871A (en) * | 2021-12-14 | 2022-03-22 | 中国航发控制系统研究所 | Multi-computer cluster parallel simulation method and multi-computer cluster system |
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Application publication date: 20150708 |