CN101561351B - Airplane engine dynamic simulation test bed - Google Patents
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Abstract
The invention pertains to the field of 'engine test equipment and test technologies', and relates to an airplane engine dynamic simulation test bed. The airplane engine dynamic simulation test bed consists of a 50-stitch interface definition, a left and right engine full privilege digital electronic controller, an engine electric control unit, an engine vibration detecting instrument, a testing part and a measuring and controlling system. The measuring and controlling system comprises a simulation/dispersion input interface card, measuring and controlling software of an embedded engine simulation model, a sensor simulation unit and an output interface card. The test bad has the advantages of complete function, high intelligent property, fast response time and capability of precisely simulating the dynamic and steady work process and fault monitoring result of the whole flight envelope internal power device system of an airplane by the engine simulation model, an electric simulation technology and a dynamic simulation technology under the condition of no real engine existing. The test bed can be used in the test study of a power device comprehensive control system of the whole system of the airplane and the function study of the airborne testing part.
Description
Technical field
The invention belongs to " engine test facility and experimental technique " field.Relate to a kind of airplane engine dynamic simulation test bed.
Background technology
Advanced aircraft power device complex control system relates to engine full powers limit digital electronic controller (Full Authority Digital Electronic Control (FADEC)), engine electrically control module (Engine Interface Control Unit (EICU)), the work of engine luggine detector airborne opertaing devices such as (Engine Vibration Monitor (EVM)), and these equipment and aircraft avionics, fly control, the ring control, the crosslinked work of systems such as undercarriage, electronization between system, integrated level, synthesization degree height, relation is complicated between system, relevance is strong.Therefore, must carry out various function tests and crosslinked test, the function and the performance of checking propulsion system complex control system to power plant system; Check the compatibility of control system and other system interface of aircraft; The matching of checking FADEC and aircraft under real airplane synthetic environment; The assessment control system must be developed aircraft power plant complex control system testing table thus and test and design verification the improvement degree of aircraft and engine performance.
At present, domestic part institutes is devoted to develop the FADEC control system, but just with the product of FADEC as engine, study its inner algorithm, principle of work etc., the propulsion system complex control system functional verification testing equipment that relates to complete machine still belongs to blank.
External advanced engine complex control system testing table (U.S. GE company) only is confined to the design of FADEC control system function and the checking of engine, can't examine the design of aircraft power plant complex control system; Also can't provide the aircraft power plant system real air-borne test environment, more can not examine the Comprehensive Control result between FADEC and airborne equipment.
Summary of the invention
The purpose of this invention is to provide a kind of can be under TT﹠C software (embedded engine mathematical model) control, drive each testpieces operate as normal, and the testing equipment of the practical work process of energy true and accurate simulated engine complex control system in whole flight envelope.
Technical solution of the present invention is, airplane engine dynamic simulation test bed by interface definition 50 pins, Left Hand Engine full powers limit digital electronic controller, right engine full powers limit digital electronic controller, engine electrically control module, engine luggine detector, engine test part (priming valve, frost valve, lighter), and TT﹠C system is formed.Wherein, TT﹠C system comprises TT﹠C software, Sensor Analog Relay System unit and the interface output card of simulation/discrete input interface card, embedded engine realistic model.The front end of interface definition 50 pins is connected with airplane synthetic avionics system testing table, and the rear end is connected with Left Hand Engine full powers limit digital electronic controller, right engine full powers limit digital electronic controller, engine electrically control module and the corresponding input interface of engine luggine detector respectively.Then, the output interface by Left Hand Engine full powers limit digital electronic controller, right engine full powers limit digital electronic controller, engine electrically control module and engine luggine detector, testpieces is connected with simulation/discrete input interface card, Sensor Analog Relay System unit and the interface output card of TT﹠C system respectively.TT﹠C software is with the software kernel of engine realistic model as system, can export the status signal of engine correspondence according to the signal controlling Sensor Analog Relay System unit that engine mockup is exported in real time in real time, its two passages, engine electrically control module and engine luggine detector of giving Left Hand Engine full powers limit digital electronic controller and right engine full powers limit digital electronic controller respectively be gathered and resolved by the output interface card.Simultaneously, the controlled quentity controlled variable that TT﹠C software is gathered left and right sides engine full powers limit digital electronic controller by simulation/discrete input interface card, and the engine test part by output interface card control outside and engine mockup real-time motion and undertaken by the engine passenger cabin indication warning system that interface definition 50 pins are given the airplane synthetic testing table with the status signal of engine that state shows and monitoring.
The advantageous effect that the present invention has, advantage of the present invention is that testing table telotism, intellectuality and reliability height, response time are fast, do not having under the situation of actual engine, by engine realistic model, electronic simulation technology and Dynamic Simulation Technology, the dynamic and steady operation process of the accurate whole flight envelope internally-powered of simulated aircraft apparatus system; The function and the performance of checking propulsion system complex control system; Check the compatibility of control system and other system interface of aircraft; The matching of checking FADEC and aircraft under real airplane synthetic environment; The assessment control system is to the improvement degree of aircraft and engine performance, it is indispensable propulsion system complex control system testing equipment before the aircraft first-fly, this invention also can be used for the experimental study of the propulsion system complex control system of other model aircraft machine system, reaches the functional study of air-borne test spares such as FADEC, EICU, EVM.
The present invention adopts the electronic simulation mode to encourage the testpieces work of The whole control system.Analog sensor comprises differential displacement sensor (LVDT), speed probe and thermocouple sensor; Analog controller comprises servo-valve, solenoid valve.In the systemic software development, adopt real-time acquisition module, dynamic data filtering and real-time dynamic data to adjust the real-time accuracy that function has guaranteed parameter detecting and simulation.Adopt interface definition 50 pins, guarantee the true airborne circumstance of power plant system.
Description of drawings
Fig. 1 testing table schematic diagram
Fig. 2 thermocouple sensor principle of simulation
Fig. 3 LVDT Sensor Analog Relay System principle
Fig. 4 speed probe principle of simulation
Fig. 5 TT﹠C software process flow diagram
Embodiment
Testing table is by interface definition 50 pins 8, Left Hand Engine full powers limit digital electronic controller 12, right engine full powers limit digital electronic controller 9, engine electrically control module 11, engine luggine detector 13, engine test part 10, and TT﹠C system 18 is formed, wherein, TT﹠C system 15 comprises simulation/discrete input interface card 14, TT﹠C software 18 embedded engine realistic models 17, Sensor Analog Relay System unit 16 and output interface card 19; The front end of interface definition 50 pins 8 is connected with airplane synthetic avionics system testing table 5, digital electronic controller 12 is limit with the Left Hand Engine full powers respectively in the rear end, right engine full powers limit digital electronic controller 9, engine electrically control module 11 and engine luggine detector 13 corresponding input interfaces connect, then, Left Hand Engine full powers limit digital electronic controller 12, right engine full powers limit digital electronic controller 9, engine electrically control module 11 and engine luggine detector 13, the output interface of testpieces respectively with the simulation of TT﹠C system 15/discrete input interface card 14, Sensor Analog Relay System/signal condition unit 16 and output interface card 19 connect.
TT﹠C software 18 embedded engine realistic models 17, TT﹠C software is exported the status signal of engine correspondence in the signal controlling Sensor Analog Relay System of output/signal condition unit 16 in real time in real time according to engine mockup, give the A of Left Hand Engine full powers limit digital electronic controller 12 and right engine full powers limit digital electronic controller 9 by output interface card 19 respectively with it, the B passage, engine electrically control module 11 and engine luggine detector 13 are gathered and are resolved, simultaneously, TT﹠C software 18 is gathered the controlled quentity controlled variable of engine full powers limit digital electronic controllers by simulation/discrete input interface card 14, and carries out by the outside engine test part 10 of output interface card 19 controls and engine mockup real-time motion and by the engine passenger cabin indication warning system 2 that interface definition 50 pins 8 are given airplane synthetic testing table 5 with the status signal of engine that state shows and monitoring.
Embodiment
1. system hardware is formed and design
System adopts PXI bus-type control system pattern, is mainly become by interface definition 50 pins, left and right sides engine full powers limit digital electronic controller, engine electrically control module, engine luggine detector, engine test part (priming valve, anti-relay, the lighter of pushing away), TT﹠C system, external interface and other enclosure group.TT﹠C system comprises TT﹠C software, Sensor Analog Relay System unit and the output interface card of simulation/discrete input interface card, embedded engine realistic model.Interface definition 50 pin front ends connect with the corresponding input end of the interface input/output cards 7 of airplane synthetic avionics system testing table, and interface 50 pin rear ends are connected with left and right sides engine full powers limit digital electronic controller, engine electrically control module and the corresponding input interface of engine luggine detector respectively.Then, the output interface by Left Hand Engine full powers limit digital electronic controller, right engine full powers limit digital electronic controller, engine electrically control module and engine luggine detector, testpieces is connected with simulation/discrete input interface card, Sensor Analog Relay System unit and the interface output card of TT﹠C system respectively.
Interface definition 50 pin front end signals comprise throttle platform 1, the starting/parking panel 4 of airplane synthetic avionics system testing table to the engine simulation test stand, the command signal of engine passenger cabin indication warning system (EICAS) 2, aircraft avionics system device 3, and engine full powers limits digital electronic controller, engine electrically control module and engine luggine detector and testpieces feed back to signals such as EICAS and aircraft avionics system device DCU, monitors in real time and show.
1.1 computing machine
Can operate under the Windows2000/XP environment 3.0GHz CPU, 180GB hard disk, 2GB internal memory, 128MB video card, DVD drive, 3.5 " floppy drives; Peripheral hardware: Samsung 19 " liquid crystal.
1.2 switch board
Two prestige figure standard industrial computer cabinets are adopted in the entire system topology layout.Be respectively test observing and controlling cabinet and testpieces cabinet, connect by the PXI bus between two industry control cabinets.Test observing and controlling cabinet is placed Industrial Control Computer, display and 8 mouthfuls of routers.Testpieces cabinet bottom place system power supply; The second layer is a 3UPXI system subrack, built-in all input/output interface board cards; The 3rd layer is 4U drawer type testpieces subrack, places test relay, fictitious load; The 4th layer is that 2U drawer type subrack is placed PMAT (portable tester); Five, six layers is 9U, two FADEC about putting respectively; Seven layers are 4U placement EICU, EVM.Switch board front panel, place system power switch and indication thereof, left and right sides engines ground maintenance switch respectively.The Sensor Analog Relay System unit places side of cabinet, meets left and right sides FADEC respectively by left-right symmetric.Rear panel arrange supply socket, with 6 50 needle interface plugs, lighter external socket and the interface integrated circuit board terminal of aircraft avionics system and other system interface.Lighter, priming valve, frost valve place industry control cabinet outside.
1.3PXI system
The PXI system configuration has A/D 64 tunnel, D/A 16 tunnel, 44 of DI/O 168 tunnel, 429 signals to receive.System's integrated circuit board all is configured in the PXI cabinet.The integrated circuit board specific targets are as follows:
◆ the PXI cabinet: 1, Ling Hua PXIS-2630 cabinet, 3U 19 " and 8 grooves, 400W, 1 system's groove (PXI-8570), 7 expansion slot are joined PCI-8570, highest-traffic 132MB/s.
◆ the A/D capture card: 1, Ling Hua PXI-2206, the Dynamic Data Acquiring integrated circuit board, 16Bit resolution, the input of 64/32 road list/both-end, the 250KS/S picking rate, 24 road DI/O possess DMA and interrupt drainage pattern, programme-controlled gain control.
◆ the D/A output card: 2, select Ling Hua PXI-2502 for use, technical indicator is: 12Bit resolution, the output of 8 road voltages, turnover rate 1MS/S, 24 road DI/O, supporting terminal board DIN-68S.
◆ digital I/O card: 2, select Ling Hua CPCI-7248 for use, 48 road Transistor-Transistor Logic levels, supporting terminal board DIN-100S.
◆ 429 bus cards: 1, select EXC-429/CPCI for use, receive transfer rate 100KHz for 44.
1.4 system power supply
System 115V/400Hz, 28VDC, 220V/50Hz power supply are provided by the aircraft power system 6 of airplane synthetic avionics testing table, DC power supplier of internal configurations, input power supply 220V/50Hz; Output comprises ± 15V/4A ± 5V/4A ,+28V/5A.
1.5 Sensor Analog Relay System unit
1.5.1 thermocouple sensor analogue unit
Principle of simulation is seen Fig. 2.The practical work process of T12 in the system simulation engine operation process (fan temperature in), T25 (Compressor Inlet Temperature).Wherein, the excitation of T12 and T25 is provided by FADEC, the maximum 10mA of exciting current.According to the sensor characteristic analysis, system adopts the resistance value (72 Ω～212 Ω corresponding temperatures-70 ℃～300 ℃) of digital regulation resistance X9C103 simulation PT100 output.Simulate every binary channels and need DO 15CH.The resistance value that system is exported according to engine mockup in real time by TT﹠C software, send corresponding DO1, DO2 and DO3 signal, in real time control figure potentiometer X9C103 changes the practical work process of resistance value simulation RTD, gives FADEC (A) with resistance output as a result then, (B) passage resolves.
1.5.2 differential displacement sensor analogue unit
Pressurized struts such as FMV in the system simulation engine operation process (fuel metering valve), VBV (adjustable air release), VSV (adjustable stator blade), HTPACC (High Pressure Turbine Clearance operation valve), TBV (transient state air release), TRAS (counter push away pressurized strut) feed back to the real-time LVDT position signalling of FADEC.
According to the requirement of LVDT characteristic, adopt the excitation load of special electronic transformer simulation FADEC, primary connects the FADEC excitation, the inferior utmost point is exported the sinusoidal signal of two groups of fixed waveforms to subsequent conditioning circuit, be input to the digital program controlled gain amplifier of forming by integrated transporting discharging LF353 then and carry out amplitude adjusted, can obtain an adjustable LVDT output waveform, send into FADEC again and resolve.Principle of simulation is seen Fig. 3.
Wherein, the selected X9312WP digital regulation resistance of system is 10K Ω, 100 taps.In the process of the test, by the LVDT signal of TT﹠C software according to the real-time output of engine mockup, by the corresponding DO mouth of CPCI-7248 output signal, the control figure potentiometer is exported the resistance of regulation on request, thereby change gain (K=RW/R1) amplitude of Va and Vb, and give FADEC with the result and gather and settle accounts
Every binary channels needs DO 35CH altogether.
1.5.3 speed probe analogue unit
N1 (rotation speed of the fan), N2 (core engine rotating speed), NG2 (hydraulic pump rotating speed) are the important parameters of FADEC and EVM input.Adopt the accurate function generator of ICL8038 to simulate in the speed probe model unit, this chip is the monolithic integrated circuit chip that adopts advanced technologies such as Schottky gesture diode of heap of stone to make, the supply voltage wide ranges, the degree of stability height, precision is high and easy-to-use, frequency with the output of sine function signal, its function waveform is controlled by external voltage, and the frequency output area is 0.001Hz-1MHz.
Send signal 0～10V by the D/A of computing machine (about totally 6 tunnel) in the test, through voltage transitions is that 10～15V is added to accurate function chip 8 pin, the chip signal output frequency is by 0～5500HZ, thereby the output of simulation speed probe send FADEC and EVM to gather then.The speed probe mimic channel is seen Fig. 4.
1.6 the detection of valve control signal and the excitation of testpieces control
In the TT﹠C system operation process of testing table can with FADEC to the control signal of various valves (priming valve, frost valve, lighter, oil mass valve) output (± 75mA) send into the system simulation observation circuit, behind filter shape, by A/D input interface card TT﹠C system is sent in this instruction again and shown in real time.TT﹠C system is when monitoring this controlled quentity controlled variable, can be in the starting of engine, igniting, instead push away, Thrust Control etc. is dynamically and in the quiet rum process, priming valve, the anti-control signal that pushes away testpieces such as relay, lighter with monitoring in real time drive outside testpieces operate as normal by analog output circuit.System needs A/D 14 tunnel, D/A 8 tunnel.
Here the excitation steering logic of sending out lighter with the right side is illustrated.Right sending out in the lighting simulation system, when collecting passenger cabin throttle platform by interface definition 50 pins, FADEC provides starting, firing command, and judge that right shipping forwards N2 〉=7% o'clock to, just send 28V lighter pumping signal, after this moment, TT﹠C software collected this command signal by analog input interface card A/D passage, just send this signal by interface output card D/A passage in real time, make the right ignition relay adhesive of sending out, just right lighter A of excitation or B work.At this moment, TT﹠C software send EICU and DCU to monitor ignition voltage and current status by interface definition 50 pins, send passenger cabin EICAS indication simultaneously.In the test, testing table needs to gather in real time right relay, initial firing current, the state of ignition voltage, and the real-time, interactive of maintenance and engine mockup sent out.Adopt identical simulation mechanism, the accordingly result of malfunctions such as other relay, testpieces can be simulated by system.
2. TT﹠C software module construction and design
TT﹠C software adopts OO Borland C++Builder 6.0 exploitations, and modular organization is divided into test configurations, the demarcation of observing and controlling passage, process of the test control, experimental data processing four module according to function.
The TT﹠C software flow process is seen Fig. 5.TT﹠C software begin 21 carry out after, just carry out system state sampling 22, whether correct by the state that simulation/discrete input interface card detects external sensor analogue unit, testpieces.If it is correct, TT﹠C software running engine realistic model 24, corresponding output parameter is given the A of FADEC respectively by the output interface card, B passage 25 carries out signals collecting, FADEC is by the input parameter of engine input parameter and aircraft cockpit instruction 23 simultaneously, judge that engine is in starting, stop, or anti-push mode 26, if be No, TT﹠C system is fed back malfunction 27 and by interface definition 50 pins it is fed back to the passenger cabin indication, if be Yes, TT﹠C software is just gathered the controlled quentity controlled variable of FADEC and EICU by the input interface card, making the digital regulation resistance of Sensor Analog Relay System unit simulate corresponding valve position according to model output first moves, rotating speed, temperature 29, first according to FADEC, the controlled quentity controlled variable control starter relay or anti-relay switch 30 closures that push away of the output of EICU controller, the excitation priming valve, frost valve testpieces 32 real-time workings, to control result 31 then send FADEC to resolve and controls engine running in real time, in the whole TT﹠C software operational process, system can be with the engine mockup parameter, aircraft state, the testpieces state is presented on the software interface 35 in real time, and preserves test figure 34.Meanwhile, system can arbitrarily be provided with malfunction by software interface, and by FADEC and passenger cabin EICAS recording geometry response results.
2.1 test configurations
Test configurations is mainly carried out the work that is provided with of experimental enviroment, comprises system works path, A/D passage, D/A passage, network channel, 429 buses and the isoparametric setting of each test parameters malfunction.
2.2 the observing and controlling passage is demarcated
The observing and controlling passage is demarcated and can be comprised that passage is demarcated, engine mockup self check two big functions.
Wherein, the passage calibrating function comprises that input channel is demarcated, output channel is demarcated and digital I/O passage is demarcated three big functional modules.The input channel calibrating function be mainly used in the signal feedback passage zero, work to the last minute and dimension is demarcated, it has functions such as programme-controlled gain, automatic zero adjustment; The output channel calibrating function is mainly used in zero, the work to the last minute adjustment and the rated current setting of analog output channel electric current; Numeral I/O passage calibrating function can be checked, be provided with employed digital I/O passage in the system.
The engine mockup self-checking function is mainly used in the ruuning situation of checking the engine software model, can simple engine parameter be set to observe the running status of engine mockup by the user.
2.3 process of the test control
Process of the test control is the Core Feature of software, and it comprises the parameter setting and controls two big functions.
Wherein, it is to test the operation steps that must carry out before the control that test parameters is provided with function, it is used for being provided with tests the necessary test parameters of control, comprises that basic general parameter setting, engine start/igniting/Stop Control System test parameters setting, the anti-icing test parameters setting of nacelle, the parameter setting of engine luggine monitoring test and anti-pushing system test parameters are provided with the five functional module.
Test control comprises following function:
A) show test figure, curve in real time;
B) by time funtcional relationship real-time storage test figure;
C) controlled variable real-time regulated;
D) have perfect fault detect, fault alarm, failure protection function;
E) real-time network communication and data-transformation facility;
F) the state simulation function of various function tests;
G) fault simulating function of various function tests;
2.4 experimental data processing
Experimental data processing is mainly used in the measuring and control data that system is preserved and carries out post-processed, and it comprises functions such as page setup, data processing and curve processing.Wherein, the page layout when page setup is used to data processing is set comprises the parameters such as last bottom margin, header, footer type and the page number of the printable page.Data processing and curve processing function are mainly used in carries out data readback, curve fit to test figure, and print data is reported, the curve report.Have functions such as print format is optional, data area is optional, curve amplifies/dwindles.
Claims (1)
- One kind airplane engine dynamic simulation test bed, it is characterized in that, testing table is by interface definition 50 pins (8), Left Hand Engine full powers limit digital electronic controller (12), right engine full powers limit digital electronic controller (9), engine electrically control module (11), engine luggine detector (13), engine test part (10), and TT﹠C system (18) is formed, wherein, TT﹠C system (15) comprises simulation/discrete input interface card (14), the embedded engine realistic model of TT﹠C software (18) (17), Sensor Analog Relay System unit (16) and interface output card (19); The front end of interface definition 50 pins (8) is connected with airplane synthetic avionics system testing table (5), digital electronic controller (12) is limit with the Left Hand Engine full powers respectively in the rear end, right engine full powers limit digital electronic controller (9), the corresponding input interface of engine electrically control module (11) and engine luggine detector (13) connects, then, Left Hand Engine full powers limit digital electronic controller (12), right engine full powers limit digital electronic controller (9), engine electrically control module (11) and engine luggine detector (13), the output interface of testpieces respectively with the simulation of TT﹠C system (15)/discrete input interface card (14), Sensor Analog Relay System unit (16) and interface output card (19) connect; The signal controlling Sensor Analog Relay System unit (16) that TT﹠C software (18) is exported in real time according to engine mockup is exported the status signal of engine correspondence in real time, give the A of Left Hand Engine full powers limit digital electronic controller (12) and right engine full powers limit digital electronic controllers (9) by interface output card (19) respectively with it, the B passage, engine electrically control module (11) and engine luggine detector (13) are gathered and are resolved, simultaneously, TT﹠C software (18) is gathered the controlled quentity controlled variable that left and right sides engine full powers are limit digital electronic controllers (12 and 9) by the simulation/input interface card (14) that disperses, and also carries out state demonstration and monitoring by the engine passenger cabin indication warning system (2) that interface definition 50 pins (8) are given airplane synthetic avionics system testing table (5) with the status signal of engine by interface output card (19) control outside engine test part (10) and engine mockup real-time motion.
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| CN110963073B (en) * | 2019-12-24 | 2022-12-09 | 中航贵州飞机有限责任公司 | Multipurpose airplane wheel speed signal simulation system |
| CN111208744B (en) * | 2019-12-27 | 2022-09-20 | 中国航空工业集团公司西安飞机设计研究所 | Central alarm verification method under comprehensive modular avionics architecture |
| CN113934153B (en) * | 2020-06-29 | 2024-09-03 | 中国航发商用航空发动机有限责任公司 | Multichannel simulation method and system for aero-engine control system |
| CN113310695B (en) * | 2021-05-28 | 2023-01-31 | 中国商用飞机有限责任公司 | Aircraft engine windmill load ground simulation method and system |
| CN113625596A (en) * | 2021-08-03 | 2021-11-09 | 中国航发湖南动力机械研究所 | Semi-physical simulation system for health management system of aircraft engine |
| CN113724556B (en) * | 2021-09-14 | 2024-02-02 | 湖南中成伟业电子技术有限公司 | Simulation training device for aircraft engine instrument |
| 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 |
| CN114136629A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Digital accelerator device and test bed accelerator signal simulation system |
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