CN205940903U - Full static pressure test system of aircraft based on self -adaptation PID method - Google Patents
Full static pressure test system of aircraft based on self -adaptation PID method Download PDFInfo
- Publication number
- CN205940903U CN205940903U CN201620618789.1U CN201620618789U CN205940903U CN 205940903 U CN205940903 U CN 205940903U CN 201620618789 U CN201620618789 U CN 201620618789U CN 205940903 U CN205940903 U CN 205940903U
- Authority
- CN
- China
- Prior art keywords
- pin
- module
- interface
- valve
- magnetic valve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Feedback Control In General (AREA)
Abstract
The utility model relates to a full static pressure test system of aircraft based on self -adaptation PID method. Power module all the way through keep apart power module respectively with the control core module, the man -machine interface module is connected, another way is connected with vacuum pump and compressor respectively, the control core module respectively with the man -machine interface module, optical coupling isolator, 485 bus module connects, optical coupling isolator respectively with relay module, signal transmitter I ~ II connects, relay module respectively with solenoid valve I ~ V, vacuum pump and compressor are connected, signal transmitter I is connected with proportional valve module I ~ II respectively, signal transmitter II is connected with sensor I ~ IV respectively, 485 bus module respectively with computer interface, the data storage interface, pressurize experiment program upgrade interface, atmospheric pressure produces the wave form interface, wireless transmission interface connection. Can accord with the full static pressure system test standard of the aircraft of stipulating in the aircraft maintenance handbook automatically with higher precision and the very fast accurate real time control atmospheric pressure of dynamic response.
Description
Technical field
The utility model belongs to field of automatic testing, particularly to a kind of aircraft pitot-static pressure based on self-adaptive PID method
Test system.
Background technology
Pitot-static pressure test system is used in the internal field maintenance and Flight Line Maintenance that need aircraft is carried out pitot-static pressure test, system
According to the operational order of tester, provide corresponding pneumatic supply respectively for aero pilot-static pressure system.Aircraft pitot-static pressure is surveyed at present
Test system acquisition cost is high, and maintenance cost is high, and maintenance period is long, and the normal operation to airline is made troubles, or even due to
The precision change bringing of transporting for long-distance changes with air-tightness, brings certain impact to flight safety.Additionally, existing tester
Carry out pressure change operation mainly by ball valve, its testing time is long, low precision, testing process is complicated, easily causes human factor
Increase, bring flight safety hidden danger.Aero pilot-static pressure system belongs to high-accuracy, high-air-tightness, low discharge aircraft system, surveys
Examination requires complexity, strongly professional, is badly in need of the defect that a kind of test system makes up this technology.
Content of the invention
The purpose of this utility model is to solve existing technical problem, makes for airline's pitot-static pressure test equipment
With with the inconvenience safeguarded, solve pitot-static pressure system testing and require implacable present situation, provide that a kind of cost is relatively low, structure is simple
Single, can quickly test, verify and easy to maintenance, can conveniently access aircraft system, meet airline's servicing manual test
The aircraft pitot-static pressure test system based on self-adaptive PID method requiring.System adoption rate valve is core component, using adaptive
Answer pid algorithm as control algolithm, can independently, flexibly, accurately, easily for aero pilot-static pressure system provide two-way accurately may be used
Control source of the gas, provide air-tightness automatically to calculate for tester simultaneously, aircraft instrument precision checking, real-time air pressure condition monitoring and
The function of record.Aircraft maintainers can be carried out automatic test to aircraft, substantially increase aircraft according to the data of system
The efficiency of maintenance and security, reduce related system fault and cause the possibility of aviation accident, reduces and is brought due to maintenance
Delayed probability.
For achieving the above object, the main technical schemes of employing are the utility model：A kind of based on self-adaptive PID method
Aircraft pitot-static pressure test system it is characterised in that：Including control core module, power module, insulating power supply module, light-coupled isolation
Device, 485 bus modules, relay module, signal transmitting device I, signal transmitting device II, proportioning valve module I, ratio valve module II,
Human-computer interaction interface module, baroceptor I, baroceptor II, baroceptor III, baroceptor IV, magnetic valve I,
Magnetic valve II, magnetic valve III, magnetic valve IV, magnetic valve V, vavuum pump and compressor, described power module leads up to isolation electricity
Source module is connected with control core module, human-computer interaction interface module respectively, and another road is connected with vavuum pump and compressor respectively,
Described control core module is connected with human-computer interaction interface module, optical coupling isolator, 485 bus modules respectively, described optocoupler every
Be connected with relay module, signal transmitting device I, signal transmitting device II respectively from device, described relay module respectively with magnetic valve
Ith, magnetic valve II, magnetic valve III, magnetic valve IV, magnetic valve V, vavuum pump and compressor connect, and described signal transmitting device I is respectively
Be connected with proportioning valve module I, ratio valve module II, described signal transmitting device II respectively with baroceptor I, baroceptor
IIth, baroceptor III, baroceptor IV connect, and described 485 bus modules are connect with computer interface, data storage respectively
Mouth, pressurize experimental arrangement upgrade interface, air pressure produce waveform interface, wireless transmission interface connects；
Described control core module includes single-chip microcomputer, power isolation circuit, interface and peripheral circuit；
485 described bus modules include 485 bus chips, optical coupling isolation circuit, transient voltage suppression circuit；
Described relay module includes high-current relay, optical coupling isolation circuit, level-conversion circuit；
Gas pressure sensor module includes sensor and its interface；Sensor include baroceptor I, baroceptor II,
Baroceptor III, baroceptor IV, the interface of sensor is respectively iic bus and RS232 EBI；
Described human-computer interaction interface module includes technical grade HMI touch-screen and its support circuit, and support circuit includes touching
Touch feedback circuit, control core circuit；
Described power supply includes 5V power module, 24V power module and 28V power module；
Described ratio valve module includes high-frequency electromagnetic needle-valve, sensor circuit, drive circuit；
Air pump and gas path module include vavuum pump, compressor, magnetic valve, draining valve, choke valve and its supporting gas circuit, electromagnetism
Valve includes magnetic valve I, magnetic valve II, magnetic valve III, magnetic valve IV, magnetic valve V；
Human-computer interaction interface module responds the input request of operator, and sends it to control core circuit, controls core
The collection of electrocardio road is from the real time data of gas pressure sensor module, and passes through 485 bus module control relay modules and ratio
Valve module constitutes closed loop feedback system, finally controls output pressure；
Human-computer interaction interface module adopts 8 inches of high graphics dot matrix screens that Di Wen company produces
DMT10768T080_07WT, ultimate resolution 1024*768, it carries capacitance touch screen, by programming to touch-control coordinate, permissible
Realize human-computer interaction function；
Control core module adopts the STM32F103VET6 microcontroller of ST company, has selected the embedded system of μ C/OS- II
The software platform that system is realized as code, operating frequency is 72MHz；
Ratio valve module adopts WFAS1TFEE045BXL the and WFAS1TFEE015BXL high-frequency electrical needle of ProALA company
Valve, it can control the flow of gas with ± 0.005% resolution precision ground；
Relay module adopts the SLA12VDC-SLA of SONGLE company, and the maximum current allowed reaches 10A, alternating voltage
Reach 250V；
Gas pressure sensor module includes two kinds, and a kind of is the RPT350 intelligence vibrating cylinder pressure transducer that GE company produces,
Its precision reaches ± 0.02%, and annual measurement stability drift is less than ± 0.015%；A kind of is that MEMA company produces
MS4525DO-DS3O015AP and MS4525DO-DS3O045AP piezoresistive silicon sensor, its response time is less than 1ms, can be right
Air pressure is quickly measured；
The control total core of RS485 is flowed in the MAX13487EESA half-duplex that 485 bus chips are produced using MAXIM company automatically
Piece, is operable with -40 DEG C to+85 DEG C temperature ranges, and transfer rate can reach 2Mbps；
Vavuum pump can reach 2kPa using the Vi120SV vavuum pump leaping refrigerant production, barometric minimum；
Using being newly the TC-20 series of compressor that sincere company produces, its highest air pressure can reach 400kPa to compressor；
Magnetic valve adopts the VT307-08 high-precision meter valve that STNC company produces, and can carry out the control of gas path on-off；
System controls inclusion：
(a) feedback element：Using the structure of closed loop feedback system, baroceptor I and baroceptor III use
MS4525 piezoresistive silicon sensor, baroceptor II and baroceptor IV adopt GERPT350 vibration cylinder pressure transducer,
In real time, automatically pick up current atmospheric pressure value, the sensor is accessed STM32 respectively in the way of IIC and RS232 bus micro-
Controller, after microcontroller recognizes sensor and accesses, you can start gathered data；
(b) control algolithm：In the microcontroller, pid control algorithm is designed with the method for software, by self-adaptive PID side
Method, the proportional component of calculating PID, differentiation element, the parameter of integral element in real time, the output of control algolithm is through RS485 bus
Module, accesses proportional valve driving gear, drives the high-frequency electromagnetic needle-valve of proportioning valve inside modules that pressure is adjusted；
(c) executing agency：Control instruction is converted to the standard signal of 4～20mA by driving means, corresponding high-frequency electrical needle
The equivalent aperture of valve is 0～100%, and when aperture is different, gas flow is of different sizes, in driving means, carries out heap to instruction
Stack designs, and rejects the instruction of mistake, retains and correctly instructs, and drives high-frequency electromagnetic needle-valve to move；
Gas circuit is connected as：1 mouthful of proportioning valve module I passes sequentially through magnetic valve I, displacement can and vacuum using gas circuit silicone tube
Pump connects, and displacement can is connected with draining valve by gas circuit silicone tube, and 2 mouthfuls of proportioning valve module I are led to successively using gas circuit silicone tube
Cross baroceptor I, baroceptor II, pressure buffer tank I are connected with Ps out splice going splice；
Compressor is connected with one end of choke valve by gas circuit silicone tube, and the other end of choke valve leads up to magnetic valve II
It is connected with 3 mouthfuls of proportioning valve module I, another road passes sequentially through magnetic valve IV, 3 mouthfuls of ratio valve module II and 1 mouthful, magnetic valve III
Gas circuit silicone tube between displacement can and magnetic valve I is connected, 2 mouthfuls of ratio valve module II pass sequentially through baroceptor III,
Baroceptor IV, magnetic valve V, pressure buffer tank II are connected with Pt out splice going splice.
The utility model has the advantages and positive effects that：Compared with existing air pressure test equipment, can be automatically
With 0.2% degree of precision and faster dynamic response accurate real-time control air pressure, meet and fly specified in aircraft maintenance handbook
Machine pitot-static pressure system testing standard (0.8%), the universal precision of other test equipments is below 0.5%.
The fortuitous event in test process can fully be tackled, protection is test for aircraft component, using safer.
Carry out man-machine interaction, easy-to-operate by the way of touch-screen input and display, hommization is good.
Adopt silicon piezo-risistive baroceptor in dynamic process, during static adjustment, adopt vibration cylinder type air pressure sensing
Device, has been effectively combined two kinds of sensors a little, and the cost of equipment can be greatly reduced, and increases economy.
Full-automation can be realized in test process, without personnel guard, the operating efficiency of flight crew can be improved.
PCB manufacturing process is focused on adopt environmental-friendly lead-free material, meet European Union's RoHS standard.
Using vavuum pump and compressor all using oil-free low-power consumption vavuum pump, compared to existing air pressure test equipment,
Power consumption is lower, and service life is longer.
The advantage that easy to maintenance, use is flexible, can customize test program according to the test request of user's request and aircraft.
Brief description
Fig. 1 is that circuit of the present utility model connects block diagram；
Fig. 2 is that gas circuit of the present utility model connects block diagram；
Fig. 3 is the structural representation of testing stand of the present utility model；
Fig. 4 is control system architecture figure of the present utility model；
Fig. 5 is control core module circuit diagram of the present utility model；
Fig. 6 is insulating power supply module circuit diagram of the present utility model；
Fig. 7 is 485 bus module circuit diagrams of the present utility model；
Fig. 8 is relay module circuit diagram of the present utility model；
Fig. 9 is human-computer interaction interface schematic diagram of the present utility model；
Figure 10 is proportioning valve modular structure schematic diagram of the present utility model；
Figure 11 is testing process schematic diagram of the present utility model；
Figure 12 is embedded software structural representation of the present utility model.
Specific embodiment
In order to be illustrated more clearly that the utility model, elaborate embodiment of the present utility model below according to accompanying drawing.
As shown in Figures 1 to 12, a kind of aircraft pitot-static pressure test system based on self-adaptive PID method, including control core
Core module, power module, insulating power supply module, optical coupling isolator, 485 bus modules, relay module, signal transmitting device I, letter
Number transmitter II, proportioning valve module I, ratio valve module II, human-computer interaction interface module, baroceptor I, baroceptor
IIth, baroceptor III, baroceptor IV, magnetic valve I, magnetic valve II, magnetic valve III, magnetic valve IV, magnetic valve V, vacuum
Pump and compressor.
Power module is led up to insulating power supply module and is connected with control core module, human-computer interaction interface module respectively,
Another road is connected with vavuum pump and compressor respectively, control core module respectively with human-computer interaction interface module, optical coupling isolator,
485 bus modules connect, and optical coupling isolator is connected with relay module, signal transmitting device I, signal transmitting device II respectively, relay
Device module is connected with magnetic valve I, magnetic valve II, magnetic valve III, magnetic valve IV, magnetic valve V, vavuum pump and compressor respectively, letter
Number transmitter I is connected with proportioning valve module I, ratio valve module II respectively, described signal transmitting device II respectively with baroceptor
Ith, baroceptor II, baroceptor III, baroceptor IV connect, 485 bus modules respectively with computer interface, data
Memory interface, pressurize experimental arrangement upgrade interface, air pressure produce waveform interface, wireless transmission interface connects.
Human-computer interaction interface module responds the input request of operator, and sends it to control core circuit, controls core
The collection of electrocardio road is from the real time data of gas pressure sensor module, and passes through 485 bus marco relay module and proportioning valve mould
Block constitutes closed loop feedback system, finally controls output pressure.
Control core module includes single-chip microcomputer, power isolation circuit, interface and peripheral circuit.
485 bus modules include 485 bus chips, optical coupling isolation circuit, transient voltage suppression circuit.
Relay module includes high-current relay, optical coupling isolation circuit, level-conversion circuit.
Gas pressure sensor module includes sensor and its interface, sensor include baroceptor I, baroceptor II,
Baroceptor III, baroceptor IV, the interface of sensor is respectively iic bus and RS232 EBI.
Human-computer interaction interface module includes technical grade HMI touch-screen and its support circuit, and support circuit includes touching feedback
Circuit, control core circuit.
Power module includes 5V power module, 24V power module and 28V power module.
Ratio valve module includes high-frequency electromagnetic needle-valve, sensor circuit, drive circuit.
Air pump and gas path module include vavuum pump, compressor, magnetic valve, draining valve, choke valve and its supporting gas circuit, electromagnetism
Valve includes magnetic valve I, magnetic valve II, magnetic valve III, magnetic valve IV, magnetic valve V.
Human-computer interaction interface module adopts 8 inches of high graphics dot matrix screens that Di Wen company produces
DMT10768T080_07WT, ultimate resolution 1024*768, it carries capacitance touch screen, by programming to touch-control coordinate, permissible
Realize human-computer interaction function.
Control core module adopts the STM32F103VET6 microcontroller of ST company, has selected the embedded system of μ C/OS- II
The software platform that system is realized as code, operating frequency is 72MHz.
Ratio valve module adopts WFAS1TFEE045BXL the and WFAS1TFEE015BXL high-frequency electrical needle of ProALA company
Valve, it can control the flow of gas with ± 0.005% resolution precision ground.
Relay module adopts the SLA12VDC-SLA of SONGLE company, and the maximum current allowed reaches 10A, alternating voltage
Reach 250V.
Gas pressure sensor module includes two kinds, and a kind of is the RPT350 intelligence vibrating cylinder pressure transducer that GE company produces,
Its precision reaches ± 0.02%, and annual measurement stability drift is less than ± 0.015%；A kind of is that MEMA company produces
MS4525DO-DS3O015AP and MS4525DO-DS3O045AP piezoresistive silicon sensor, its response time is less than 1ms, can be right
Air pressure is quickly measured.
The control total core of RS485 is flowed in the MAX13487EESA half-duplex that 485 bus chips are produced using MAXIM company automatically
Piece, is operable with -40 DEG C to+85 DEG C temperature ranges, and transfer rate can reach 2Mbps.
Vavuum pump can reach 2kPa using the Vi120SV vavuum pump leaping refrigerant production, barometric minimum.
Using being newly the TC-20 series of compressor that sincere company produces, its maximum gas pressure can reach 400kPa to compressor.
Magnetic valve adopts the VT307-08 high-precision meter valve that STNC company produces, and can carry out the control of gas path on-off.
Gas circuit is connected as：1 mouthful of proportioning valve module I passes sequentially through magnetic valve I, displacement can and vacuum using gas circuit silicone tube
Pump connects, and displacement can is connected with draining valve by gas circuit silicone tube, and 2 mouthfuls of proportioning valve module I are led to successively using gas circuit silicone tube
Cross baroceptor I, baroceptor II, pressure buffer tank I are connected with Ps out splice going splice；
Compressor is connected with one end of choke valve by gas circuit silicone tube, and the other end of choke valve leads up to magnetic valve II
It is connected with 3 mouthfuls of proportioning valve module I, another road passes sequentially through magnetic valve IV, 3 mouthfuls of ratio valve module II and 1 mouthful, magnetic valve III
Gas circuit silicone tube between displacement can and magnetic valve I is connected, 2 mouthfuls of ratio valve module II pass sequentially through baroceptor III,
Baroceptor IV, magnetic valve V, pressure buffer tank II are connected with Pt out splice going splice.
Specifically being connected as of control core modular circuit, 4,6,8,10,12,14,16,18,20 pin of jtag interface are respectively
Ground connection, 2 pin and 1 pin connect and distinguish one end and the power supply+3.3V of connecting resistance R6, R7, R8, R9, another termination JTAG of resistance R6
3 pin of interface, resistance R7 connects 5 pin of jtag interface, and resistance R8 connects 7 pin of jtag interface, and resistance R9 connects 13 pin of jtag interface,
9 pin of jtag interface are grounded by resistance R10, and 3 pin of jtag interface connect 90 pin of STM32 single-chip microcomputer, and jtag interface 5 pin connects
77 pin of STM32 single-chip microcomputer, 7 pin of jtag interface connect 72 pin of STM32 single-chip microcomputer, and 9 pin of jtag interface connect STM32 single-chip microcomputer
76 pin, 13 pin of jtag interface connect 89 pin of STM32 single-chip microcomputer, and 15 pin of jtag interface connect the 14 of STM32 single-chip microcomputer respectively
Pin and switch S1, resistance R2, one end of electric capacity C5, the other end of another termination capacitor C5 of switch S1 and ground, resistance R2's is another
One termination power+3.3V, 23 pin of STM32 single-chip microcomputer pass sequentially through resistance R99, light emitting diode D2 ground connection, and 24 pin lead to successively
Cross resistance R98, light emitting diode D3 ground connection, 37 pin are grounded by resistance R3,12 pin, 13 pin parallel resistances R1, crystal oscillator Y1, crystal oscillator
2 pin of Y1 are grounded by electric capacity C1, and 1 pin of crystal oscillator Y1 is grounded by electric capacity C2, and 94 pin of STM32 single-chip microcomputer are connect by resistance R4
Ground, 19 pin are grounded by resistance R96, and 10 pin, 20 pin, 27 pin, 49 pin, 74 pin, 99 pin are grounded respectively, 11 pin, 28 pin, 50 pin,
75 pin, 100 pin meet power supply+3.3V, 8 pin and 9 pin parallel connection crystal oscillator Y2 respectively, and 2 pin of crystal oscillator Y2 are grounded by electric capacity C3, crystal oscillator Y2
1 pin be grounded by electric capacity C4,25 pin of STM32 single-chip microcomputer, 26 pin are connected with 3 pin of interface P98,2 pin respectively, 68 pin, 69
Pin is connected with 3 pin of interface P1,2 pin respectively, and 47 pin, 48 pin are connected with 3 pin of interface P4,2 pin respectively, and 78 pin, 79 pin are respectively
Connect with 2 pin of interface P99,3 pin, 1 pin of interface P98,1 pin of interface P1,1 pin of interface P4, the 4 pin difference of interface P99
Ground connection, 4 pin of interface P98,4 pin of interface P1,4 pin of interface P4,1 pin of interface P99 are grounded DCVCC respectively.Crystal oscillator Y2's
Model：32K768.
Control core modular circuit is its main operational part of system, the STM32F103VET6 chip adopting on hardware
For LQFP100 encapsulation, there is very high integration, pin reaches 100, memory reaches 512K, operating frequency frequency multiplication arrives
72MHz.The software platform that μ C/OS- II embedded system is realized is selected on software, it is to avoid monolithic flowing water journey as code
Sequence easily runs the shortcoming flying and crashing it is ensured that the chronicity of system operation and reliability.In control core modular circuit, fortune
One self-adaptive PID algorithm based on neutral net of row, can be according to the control instruction of operating personnel and gas pressure sensor module
Value of feedback, real-time adjustment PID controller parameter, and passing ratio valve module realize to gas circuit air pressure real-time control, follow finger
The effect of order.
Specifically being connected as of insulating power supply modular circuit, 2 pin of voltage-stablizer U2 and 4 pin connect the positive pole of electric capacity C9, electricity respectively
Hold C7, one end of resistance R90 and power supply+3.3V, 3 pin of voltage-stablizer U2 connect respectively the positive pole of electric capacity C8, one end of electric capacity C6, every
From 4 pin of power module P33, the other end of resistance R90 by light emitting diode D1 connect respectively the negative pole of electric capacity C9 and electric capacity C8,
1 pin of electric capacity C7, the other end of electric capacity C6 and voltage-stablizer U2 and ground, 2 pin of insulating power supply module P33 meet power supply+5V respectively, connect
2 pin of mouth P45,1 pin of interface P45 is connected with 2 pin of interface P22, and 1 pin of interface P22 connects 1 pin of insulating power supply module P33,
3 pin ground connection of insulating power supply module P33.The model of voltage-stablizer U2：ASM1117-33.
Insulating power supply module adopts the B0505SDC-DC modular converter that Jin Shengyang company produces, can be by the electricity of input
The power supply of source and ground and output end and ground physical isolation, so avoid the electrical module such as vavuum pump, compression due to system
The equipment such as machine operationally produce interference to the light current module of control core；Module possesses voltage stabilizing function simultaneously, in line voltage
When fluctuation, by stable for the supply voltage of controller module in normal value, circuit can be had about protection.
Specifically being connected as of 485 bus module circuit, 1 pin of chip U10 connects the 2 of photoelectrical coupler U24 by resistance R65
Pin, 2 pin and 3 pin one end of connecting resistance R69 and 4 pin of photoelectrical coupler U25 respectively, the 4 pin connecting resistance R60 respectively of chip U10
One end and photoelectrical coupler U26 4 pin, 5 pin of chip U10 meet 3 pin of photoelectrical coupler U26, photoelectrical coupler U25 respectively
3 pin and ground, 6 pin of chip U10 and 7 pin parallel resistances R66, transient state suppression diode D12, transient state suppresses diode D12 mono-
End is connected with 2 pin of interface PS by resistance R67, and transient state suppresses the other end of diode D12 to pass through resistance R68 and interface PS's
3 pin connect, and 8 pin of chip U10 connect 1 pin of photoelectrical coupler U24, resistance R69, the other end of resistance R60, photoelectric coupling respectively
The 3 pin ground connection of device U24,4 pin by resistance R62 connect 1 pin of photoelectrical coupler U25,1 pin of photoelectrical coupler U26 and power supply+
2 pin connecting resistance R63 one end of 3.3V, photoelectrical coupler U25,2 pin connecting resistance R64 one end of photoelectrical coupler U26.Chip U10
Model： U32MAX13487EESA.
485 bus modules are the main circuits of system transfers data, are control core modules, gas pressure sensor module, outer
The main circuit of the swapping data of portion's interface.Whether its function is intact, and whether the bit error rate is system energy in relatively low scope
The key of no normal work.Thus it is guaranteed that the reliability of data transfer and low bit error are circuit having to the feature that possesses.Using
Transient Suppression Diode, to suppress to disturb, eliminates the impact of other parts circuit, increases reliability.Employ high speed photo coupling every
From device by the circuit of controller module and 485 data transmission circuit physical isolation, effectively reduce the bit error rate of data transfer.
Specifically being connected as of relay module circuit, the diode cathode of photo-coupler U1 passes through resistance R169A and interface
3 pin of P116 connect, and the diode cathode of photo-coupler U1 is connected with 1 pin of interface P116 by LED1, photo-coupler U1's
Transistor collector meets VCC, and emitter stage is connected with the base stage of triode Q1 by resistance R3, coils from parallel connection of coils two pole of relay K1
One end of negative pole connecting resistance R2A of pipe D0, diode D0 and VCC, the negative pole of diode D0 connects the current collection meeting triode Q1 respectively
Pole, the negative pole of LED2, the grounded emitter of triode Q1, the other end of the positive pole connecting resistance R2A of LED2, one of relay K1
Contact is connected with 1 pin of interface P28, and another contact of relay K1 is connected with 21 pin of interface P28.
Relay module operating current is larger, with optical coupling isolation circuit and with status indicator lamp, can be by single-chip microcomputer
3.3V vulnerabilities scan signal be changed into alternating current 220V break-make control.During system testing, control core module interior
The program of putting can control the working condition of the electrical equipments such as magnetic valve, vavuum pump, compressor by relay module.
In fig. 2, as a example with Ps (static pressure, static pressure) control, when the system is operating, magnetic valve I and electromagnetism
Front stage gas circuit can be separated by valve II, and the vavuum pump of prime gas circuit can provide higher vacuum (about 2kPa), and compressor can
To provide higher malleation (about 400kPa), therefore they can consume rapidly the gas of gas in proportioning valve rear class gas circuit
Pressure.
When the static pressure in Fig. 1 needs to increase, the proportioning valve I of respective line is opened, and magnetic valve I cuts out, magnetic valve
II opens, from compressor to pipeline in pressurize.The air flow rate of pressurization is subject to controlling of proportioning valve I, and therefore air pressure change rate can
With precise control；When air pressure needs to reduce, magnetic valve I is opened, and magnetic valve II cuts out, and extracts pipeline gas by vavuum pump
Body, realizes decompression and adjusts, the speed of decompression is controlled by proportioning valve II.
Control system adopts closed-loop feedback control system structure, and as shown in Figure 1 and Figure 2, method for designing includes three links：
Feedback element design, control algorithm design, actuator design.
A () feedback element adopts two kinds of sensors：In Fig. 2, baroceptor II and baroceptor IV utilize GE company
RPT350 aviation-grade vibration cylinder type other sensors, can make static system certainty of measurement reach ± 0.02%, annual measurement is steady
Qualitative drift is less than ± 0.015%, fullys meet the requirement of aircraft pitot-static pressure test system, baroceptor I He in Fig. 2
Baroceptor III utilizes MS4525DO-DS3O015AP the and MS4525DO-DS3O045AP silicon piezoresistance type sensing of MEMA company
Device, its response time is less than 1ms, and air pressure quickly can be measured.Two kinds of sensors respectively test equipment static state and
In dynamic testing process use, not only high precision and also measuring speed is fast.After sensor access system, in real time, automatically pick up
Current atmospheric pressure value, the sensor is accessed STM32 microcontroller respectively in the way of IIC and RS232 bus, works as microcontroller
After device recognizes sensor access, you can start gathered data.
The design of (b) pid control algorithm：In the microcontroller, pid control algorithm is designed with the method for software, enter first
The determination of row initial parameter, after completing, determines proportional component, the differential ring of PID online in real time by self-adaptive PID method
Section, the parameter of integral element, the output of control algolithm, through RS485 bus module, accesses proportional valve driving gear, drives ratio
High-frequency electromagnetic needle-valve within valve module is adjusted to pressure.
During initial regulation parameter, first have to adjust scale parameter, when control effect is more satisfactory, do not occurred
When degree vibration or control time are long, then adjust integration and differential parameter；If scale parameter too conference causes system to shake
Swing overlong time, too little result in the rise time oversize it is therefore desirable to scale parameter is adjusted to first the feelings of system slightly concussion
Condition, is adjusted with differential and integral parameter afterwards again；Increase integral parameter can accelerate to eliminate steady-state error；Differential parameter exists
First should be less during regulation, then incrementally increase, minimizing system ripple, the effect of enhancing damping can be reached.When initial
After parameter determination, P, I, D parameter of system is just no longer changed by designer, but by adaptive neural network method according to being
System error calculates in real time,
(c) executing agency：Executing agency is ratio valve module, including high-frequency electromagnetic needle-valve, sensor circuit, drives electricity
Road module, high-frequency electromagnetic needle-valve adopts the high-frequency electromagnetic needle-valve of ProALA company, and it can be with ± 0.005% resolution precision
Ground controls the flow of gas, energising and power-off response time to be respectively 1.0ms and 0.5ms；Sensor circuit adopts Honeywell
The CAFS3000 type flow sensor of company；Drive circuit module is mainly by the high frequency relay G6K2P module of Omron Corp
Composition, can be with the break-make of the FREQUENCY CONTROL high-frequency electromagnetic valve of 150Hz.The flow adjustment range of ratio valve module be 0～
100mL/min, meets the sets requirement to height and air speed rate of change for the test equipment.
Control instruction is converted to the standard signal of 4～20mA, the equivalent aperture of corresponding high-frequency electromagnetic needle-valve by driving means
For 0～100%, when aperture is different, gas flow is of different sizes, in driving means, instruction is carried out with stack design, rejects wrong
Instruction, retains correct instruction by mistake, drives high-frequency electromagnetic needle-valve to move.
The control algolithm that the utility model uses is Adaptive PID Control algorithm.Static prestressed-pile in the utility model is calculated
Method and total head control algolithm all using adaptive Neural Network PID, the gas that controlled due to Static prestressed-pile and total head
Road is basically identical, and the control algolithm of therefore two gas circuits and its parameter are also consistent.This pid algorithm is to operate in control core module
Software algorithm, the condition of this algorithm performs is：When tester presses " Enter " button on Touch Screen, and correctly
Have input operational order.The function of this algorithm is；By the real-time data calculating gas pressure sensor module feedback, by itself and test
The input instruction of personnel compares, and according to the size of deviation, the gas flow of real-time adjustment passing ratio valve module, and finally makes
Stable gas pressure in test gas circuit is in the input value of tester.After algorithm brings into operation, algorithm can be automatically by controlling
Nucleus module is calculated, without manual intervention in whole test process.
Pid control algorithm mainly has position model and two kinds of increment type, and increment type PID is used for the feelings that controlled quentity controlled variable is system increment
Condition, if Δ u is the increment of controlled quentity controlled variable, KP、KI、KDFor proportional component, integral element, differentiation element coefficient, e (k) be the k moment
Command signal and the deviation feeding back signal, Δ e (k) is the knots modification of this error signal, then have equation below：
Δ u=KPΔe(k)+KIe(k)+KD[Δe(k)-Δe(k-1)]
The advantage of the increment type control algolithm that the utility model adopts is：
(1) due to computer export increment, therefore in operation, misoperation is less, and being judged using certain logic threshold can
So that mistake to be removed；
(2) when manually, automatically switching, impact is less, when computer breaks down, due to maintaining the lock of original signal
Deposit effect, therefore, it is possible to remain in that initial value.
The adaptive approach that the utility model adopts is Neural Network PID, adaptive Neural network PID control
Algorithm processed can be calculated according to the atmospheric pressure value of gas pressure sensor module feedback in real time by the neutral net shown in Fig. 4,
By state converter and learning algorithm, on-line control pid parameter, according to current air pressure and atmospheric pressure trends, to control
The parameter of algorithm processed is modified.
Pid control algorithm structure based on neutral net is as shown in figure 4, wherein xiFor calculating the deviation of gained, wiFor each
The weights of deviation.
The input In of neuron is：
The output Δ u of neuron is：
Δ u=f (In)
Then output Δ u (k) of k moment controller can be write as：
Δ u (k)=w1x1+w2x2+w3x3
Formula by digital incremental PID
Δ u (k)=Kp[e(k)-e(k-1)]+Kie(k)+Kd[e(k)-2e(k-1)+e(k-2)]
Then can take
x1=e (k)-e (k-1), x2=e (k), x3=e (k) -2e (k-1)+e (k-2)
Then
Δ u (k)=w1[e(k)-e(k-1)]+w2e(k)+w3[e(k)-2e(k-1)+e(k-2)]
Wherein wiWeight coefficient learning rules be neuron control method core, here, system has employed supervision
Hebb learning algorithm,
Can be obtained by above formula, output u (k) of k moment controller is：
The weights learning rule that the utility model adopts is as follows：
ηp、ηI、ηDThe ratio of being respectively, differential, the learning rate of integration, K is neuron proportionality coefficient.
In formula, the method employing neutral net is to wiWeights be adjusted, when system load changes, or introduce
After new interference, in real time weights can be adjusted according to load, there is very strong adaptability, therefore just because of
Employ this adaptive method so that higher adaptability is had based on the pid control algorithm of neutral net, enhance control
The robustness of algorithm processed.
Tri- parameters of PID are mainly relevant with e (k) and Δ e (k), algorithm can be written as equation below：
Wherein, u (k+1) is the output in k+1 moment, and u (k) is the output in k moment, for controlling ratio valve module, Δ u
K () is the output increment in k moment, K is neuron proportionality coefficient, is that constant depends primarily on systematic parameter, in the utility model
In, value is 2.32；wiFor the weights of each deviation, ηp、ηI、ηDThe ratio of being respectively, differential, the learning rate of integration, in this reality
In new, be identified as 1.862 by debugging, 0.678,1.273, e (k), Δ e (k) be k moment gas pressure sensor module
Deviation between the air pressure desired value of the atmospheric pressure value of feedback and current tester input.
As shown in Figure 5, Figure 6, control core employs is anticipated by Europe for the control core of this example and its insulating power supply circuit
What method semiconductor (STMicroelectronics) produced a requires high-performance, low one-tenth based on aiming at of ARM Cortex-M3
Originally, the custom-designed 32 Flash type microcontrollers of Embedded Application of low-power consumption.It collects high-performance, real-time function, numeral letter
Number process, the characteristic such as low-power consumption and low voltage operating, also maintain integrated level high and be easy to the feature developed simultaneously.Adopt
STM32F103VET6 chip is LQFP100 encapsulation, and pin reaches 100, and memory reaches 512K, operating frequency frequency multiplication
To 72MHz, highest arithmetic speed reaches 1.25DMips/MHZ.Support hardware multiplication, support that CAN interface, USB2.0 are complete
Fast interface, it is possible to achieve the Lossless Compression of data and process, reduces the bandwidth of data path, is fully able to meet test equipment
Requirement.Using 5 whole UART ports, 2 IIC ports, equipment carries out data interaction to this example to external world, and CRC is hard
Part computing unit verifies to data.
Employ two pieces of STM32 single-chip microcomputers in this example, be respectively completed man-machine interaction task and core control task, with
Down referred to as " human-computer interaction interface module " and " control core module ".Screen board is carried out using common hardware platform with core board
Design, so can strengthen versatility, improve design efficiency.
" human-computer interaction interface module ", as shown in figure 9, needing to complete some man-machine interworkings, mainly has following side
Face：
1st, liquid crystal touch screen is controlled to carry out numeral and its graphic software platform, including touchscreen commands identification, the work(such as parameter instruction
Can, interactive device employs 8 inch touchscreen of Beijing Di Wen company production；
2nd, instruction calculates, and the control parameter being obtained reality by control instruction is a complex process, because this is
The involved number of parameters of system is more, and has close crosslinked relation between parameter, needs to be joined by special program
Number resolves and descending control；
3rd, ADM module testing, needs to carry out Data Collection and housekeeping to the ADM being tested, realizes LRU (Line
Replaceable Unit, Line Replaceable Module) full-automatic testing；
4th, sensor calibration and computer end interface service, screen version needs the communications status of monitoring and core board, and is electricity
Brain end provides the good communication protocol based on 485 buses to carry out ipc monitor.
The task that " control core module " completes is increasingly complex, mainly has the following aspects：
1st, data acquisition and interaction：Carry out data interaction with screen version, receive the setting signal from screen, simultaneously for screen
Curtain display provides data source, and state current for system is collected giving screen display again；
2nd, run the self-adaptive PID algorithm of an increment type, real-time control is carried out to equipment, realizes the closed loop control of system
System；
3rd, using 3 road serial ports, 2 pressure transmitters, 2 flow valves are controlled, two of which pressure transmitter is multiplexed
One passage, the instruction output that algorithm is calculated in real time is controlled；
4th, provide I/O interface for equipment, the switch order of manual control zone is responded, provide for ADM test corresponding
Driving source, and gather the response signal of ADM and be analyzed；
5th, run the Mathematical Modeling of all parameter calculations, resolved by basic static pressure and total head and obtain height, air speed, Mach
The information such as number；Calculate with the instruction of screen version and combine, the precise control of complete paired systems and display.
485 bus modules, as shown in fig. 7, realize " control core module ", " human-computer interaction interface module ", proportioning valve mould
Data exchange between block, for bus, different circuit boards is simply articulated in " equipment " in bus, each equipment
Before transmitting data, bus will be first listened to whether occupied, if occupied, need time delay to be transmitted again.Interface
Joint, using conventional nine kinds of needles serial line interface, increases versatility.Bus protocol chip adopts American TI Company
Sn65hvd3088e chip.Meet TIA/EIA-485A standard, (0.3mA under working condition, under Disconnected mode for low speed paper tape reader static power disspation
1nA), 256 nodes are at most driven.Unrepeatered transmission distance reaches 1200 meters.Circuit passes through to suppress two using TVS transient voltage
Pole pipe is reducing the impact to circuit for the glitch such as electromagnetism, electrostatic.Additionally use PS2801 chip in the design as optocoupler
Isolation circuit, the reliability of strengthening system, make signal one-way transmission, input and output end fully achieve electrical isolation, defeated
Going out signal no affects on input, strong antijamming capability, working stability.
Relay module, as shown in figure 8, using up to 20 in the utility model, pump, the control of these switching values of valve
It is required for using relay, relay also needs to the switch of manual operating space is responded accordingly simultaneously, therefore designs
Reliable relay module is extremely important.Because needing in system powerful device is controlled, such as vacuum pump power is
180W, has therefore selected the high power relay of 250V10A.Adopt the method for designing of light-coupled isolation in the same manner, by P116 interface
It is directly connected to the control end of single-chip microcomputer, this prevents the impact to prime for the rear class equipment.The effect of triode Q21 is mainly
Strengthen the driving force of optical coupling module, prevent from causing the situation that relay is not turned on to occur due to driving current deficiency.Simultaneously
So design also gives circuit certain flexibility, when VCC voltage is different, can adjust light by changing the resistance of R170
The driving force of coupling.
Gas circuit and air pump module are made up of gas circuit, vavuum pump, compressor, magnetic valve, gas circuit and its accessory, as shown in Figure 2.
Air pump, magnetic valve are connected to relay module, the digital output modul being provided by control core module.Gas circuit adopts external diameter 8 milli
Rice, the high leakproofness silicon special sebific duct of 5 millimeters of internal diameter, good sealing can be provided for system；Vavuum pump is cold using leaping
The Vi120SV vavuum pump that matchmaker produces, barometric minimum can reach 2kPa；Compressor is using the TC-20 system being newly the production of sincere company
Row compressor, its maximum gas pressure can reach 400kPa；Magnetic valve includes magnetic valve I, magnetic valve II, magnetic valve III, magnetic valve
IVth, draining valve, the VT307-08 high-precision meter valve all being produced using STNC company, the control of gas path on-off can be carried out,
The utility model adopts Lange Omnifit series S type and p-type joint, is crimped using specialist tools butt joint,
The air-tightness of guarantee system and the repeatability of construction.The out splice going splice of gas circuit is Ps out splice going splice and Pt out splice going splice, corresponding
S23 adapter and P23 adapter can be respectively connected to static-pressure system and the total head system of aircraft, and ensure that and connect during test
Situations such as be not in gas pressure leak at head.In the gas pressure buffer tank of 3L volume, primarily to avoiding in test process
Central emergency case, leads to the air pressure in gas circuit to be undergone mutation, and then damages the situation of aero pilot-static pressure system sensor
Occur, pressure buffer tank can efficiently reduce the pulsation air pressure interference phenomenon in gas circuit.
Gas pressure sensor module accesses whole gas circuit, main inclusion：Baroceptor I and baroceptor III employ GE
The RPT350 intelligence vibrating cylinder pressure transducer that company produces, its precision reaches ± 0.02%, baroceptor II and air pressure transmission
Sensor IV employs MS4525DO-DS3O015AP the and MS4525DO-DS3O045AP silicon piezoresistance type sensing of MEMA company production
Device, its response time is less than 1ms.
Ratio valve module as shown in Figure 10, is made up of high-frequency electromagnetic needle-valve, sensor circuit, drive circuit；High-frequency electromagnetic
Needle-valve adopts the high-frequency electromagnetic needle-valve of ProALA company, and it can control the stream of gas with ± 0.005% resolution precision ground
Amount, energising and power-off response time are respectively 1.0ms and 0.5ms；Sensor adopts the CAFS3000 type stream of Honeywell Inc.
Quantity sensor；Drive circuit module is mainly made up of the high frequency relay G6K2P module of Omron Corp, can be with 150Hz's
The break-make of FREQUENCY CONTROL high-frequency electromagnetic valve.The flow adjustment range of ratio valve module is 0～100mL/min, meets test and sets
The standby sets requirement to height and air speed rate of change.
Described power module produces the power supply of various needs, its technical indicator：
1st, output area：5V 0～26A 5 road power 150W
Output voltage precision：± 2%, ripple is less than 80mV
Efficiency：78%
Input range：88～132VAC or 180～264VAC, maximum inrush current 40A
Voltage adjusting range：± 10%
Overload protection, overvoltage protection, start the rise time less than 1s
2nd, output area：24V 0～4A 3 road power 32W
Output voltage precision：± 2%, ripple is less than 80mV
Efficiency：80%
Input range：85～264VAC, maximum inrush current 45A
Voltage adjusting range：- 5%～10%
Overload protection, overvoltage protection, start the rise time less than 500ms
3rd, output area：28V 0～10.7A 2 road power 300W
Output voltage precision：± 3%, ripple is less than 90mV
Efficiency：83%
Input range：125～252VAC, maximum inrush current 48A
Voltage adjusting range：- 5%～7%
Overload protection, overvoltage protection, start the rise time less than 900ms.
Carry out on the mainly shown in figure 3 guidance panel of the test operation of aircraft pitot-static pressure test system, in Fig. 3,
101. is Power Supply Monitoring operating space, and 102. is manually operated area, and 103. is air pressure output interface area, the P23 in corresponding Fig. 2 and
S23 gas circuit output interface, every kind of interface provides three kinds of different connected modes, and 104 is human-computer interaction module operating space, and 105 are
Analog quantity test section after assembly access, 106 is bailout gas input interface, after internal system origin fault, can adopt
Using equipment, 107 is valve body instruction and jerk operating space to the mode of external bailout gas, and 108 is antistatic wrist strap access area.
As shown in figure 11, embedded software structure is as shown in figure 12 for each operating procedure of aircraft pitot-static pressure test system：
The first step：Start；Power supply in Fig. 1 starts to power, electricity on vavuum pump and compressor, and tester can be by figure
Equipment is opened in Power Supply Monitoring operating space in 1；By the air pressure output interface area in Fig. 1, system access S23 and P23 is adapted to
Device；Wear antistatic wrist strap, access the antistatic wrist strap access area in Fig. 1；
Second step：Carry out self-inspection, system initialization, embedded software application computing resource, opens interrupters simultaneously wait instruction；
Baroceptor I in Fig. 2 and baroceptor II gather atmospheric pressure value in pipeline respectively, are entered by the control core module in Fig. 1
Row self-inspection, it is to avoid the danger of gas circuit pressure fluctuations；Embedded software in Figure 12 carries out computing resource application；
3rd step：Equipment user of service utilizes the human-computer interaction interface module in Fig. 1 to input height, altitude rate, sky
Several parameters such as speed, air speed rate of change, input operation human-computer interaction module operating space in FIG is carried out, using hommization
Touch-screen input mode, meets the operating habit of most people；
4th step：Carry out self-inspection, whether instruction input is correct？
5th step：Correctly, instruction enters parsing link；
6th step：Incorrect, instruction re-starts input；
7th step：Control core module in Fig. 1 is changed to instruction and is parsed, and is converted into 4～20mA letter of standard
Number form；
8th step：The process of execute instruction is：If have input height and altitude rate data, and height is needed to increase
Or during air pressure reduction, the magnetic valve I in Fig. 2 is opened, and magnetic valve II cuts out, vacuum pump work, by the gas in Ps static line
Extract out；By operating in the self-adaptive PID algorithm on software, Real-time Collection is derived from the number of sensor assembly to control core module
According to, the real-time, parameter of adjust automatically pid algorithm, the signal transmitting in Fig. 1 is passed through by the calculated output order of pid algorithm
Ratio valve module 1 sent into by device, and the ratio valve module 1 in Figure 10, according to signal, adjusts the start of high-frequency electromagnetic needle-valve G6K2P, changes
Variable-flow, controls the size of altitude rate；
If have input height and altitude rate data, and need height reduction or air pressure increase constantly, the electricity in Fig. 2
Magnet valve I is closed, and magnetic valve II is opened, compressor operating, squeezes into gas in Ps static line, the ratio valve module root in Figure 10
According to the self-adaptive PID algorithm operating in control core module, calculate control signal in real time, adjust high-frequency electromagnetic needle-valve G6K2P
Start, change flow, control altitude rate size.If have input air speed and air speed rate of change data, implementation procedure
Similar with said process.
9th step：Whether set out stop command？
Tenth step：It is then to terminate this secondary program；The instruction of emergent stopping can be by the valve body instruction in Fig. 3 and jerk
Operating space is operated, if scram button is pressed, the magnetic valve I in Fig. 2, magnetic valve II, magnetic valve III, magnetic valve IV
Close, it is to avoid gas enters rear class and damages sensor and proportioning valve.
11st step：No, start to gather the atmospheric pressure value of baroceptor II and baroceptor IV in Fig. 2；
12nd step：The baroceptor II of continuous collecting and baroceptor IV numerical value, until completing control instruction
13rd step：Whether control core module check reaches desired value？
14th step：It is to terminate
15th step：Otherwise re-execute instruction
The test that aircraft pitot-static pressure test system can be carried out has two kinds, can be wanting of aircraft maintenance handbook according to AMM
The pitot-static pressure system seeking the aircraft to aircraft Flight Line Maintenance is tested, and test assignment number is Task-34-11-00-790-804,
Can also test according to the ADM Air Data Module that the requirement that CMM is aircraft components maintenance handbook is keeped in repair to aircraft internal field,
Module piece number is：S242W601-100.Testing process is as follows：
1st, carry out the operation of this air pressure equalisation, click on CAL button, make device interior air pressure consistent with Current terrestrial air pressure；
Now the magnetic valve I in Fig. 2, magnetic valve II, magnetic valve III, magnetic valve IV, magnetic valve V are all opened it is ensured that internal duct can
With local atmosphere；
2nd, static line, total head pipeline are connected, respectively using adapter S23 and P23 in Fig. 2, by equipment and aircraft
Static line, total head pipeline couple together, the drainage interface in closing pipe line, closing choke valve, and control core module can be certainly
Dynamic closing magnetic valve I～V；
3rd, pass through Fig. 2 in human-computer interaction interface module touch-screen, selection unit be hPa, m (km/h), ft (knts,
Ma one of), Ps, Pt, RtPs, RtPt are inputted respectively by touch control keyboard it is desirable to：Pressure in static line can not be more than
Pressure in dynamic pressure pipeline；The static line pressure limit 3.26-33.31 inch of mercury；Static line maximum pressure with ambient atmosphere
Differ from 28 inches of mercury；The dynamic pressure pipeline pressure limit 3.26-41.34 inch of mercury；Dynamic pressure pipeline and static line maximum differential pressure 10
The inch of mercury；Maximum 5000 feet/min of altitude rate；Percentage speed variation maximum 300 sections/minute；
4th, selection test is one of system testing (acquiescence selects), loop test, single stepping test, leakage test, point
Hit Enter button to start to test；In test process, the operation such as test can be selected to suspend, continue by touch controlled key；
In the system testing of acquiescence, if having input height and altitude rate data, and height is needed to increase or gas
When pressure reduces, the magnetic valve I in Fig. 2 is opened, and magnetic valve II cuts out, vacuum pump work, and the gas in Ps static line is extracted out；
By operating in the self-adaptive PID algorithm on software, Real-time Collection is derived from the data of sensor assembly, real-time, adjust automatically PID
The parameter of algorithm, sends into ratio valve module 1, the ratio in Figure 10 by the calculated output signal of pid algorithm by transmitter
Valve module, according to signal, adjusts the start of high-frequency electromagnetic needle-valve G6K2P, changes flow, controls the size of altitude rate；
If have input height and altitude rate data, and when needing height reduction or air pressure to increase, the electromagnetism in Fig. 2
Valve I cuts out, and magnetic valve II is opened, compressor operating, squeezes into gas in Ps static line, the ratio valve module in Figure 10 according to
Operate in the self-adaptive PID algorithm in control core module, calculate control signal in real time, adjust high-frequency electromagnetic needle-valve G6K2P's
Start, changes flow, controls the size of altitude rate.If have input air speed and air speed rate of change data, implementation procedure with
Said process is similar to.
In loop test, tester can store system testing process before it is only necessary to a key resets, and equipment is
New testing process can be restarted, reset without tester；In single stepping test, tester needs according to touch
Screen prompting, often completes a step, all clicks on " next step ", and system can proceed to test.
In revealing test, control core module can be automatically switched off the magnetic valve I～V in Fig. 2, open choke valve simultaneously
And draining valve, according to the testing time of tester's setting, it is defaulted as 1 minute, control core module starts automatic data collection air pressure
The value of sensor II and baroceptor IV is simultaneously recorded, and after the time arrives, calculates the leakage of system under test (SUT) in the testing time
Rate, shows on human-computer interaction interface simultaneously.
5th, after test terminates, click on pressure release button, now, control core module can automatically calculate atmospheric pressure value in pipeline with
The difference of local atmospheric pressure value, locally air pressure is consistent to control proportioning valve I with II module, pipeline internal gas pressure to be adjusted to the external world, makes entirely quiet
Pressure in pressure pipe road discharges, and after waiting air pressure instruction stable, system is automatically switched off draining valve and choke valve, and tester needs
S23 and P23 adapter to be taken off, pass hull closure completes to test.
As equipment runs into fault in test, emergency stop switch can be adopted, urgent interrupt be carried out to test process, when jerk is opened
When closing, the magnetic valve I in Fig. 2, magnetic valve II, magnetic valve III, magnetic valve IV are closed, it is to avoid gas enters rear class and damages biography
Sensor and proportioning valve.
Claims (5)
1. a kind of aircraft pitot-static pressure test system based on self-adaptive PID method it is characterised in that：Including control core module,
Power module, insulating power supply module, optical coupling isolator, 485 bus modules, relay module, signal transmitting device I, signal transmitting
Device II, proportioning valve module I, ratio valve module II, human-computer interaction interface module, baroceptor I, baroceptor II, air pressure
Sensor III, baroceptor IV, magnetic valve I, magnetic valve II, magnetic valve III, magnetic valve IV, magnetic valve V, vavuum pump and pressure
Contracting machine, described power module is led up to insulating power supply module and is connected with control core module, human-computer interaction interface module respectively,
Another road is connected with vavuum pump and compressor respectively, described control core module respectively with human-computer interaction interface module, optocoupler every
From device, 485 bus modules connect, described optical coupling isolator respectively with relay module, signal transmitting device I, signal transmitting device II
Connect, described relay module respectively with magnetic valve I, magnetic valve II, magnetic valve III, magnetic valve IV, magnetic valve V, vavuum pump and
Compressor connects, and described signal transmitting device I is connected with proportioning valve module I, ratio valve module II respectively, described signal transmitting device II
It is connected with baroceptor I, baroceptor II, baroceptor III, baroceptor IV respectively, described 485 bus modules
Produce waveform interface, be wirelessly transferred with computer interface, data memory interface, pressurize experimental arrangement upgrade interface, air pressure respectively
Interface connects；
Described control core module includes single-chip microcomputer, power isolation circuit, interface and peripheral circuit；
485 described bus modules include 485 bus chips, optical coupling isolation circuit, transient voltage suppression circuit；
Described relay module includes high-current relay, optical coupling isolation circuit, level-conversion circuit；
Gas pressure sensor module includes sensor and its interface；Sensor includes baroceptor I, baroceptor II, air pressure
Sensor III, baroceptor IV, the interface of sensor is respectively iic bus and RS232 EBI；
Described human-computer interaction interface module includes technical grade HMI touch-screen and its support circuit, and support circuit includes touching instead
Current feed circuit, control core circuit；
Described power supply includes 5V power module, 24V power module and 28V power module；
Described ratio valve module includes high-frequency electromagnetic needle-valve, sensor circuit, drive circuit；
Air pump and gas path module include vavuum pump, compressor, magnetic valve, draining valve, choke valve and its supporting gas circuit, magnetic valve bag
Include magnetic valve I, magnetic valve II, magnetic valve III, magnetic valve IV, magnetic valve V；
Human-computer interaction interface module responds the input request of operator, and sends it to control core circuit, control core electricity
Road collection is from the real time data of gas pressure sensor module, and passes through 485 bus module control relay modules and proportioning valve mould
Block constitutes closed loop feedback system, finally controls output pressure；
Human-computer interaction interface module adopts 8 inches of high graphics dot matrix screen DMT10768T080_ that Di Wen company produces
07WT, ultimate resolution 1024*768, it carries capacitance touch screen, by programming to touch-control coordinate, it is possible to achieve man-machine interaction
Function；
Control core module adopts the STM32F103VET6 microcontroller of ST company, has selected μ C/OS- II embedded system to make
The software platform realized for code, operating frequency is 72MHz；
Ratio valve module adopts WFAS1TFEE045BXL the and WFAS1TFEE015BXL high-frequency electromagnetic needle-valve of ProALA company, its
The flow of gas can be controlled with ± 0.005% resolution precision ground；
Relay module adopts the SLA12VDC-SLA of SONGLE company, and the maximum current allowed reaches 10A, and alternating voltage reaches
250V；
Gas pressure sensor module includes two kinds, and a kind of is the RPT350 intelligence vibrating cylinder pressure transducer that GE company produces, its essence
Degree reaches ± 0.02%, and annual measurement stability drift is less than ± 0.015%；A kind of is that MEMA company produces
MS4525DO-DS3O015AP and MS4525DO-DS3O045AP piezoresistive silicon sensor, its response time is less than 1ms, can be right
Air pressure is quickly measured；
Control RS485 bus chip is flowed in the MAX13487EESA half-duplex that 485 bus chips are produced using MAXIM company automatically, can
Work in -40 °C to+85 °C temperature ranges, transfer rate can reach 2Mbps；
Vavuum pump can reach 2kPa using the Vi120SV vavuum pump leaping refrigerant production, barometric minimum；
Using being newly the TC-20 series of compressor that sincere company produces, its highest air pressure can reach 400kPa to compressor；
Magnetic valve adopts the VT307-08 high-precision meter valve that STNC company produces, and can carry out the control of gas path on-off；
Gas circuit is connected as：1 mouthful of proportioning valve module I passes sequentially through magnetic valve I, displacement can and vavuum pump even using gas circuit silicone tube
Connect, displacement can is connected with draining valve by gas circuit silicone tube, 2 mouthfuls of proportioning valve module I pass sequentially through gas using gas circuit silicone tube
Pressure sensor I, baroceptor II, pressure buffer tank I are connected with Ps out splice going splice；
Compressor is connected with one end of choke valve by gas circuit silicone tube, the other end of choke valve lead up to magnetic valve II with than
3 mouthfuls of connections of example valve module I, another road passes sequentially through magnetic valve IV, 3 mouthfuls of ratio valve module II and 1 mouthful, magnetic valve III and row
Gas circuit silicone tube between water pot and magnetic valve I connects, and 2 mouthfuls of ratio valve module II pass sequentially through baroceptor III, air pressure
Sensor IV, magnetic valve V, pressure buffer tank II are connected with Pt out splice going splice.
2. a kind of aircraft pitot-static pressure test system based on self-adaptive PID method according to claim 1, its feature exists
In：Specifically being connected as of described control core modular circuit, 4,6,8,10,12,14,16,18,20 pin of jtag interface are respectively
Ground connection, 2 pin and 1 pin connect and distinguish one end and the power supply+3.3V of connecting resistance R6, R7, R8, R9, another termination JTAG of resistance R6
3 pin of interface, resistance R7 connects 5 pin of jtag interface, and resistance R8 connects 7 pin of jtag interface, and resistance R9 connects 13 pin of jtag interface,
9 pin of jtag interface are grounded by resistance R10, and 3 pin of jtag interface connect 90 pin of STM32 single-chip microcomputer, and jtag interface 5 pin connects
77 pin of STM32 single-chip microcomputer, 7 pin of jtag interface connect 72 pin of STM32 single-chip microcomputer, and 9 pin of jtag interface connect STM32 single-chip microcomputer
76 pin, 13 pin of jtag interface connect 89 pin of STM32 single-chip microcomputer, and 15 pin of jtag interface connect the 14 of STM32 single-chip microcomputer respectively
Pin and switch S1, resistance R2, one end of electric capacity C5, the other end of another termination capacitor C5 of switch S1 and ground, resistance R2's is another
One termination power+3.3V, 23 pin of STM32 single-chip microcomputer pass sequentially through resistance R99, light emitting diode D2 ground connection, and 24 pin lead to successively
Cross resistance R98, light emitting diode D3 ground connection, 37 pin are grounded by resistance R3,12 pin, 13 pin parallel resistances R1, crystal oscillator Y1, crystal oscillator
2 pin of Y1 are grounded by electric capacity C1, and 1 pin of crystal oscillator Y1 is grounded by electric capacity C2, and 94 pin of STM32 single-chip microcomputer are connect by resistance R4
Ground, 19 pin are grounded by resistance R96, and 10 pin, 20 pin, 27 pin, 49 pin, 74 pin, 99 pin are grounded respectively, 11 pin, 28 pin, 50 pin,
75 pin, 100 pin meet power supply+3.3V, 8 pin and 9 pin parallel connection crystal oscillator Y2 respectively, and 2 pin of crystal oscillator Y2 are grounded by electric capacity C3, crystal oscillator Y2
1 pin be grounded by electric capacity C4,25 pin of STM32 single-chip microcomputer, 26 pin are connected with 3 pin of interface P98,2 pin respectively, 68 pin, 69
Pin is connected with 3 pin of interface P1,2 pin respectively, and 47 pin, 48 pin are connected with 3 pin of interface P4,2 pin respectively, and 78 pin, 79 pin are respectively
Connect with 2 pin of interface P99,3 pin, 1 pin of interface P98,1 pin of interface P1,1 pin of interface P4, the 4 pin difference of interface P99
Ground connection, 4 pin of interface P98,4 pin of interface P1,4 pin of interface P4,1 pin of interface P99 are grounded DCVC respectively；The type of crystal oscillator Y2
Number it is：32K768.
3. a kind of aircraft pitot-static pressure test system based on self-adaptive PID method according to claim 1, its feature exists
In：Specifically being connected as of described insulating power supply modular circuit, 2 pin of voltage-stablizer U2 and 4 pin connect the positive pole of electric capacity C9, electricity respectively
Hold C7, one end of resistance R90 and power supply+3.3V, 3 pin of voltage-stablizer U2 connect respectively the positive pole of electric capacity C8, one end of electric capacity C6, every
From 4 pin of power module P33, the other end of resistance R90 by light emitting diode D1 connect respectively the negative pole of electric capacity C9 and electric capacity C8,
1 pin of electric capacity C7, the other end of electric capacity C6 and voltage-stablizer U2 and ground, 2 pin of insulating power supply module P33 meet power supply+5V respectively, connect
2 pin of mouth P45,1 pin of interface P45 is connected with 2 pin of interface P22, and 1 pin of interface P22 connects 1 pin of insulating power supply module P33,
3 pin ground connection of insulating power supply module P33；The model of voltage-stablizer U2：ASM1117-33.
4. a kind of aircraft pitot-static pressure test system based on self-adaptive PID method according to claim 1, its feature exists
In：Specifically being connected as of 485 described bus module circuit, 1 pin of chip U10 connects photoelectrical coupler U24's by resistance R65
2 pin, 2 pin and 3 pin one end of connecting resistance R69 and 4 pin of photoelectrical coupler U25 respectively, the 4 pin connecting resistance R60 respectively of chip U10
One end and photoelectrical coupler U26 4 pin, 5 pin of chip U10 meet 3 pin of photoelectrical coupler U26, photoelectrical coupler U25 respectively
3 pin and ground, 6 pin of chip U10 and 7 pin parallel resistances R66, transient state suppression diode D12, transient state suppresses diode D12 mono-
End is connected with 2 pin of interface PS by resistance R67, and transient state suppresses the other end of diode D12 to pass through resistance R68 and interface PS's
3 pin connect, and 8 pin of chip U10 connect 1 pin of photoelectrical coupler U24, resistance R69, the other end of resistance R60, photoelectric coupling respectively
The 3 pin ground connection of device U24,4 pin by resistance R62 connect 1 pin of photoelectrical coupler U25,1 pin of photoelectrical coupler U26 and power supply+
2 pin connecting resistance R63 one end of 3.3V, photoelectrical coupler U25,2 pin connecting resistance R64 one end of photoelectrical coupler U26；Chip U10
Model：U32MAX13487EESA.
5. a kind of aircraft pitot-static pressure test system based on self-adaptive PID method according to claim 1, its feature exists
In：Specifically being connected as of described relay module circuit, the diode cathode of photo-coupler U1 passes through resistance R169 A and connects
3 pin of mouth P116 connect, and the diode cathode of photo-coupler U1 is connected with 1 pin of interface P116 by LED1, photo-coupler U1
Transistor collector meet VCC, emitter stage is connected with the base stage of triode Q1 by resistance R3, the coils from parallel connection of coils two of relay K1
Pole pipe D0, one end of negative pole connecting resistance R2A of diode D0 and VCC, the negative pole of diode D0 connects the collection meeting triode Q1 respectively
Electrode, the negative pole of LED2, the grounded emitter of triode Q1, the other end of the positive pole connecting resistance R2A of LED2, the one of relay K1
Individual contact is connected with 1 pin of interface P28, and another contact of relay K1 is connected with 21 pin of interface P28.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620618789.1U CN205940903U (en) | 2016-06-20 | 2016-06-20 | Full static pressure test system of aircraft based on self -adaptation PID method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620618789.1U CN205940903U (en) | 2016-06-20 | 2016-06-20 | Full static pressure test system of aircraft based on self -adaptation PID method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205940903U true CN205940903U (en) | 2017-02-08 |
Family
ID=57933440
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620618789.1U Expired - Fee Related CN205940903U (en) | 2016-06-20 | 2016-06-20 | Full static pressure test system of aircraft based on self -adaptation PID method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205940903U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104208A (en) * | 2019-05-09 | 2019-08-09 | 中国飞机强度研究所 | A kind of air inflation discharging control device |
-
2016
- 2016-06-20 CN CN201620618789.1U patent/CN205940903U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104208A (en) * | 2019-05-09 | 2019-08-09 | 中国飞机强度研究所 | A kind of air inflation discharging control device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105973544B (en) | A kind of aircraft pitot-static pressure test system and method based on self-adaptive PID method | |
| CN103207336B (en) | Lightning arrester operation analog simulation system | |
| CN106772008B (en) | Pressure-controllable SF6 gas density relay signal simulation tester | |
| CN108572054A (en) | A kind of intermittent wind tunnel simulation experiment method and device | |
| CN110525698A (en) | Test macro and test method for space capsule pressure guard system | |
| CN205940903U (en) | Full static pressure test system of aircraft based on self -adaptation PID method | |
| CN202255802U (en) | Airtight pressurization test set for cabin | |
| CN109828553A (en) | A kind of air data computer detection system | |
| CN202350878U (en) | Automatic checking device for flow meter | |
| CN103344499B (en) | Passenger plane fuselage pressure and tightness test equipment | |
| CN209203616U (en) | A kind of animal experimental chamber and its system | |
| CN101169634A (en) | Machine-mounted apparatus power supply detecting bench | |
| CN209625405U (en) | A kind of gas leakage detection warning instrument | |
| CN201812005U (en) | Performance test box and performance test system for analogue input/output (AI/O) module | |
| CN209167486U (en) | A kind of automobile data recorder calibration equipment | |
| CN205854539U (en) | Sealed compartment | |
| CN211148560U (en) | Portable oxyhydrogen calibrating device | |
| CN211207190U (en) | Automatic control system for air-tight test | |
| CN205655971U (en) | A test device for detecting framework air chamber gas tightness | |
| CN201821314U (en) | Modularized microcomputer excitation regulator | |
| CN209130527U (en) | For detecting the pressure drop rate detection device of booster detection device | |
| CN202305238U (en) | Test bed for detecting combination property of air pipeline cabinet of locomotive brake system | |
| CN210719249U (en) | Novel gas blowing instrument | |
| CN208672108U (en) | A kind of gas meter function test macro | |
| CN106249070A (en) | A kind of test system and method for electric automobile heat management pipeline |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170208 Termination date: 20180620 |