CN107065969A - Closed loop probe heating control system - Google Patents
Closed loop probe heating control system Download PDFInfo
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- CN107065969A CN107065969A CN201710389848.1A CN201710389848A CN107065969A CN 107065969 A CN107065969 A CN 107065969A CN 201710389848 A CN201710389848 A CN 201710389848A CN 107065969 A CN107065969 A CN 107065969A
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- probe
- heating
- head
- closed loop
- control system
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- 239000000523 sample Substances 0.000 title claims abstract description 126
- 238000010438 heat treatment Methods 0.000 title claims abstract description 76
- 230000003750 conditioning effect Effects 0.000 claims abstract description 18
- 230000033228 biological regulation Effects 0.000 claims abstract description 14
- 230000000052 comparative effect Effects 0.000 claims abstract description 4
- 230000001629 suppression Effects 0.000 claims description 8
- 230000009466 transformation Effects 0.000 claims description 8
- 230000001052 transient effect Effects 0.000 claims description 8
- 230000000694 effects Effects 0.000 claims description 4
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims description 3
- 230000005669 field effect Effects 0.000 claims description 2
- 229910044991 metal oxide Inorganic materials 0.000 claims description 2
- 150000004706 metal oxides Chemical class 0.000 claims description 2
- 239000004065 semiconductor Substances 0.000 claims description 2
- 238000005265 energy consumption Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 241001274660 Modulus Species 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000010792 warming Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D23/00—Control of temperature
- G05D23/19—Control of temperature characterised by the use of electric means
- G05D23/20—Control of temperature characterised by the use of electric means with sensing elements having variation of electric or magnetic properties with change of temperature
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Control Of Temperature (AREA)
Abstract
A kind of a kind of closed loop probe heating control system proposed by the present invention, it is desirable to provide the heating control system that temperature control is accurate, low in energy consumption, reliability is high.The technical scheme is that：Probe temperature sensor（1）Resistance signal is sent into analog quantity conditioning module（2）Conditioning is converted to voltage signal, via A/D converter（3）Be converted to and central processor CPU is supplied after data signal（5）Processing, central processor CPU according to the temperature signal collected to adjust PWM Wave heating modules（6）Control signal is sent, is compared with the predetermined threshold value of probe heating, the dutycycle of PWM Wave heating modules is adjusted according to comparative result, to probe heater strip（7）Output pulse width modulation (PWM) ripple, regulation probe heater strip heating power, by the temperature control of probe in default threshold value, the regulation that power is heated to probe heater strip is realized by adjusting the dutycycle of heating power supply.
Description
Technical field
The present invention relates to a kind of aircraft probe total Air Temperature probe heating control system.More specifically, the present invention is pin
To the probe heating control system of accurate temperature controlling.
Background technology
The pitot probe of aircraft is measurement air-flow stagnation pressure and static pressure to determine a kind of tube of air velocity.Air speed
Pipe is survey tool particularly important on aircraft.The installation site of pitot probe must be received aircraft exterior air-flow is less
The region of aircraft influence, in order to prevent the pitot on pitot probe distal end aperture ice blockage awing, general aircraft
There is electric warming device.
Probe heating control system of the prior art is made up of relay and heater strip, is directly controlled by relay
What heater strip was heated.This mode of heating is that the relay contact in heating system is controlled by other equipment on aircraft
Break-make is realized to heater strip electrified regulation.Taken due to this heating mode and heater strip progress is directly connected by relay manually
Heat, heating-up temperature be not controlled, had the following disadvantages：One is that heater strip is in full heated condition all the time, is added winged
The unnecessary electric power consumption of machine；Two are the increase in the risk of probe deformation, will cause to visit in low latitude or state of ground heating
Head overheating deforming；Three be that relay weight is big, reliability is low；Four be opened loop control, and the warm-up mode of probe is indefinite.
The content of the invention
The purpose of the present invention is that there is provided a kind of temperature control is accurate, low in energy consumption, reliability in view of the deficiencies of the prior art
High, lightweight closed loop probe heating control system.
The technical solution that the present invention is provided is：A kind of closed loop probe heating control system, including：Installed in probe by
In hot-zone, impression probe heterogeneity phantom probe temperature sensor, be electrically connected pick upper power supply PWM Wave heatings module and voltage turn
Change the mold block, it is characterised in that：Probe temperature sensor 1 is passed by the series connection A/D converter 3 of analog quantity conditioning module 2, probe temperature
Resistance signal is sent into the conditioning of analog quantity conditioning module 2 and is converted to voltage signal by sensor 1, and numeral is converted to via A/D converter 3
Handled after signal for central processor CPU 5, central processor CPU 5 according to the temperature signal collected to regulation PWM Wave heatings
Module 6 sends control signal, is compared with the predetermined threshold value of probe heating, according to comparative result regulation PWM Wave heatings module 6
Dutycycle, to probe the output pulse width modulation (PWM) ripple of heater strip 7, regulation probe heater strip 7 heating power, by the temperature of probe
Control heats the dutycycle of power supply to realize the regulation to the probe heating power of heater strip 7 in default threshold value.
The present invention has the advantages that compared to prior art.
Temperature control is accurate, low in energy consumption：The present invention controls the heating of heater strip using PWM ripples, can reduce probe when inessential
Heating power consumption, reduction aircraft flight in the air when heating power consumption expense, while using MOSFET be used as power discharging device, realize
Accurate control to the heat affected zone thermal field of probe.PWM Wave heatings module by adjust heat 27V/ ON signals dutycycle come
The control to heating intensity is realized, single channel heating power can reach 1000W, be much higher than the specified of traditional relay heating mode
Power.Probe temperature sensor is directly installed on probe inside, and the aerodynamic configuration of probe is not destroyed.Probe temperature sensor is close to
The heat affected zone of probe, heating effect of the accurate measurement " heater strip " to probe.Enhance the essence to probe heating control
Exactness and stability, save power consumption of the aircraft in flight, and it also avoid probe superheated caused may deform.
Reliability is high：The present invention experiences the probe temperature sensing of probe heterogeneity phantom using being arranged in probe heat affected zone
Device, be electrically connected the PWM Wave heatings module and voltage transformation module of upper power supply of picking, the heat of probe temperature sensor feedback impression probe
Field distribution, PWM heating modules, as power-ourput device, introduce the Digital Control of probe heating, easily using MOSFET element
Docked in flight control system with the digitlization of probe heating control subsystem.Central processor CPU uses full automatic heating
Control, adjusts the dutycycle of PWM Wave heating modules, and adjusting PWM Wave heatings module 6 according to comparative result exports accounting for for heating power supply
Sky ratio heats the regulation of power to realize to probe heater strip 7, and closed-loop dynamic controls probe temperature sensor, it will can pop one's head in
Temperature control in default threshold value, it is to avoid traditional relay warm up mode causes full heated condition to be heated to probe
High-temperature causes the risk of deformation.Electricity can start probe heating on aircraft, reduce the operation of pilot.
It is lightweight：The present invention is arranged on " probe temperature sensor " in probe heat affected zone（Multiple spies can be installed if necessary
Head temperature sensor is to experience the heterogeneity phantom of large-scale probe）, the pulse-width modulation PWM Wave heating mould of an adjustable dutycycle
Block, one according to probe temperature sensor experience probe heterogeneity phantom central processor CPU, by the way of closed-loop control
Probe is heated, the accurate closed-loop control to thermal field of popping one's head in is realized, compared to traditional relay warm up mode small volume,
It is lightweight.
The present invention can upload warm-up mode information and probe temperature in real time according to the increase in demand bus communication module of aircraft
Etc. information.Both in the heating system of the invention that probe can have been applied to or in the heating system of weathercock.
Brief description of the drawings
Fig. 1 is the operation principle schematic diagram of closed loop probe heating control system of the present invention.
Fig. 2 is Fig. 1 circuit theory schematic diagram.
Fig. 3 is the organigram of sensor probe.
Fig. 4 is the circuit theory schematic diagram of Fig. 1 PWM ripple control modules.
In figure：1 probe temperature sensor, 2 analog quantity conditioning modules, 3 probe As/D converters, 4 probe voltage moduluss of conversion
Power supply on block, 5 central processor CPUs, 6PWM Wave heating modules, 7 probe heater strips, 8 aircraft machines, 9 sensor probes, 10 heatings
Deicing controller, I gas circuit chambers, II probe temperature sensors, III heater strips, IV gas circuits.
Embodiment
Refering to Fig. 1-Fig. 3.In embodiment described below, a kind of closed loop probe heating control system, including：It is arranged on
Pop one's head in heat affected zone, the probe temperature sensor 1 of impression probe heterogeneity phantom is connected electrically in power supply 8 and probe heater strip 7 on machine
Between PWM Wave heatings module 6, be fixed on the heating deicing controller 10 of the bend pipe afterbody bottom of sensor probe 9, its feature exists
In：Heating deicing controller 10 includes：One end is electrically connected the upper power supply 8 that picks, and the other end electrically connects the voltage of central processor CPU 5
Modular converter 4, voltage transformation module 4 connects PWM Wave heatings module 6 and the formation of power supply 8 on machine the by central processor CPU 5
One closed loop, probe temperature sensor 1 passes through the series connection A/D converter 3 of analog quantity conditioning module 2, the He of analog quantity conditioning module 2
A/D converter 3 connects central processor CPU 5, the electrical connection central processor CPU 5 of A/D converter 3 by voltage transformation module 4
Constitute the second closed loop.Wherein, probe temperature sensor 1 is arranged in the tube head of the pitot probe 9 shown in Fig. 3, necessary
When the mount point of multiple probe temperature sensors 1 can be selected according to the size of probe；Analog quantity conditioning module 2 and A/D converter 3
Operating voltage needed for work is provided by voltage transformation module 4.Probe temperature sensor 1 is connected by analog quantity conditioning module 2
Resistance signal is sent into the conditioning of analog quantity conditioning module 2 and is converted to voltage signal by A/D converter 3, probe temperature sensor 1, is passed through
Be converted to after data signal and handled for central processor CPU 5 by A/D converter 3, central processor CPU 5 is according to the temperature collected
Degree signal sends control signal to regulation PWM Wave heatings module 6, is compared with the predetermined threshold value of probe heating, foundation compares
As a result the dutycycle of regulation PWM Wave heatings module 6, to the probe output pulse width modulation (PWM) ripple of heater strip 7, adjusts probe heater strip 7
Power is heated, by the temperature control of probe in default threshold value, is realized by adjusting the dutycycle of heating power supply to probe
Heater strip 7 heats the regulation of power.
The inwall of pitot probe body air intake duct is embedded with probe temperature sensor II, probe temperature sensor II insertions
In the inwall of probe body air intake duct, probe temperature sensor II impressions are wrapped in probe ozzle circular cone cavity heater strip III's
Heating effect.During practical flight, blocked in order to avoid being considered to be worth doing at gas circuit chamber I or probe ozzle by ice, obstruction pitot is visited
Head tube body gas circuit IV's is unimpeded, and heater strip III is heated to probe body air intake duct gas circuit chamber I, if necessary, can be in probe pipe
Mouth circular cone cavity big end section inwall installs probe temperature sensor II, makes that the probe thermal field of impression is more uniform, and temperature control is more
Plus it is accurate.Avoid air intake duct V from freezing and block gas circuit, heater strip III is uniformly wrapped on the inwall of probe body air intake duct, is led to
Cross and heater strip energization is come to heat air intake duct.In probe temperature sensor II insertion inwalls, the temperature of direct feeling inwall is surveyed
Measure heating effect.
Refering to Fig. 4, PWM ripples control module 6 includes：Electrically connect the resistance R1 of central processor CPU, connect DGND two poles
Pipe V1, the electric capacity C1 being connected in parallel between resistance R1 and diode V1 and its be connected in parallel on electric capacity C1 two ends photoelectrical coupler N1A and
By photoelectrical coupler N1A series resistance R2, the metal oxide semiconductor field effect tube electrically connected through shunt circuit resistance R2
MOSFET power amplifirer V3, and it is connected in parallel on the Transient Suppression Diode V2 and its resistance at MOSFET power amplifirer V3 two ends
R4 and Transient Suppression Diode V4.Electricity of the Transient Suppression Diode V2 at MOSFET power amplifirer V3 two ends to connection resistance R4
Source suppresses the spike that power supply is produced, and electric power output voltage is heated by Transient Suppression Diode V4.What central processor CPU was produced
The PWM wave control signals of Transistor-Transistor Logic level, directly drive MOSFET power amplifirer V3 after photoelectrical coupler N1A level conversions,
Different MOSFET power amplifirer V3 are selected to heat probe according to the concrete condition of probe heater strip.
Claims (10)
- The heating control system 1. a kind of closed loop is popped one's head in, including：In probe heat affected zone, the probe of impression probe heterogeneity phantom Temperature sensor（1）, be electrically connected the PWM Wave heating modules of upper power supply of picking（6）And voltage transformation module（4）, it is characterised in that：Visit Head temperature sensor（1）Pass through analog quantity conditioning module（2）Series connection A/D converter（3）, probe temperature sensor（1）By resistance Signal sends into analog quantity conditioning module（2）Conditioning is converted to voltage signal, via A/D converter（3）Be converted to after data signal For central processor CPU（5）Processing, central processor CPU（5）According to the temperature signal collected to regulation PWM Wave heating moulds Block（6）Control signal is sent, is compared with the predetermined threshold value of probe heating, PWM Wave heating modules is adjusted according to comparative result （6）Dutycycle, to probe heater strip（7）Output pulse width modulation (PWM) ripple, regulation probe heater strip（7）Power is heated, will be popped one's head in Temperature control in default threshold value, by adjust heat power supply dutycycle come realize to probe heater strip（7）Heat work( The regulation of rate.
- The heating control system 2. closed loop as claimed in claim 1 is popped one's head in, it is characterised in that probe temperature sensor（1）Install In the tube head that pitot is popped one's head in, multiple probe temperature sensors are selected according to the size of probe（1）Mount point.
- The heating control system 3. closed loop as claimed in claim 1 is popped one's head in, it is characterised in that analog quantity conditioning module（2）And A/D Converter（3）Operating voltage needed for work is by voltage transformation module（4）There is provided.
- The heating control system 4. closed loop as claimed in claim 1 is popped one's head in, it is characterised in that pitot probe body air intake duct Inwall is embedded with probe temperature sensor II, and probe temperature sensor II impressions are wrapped in probe ozzle circular cone cavity heater strip III heating effect.
- The heating control system 5. closed loop as claimed in claim 1 is popped one's head in, it is characterised in that during practical flight, in order to Avoid being considered to be worth doing by ice at gas circuit chamber I or probe ozzle and block, obstruction gas circuit IV's is unimpeded, and heater strip III is to probe body air intake duct Gas circuit chamber I is heated, or installs probe temperature sensor II in the big end section inwall of probe ozzle circular cone cavity, makes the spy of impression Head thermal field is more uniform, and temperature control is more accurate.
- The heating control system 6. closed loop as claimed in claim 1 is popped one's head in, it is characterised in that during practical flight, in order to Avoid being considered to be worth doing by ice at gas circuit chamber I or probe ozzle and block, obstruction pitot probe body gas circuit IV unimpeded, III pairs of heater strip Probe body air intake duct gas circuit chamber I is heated, or installs probe temperature sensing in the big end section inwall of probe ozzle circular cone cavity Device II, makes that the probe thermal field of impression is more uniform, and temperature control is more accurate.
- The heating control system 7. closed loop as claimed in claim 1 is popped one's head in, it is characterised in that PWM ripple control modules（6）Including： Electrically connect the resistance R1 of central processor CPU, connect DGND diode V1, be connected in parallel on the electricity between resistance R1 and diode V1 Hold C1 and its be connected in parallel on the photoelectrical coupler N1A at electric capacity C1 two ends and by photoelectrical coupler N1A series resistance R2, returned through parallel connection The metal oxide semiconductor field effect tube MOSFET power amplifirer V3 of road resistance R2 electrical connections, and it is connected in parallel on MOSFET work( The Transient Suppression Diode V2 and its resistance R4 at rate amplifirer V3 two ends and Transient Suppression Diode V4.
- The heating control system 8. closed loop as claimed in claim 1 is popped one's head in, it is characterised in that MOSFET power amplifirer V3 two ends Transient Suppression Diode V2 to connect resistance R4 power supply suppress power supply produce spike, added by Transient Suppression Diode V4 Warm electric power output voltage.
- The heating control system 9. closed loop as claimed in claim 1 is popped one's head in, it is characterised in that central processor CPU（5）Produce The PWM wave control signals of Transistor-Transistor Logic level, directly drive MOSFET power amplifirer V3 after photoelectrical coupler N1A level conversions, Heater strip of popping one's head in is heated to different MOSFET power amplifirer V3 to probe.
- The heating control system 10. closed loop as claimed in claim 1 is popped one's head in, it is characterised in that heating deicing controller（10）Bag Include：One end is electrically connected the upper power supply that picks（8）, other end electrical connection central processor CPU（5）Voltage transformation module（4）, voltage turn Change the mold block（4）Pass through central processor CPU（5）Connect PWM Wave heating modules（6）With power supply on machine（8）The first closed loop is formed to return Road, probe temperature sensor（1）Pass through analog quantity conditioning module（2）Series connection A/D converter（3）, analog quantity conditioning module（2）With A/D converter（3）Pass through voltage transformation module（4）Connect central processor CPU（5）, A/D converter（3）Electrically connect centre Manage device CPU（5）Constitute the second closed loop.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710389848.1A CN107065969A (en) | 2017-05-27 | 2017-05-27 | Closed loop probe heating control system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710389848.1A CN107065969A (en) | 2017-05-27 | 2017-05-27 | Closed loop probe heating control system |
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| Publication Number | Publication Date |
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| CN107065969A true CN107065969A (en) | 2017-08-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710389848.1A Pending CN107065969A (en) | 2017-05-27 | 2017-05-27 | Closed loop probe heating control system |
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| CN (1) | CN107065969A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108803709A (en) * | 2018-04-02 | 2018-11-13 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of anti-icing wall static pressure measurement control structure |
| CN109164508A (en) * | 2018-09-05 | 2019-01-08 | 北京雨根科技有限公司 | Thermostatic control module and microwave scintiloscope |
| CN109560537A (en) * | 2017-09-27 | 2019-04-02 | 深圳光峰科技股份有限公司 | A kind of optocoupler overvoltage crowbar and associated appliance |
| CN110319942A (en) * | 2018-03-30 | 2019-10-11 | 霍尼韦尔国际公司 | Self-regulation heating system for total air themperature probe |
| CN112004271A (en) * | 2020-07-24 | 2020-11-27 | 西安爱生技术集团公司 | Intelligent heater of small unmanned aerial vehicle airspeed head |
| US20210107678A1 (en) * | 2019-10-11 | 2021-04-15 | Shanghai Autoflight Co., Ltd. | Integrated heating airspeed tube and unmanned aerial vehicle including same |
| US11524790B2 (en) | 2018-08-21 | 2022-12-13 | Honeywell International Inc. | Enhanced pitot tube power management system and method |
| CN115717681A (en) * | 2022-11-18 | 2023-02-28 | 浙江陶特半导体材料有限公司 | Steel cylinder for precursor solid source |
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| US5464965A (en) * | 1993-04-20 | 1995-11-07 | Honeywell Inc. | Apparatus for controlling temperature of an element having a temperature variable resistance |
| US20070107510A1 (en) * | 2005-10-24 | 2007-05-17 | Mark Agami | Multi-function air data sensor |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109560537A (en) * | 2017-09-27 | 2019-04-02 | 深圳光峰科技股份有限公司 | A kind of optocoupler overvoltage crowbar and associated appliance |
| CN110319942A (en) * | 2018-03-30 | 2019-10-11 | 霍尼韦尔国际公司 | Self-regulation heating system for total air themperature probe |
| CN110319942B (en) * | 2018-03-30 | 2023-09-19 | 霍尼韦尔国际公司 | Self-regulating heating system for total air temperature probe |
| CN108803709A (en) * | 2018-04-02 | 2018-11-13 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of anti-icing wall static pressure measurement control structure |
| US11524790B2 (en) | 2018-08-21 | 2022-12-13 | Honeywell International Inc. | Enhanced pitot tube power management system and method |
| CN109164508A (en) * | 2018-09-05 | 2019-01-08 | 北京雨根科技有限公司 | Thermostatic control module and microwave scintiloscope |
| CN109164508B (en) * | 2018-09-05 | 2024-03-01 | 北京雨根科技有限公司 | Constant temperature control module and microwave scintillator |
| US20210107678A1 (en) * | 2019-10-11 | 2021-04-15 | Shanghai Autoflight Co., Ltd. | Integrated heating airspeed tube and unmanned aerial vehicle including same |
| US11780602B2 (en) * | 2019-10-11 | 2023-10-10 | Shanghai Autoflight Co., Ltd. | Integrated heating airspeed tube and unmanned aerial vehicle including same |
| CN112004271A (en) * | 2020-07-24 | 2020-11-27 | 西安爱生技术集团公司 | Intelligent heater of small unmanned aerial vehicle airspeed head |
| CN115717681A (en) * | 2022-11-18 | 2023-02-28 | 浙江陶特半导体材料有限公司 | Steel cylinder for precursor solid source |
| CN115717681B (en) * | 2022-11-18 | 2023-12-29 | 浙江陶特半导体材料有限公司 | Steel cylinder for precursor solid source |
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Application publication date: 20170818 |
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