CN106679983A - Parameter calibration method for airplane turbofan engine - Google Patents

Parameter calibration method for airplane turbofan engine Download PDF

Info

Publication number
CN106679983A
CN106679983A CN201710078194.0A CN201710078194A CN106679983A CN 106679983 A CN106679983 A CN 106679983A CN 201710078194 A CN201710078194 A CN 201710078194A CN 106679983 A CN106679983 A CN 106679983A
Authority
CN
China
Prior art keywords
engine
parameter
calibration
value
electromotor
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.)
Pending
Application number
CN201710078194.0A
Other languages
Chinese (zh)
Inventor
邓乐武
朱小平
舒武静
姚琪
罗华
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Chengdu Aircraft Industrial Group Co Ltd
Original Assignee
Chengdu Aircraft Industrial Group Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Chengdu Aircraft Industrial Group Co Ltd filed Critical Chengdu Aircraft Industrial Group Co Ltd
Priority to CN201710078194.0A priority Critical patent/CN106679983A/en
Publication of CN106679983A publication Critical patent/CN106679983A/en
Pending legal-status Critical Current

Links

Classifications

    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00Testing of engines
    • G01M15/04Testing internal-combustion engines
    • G01M15/05Testing internal-combustion engines by combined monitoring of two or more different engine parameters

Abstract

The invention discloses a parameter calibration method for airplane turbofan engine, and the method comprises the following steps: determining the engine parameter items in need of calibration; using the accurate non-electric quantity parameter value Xi as a signal source to be inputted to an engine sensor; converting the non-electric quantity parameter value into an electric signal and transmitting it to an engine parameter acquisition device; outputting the electric signal to a ground calibration device for measurement and recording the measured value as Yi; conducting logic comparison between Xi and Yi by the ground calibration device to see if the calibration is completed or not; using the ground calibration device to calculate the corresponding calibrated primary coefficient a0 and the constant coefficient b according to the calibration value Xi and the measured value Yi; and selecting a fitting curve to solve the constant coefficient b through the minimum value of the equation. According to the invention, as long as the accurate non-electric quantity parameter value Xi can be provided by various standard devices, the method could be used to calculate the curve for calibration so that the various parameters could be reflected truly and objectively.

Description

One kind is used for aircraft fanjet parameter calibration method
Technical field
The present invention relates to aviation aircraft parametric measurement calibrates field, the turbofan of more particularly, to fixed wing airplane starts Machine item argument measurement calibration steps field, is that one kind is used for aircraft fanjet parameter calibration method specifically.
Background technology
Aircraft engine parameter is referred to and represents the technical parameter related to function of the engine, output characteristic, and it is to sentence The whether normal important evidence of disconnected aircraft engine working condition.Engine parameter mainly includes:Engine high pressure rotating speed, starts Machine low pressure rotating speed, electromotor is low, high pressure mechanism of qi air-intake guide vane corner, engine tail nozzle diameter, engine intake air-flow Stagnation temperature, fuel gas temperature after electromotor low-pressure turbine, motor oil pressure, electromotor machine lock vibration velocity etc..
Flight Data Record System for Aircraft and engine parameter collecting device are that modern manned fixed wing airplane is important airborne Finished product, including flight parameter collector, protection type composite record device, cache recorder, engine parameter collecting device etc. four LRU (Field Replaceable Unit, Line replaceable unit) is constituted.On modern manned fixed wing airplane, start Machine parameter first passes through electromotor related sensor and carries out data acquisition, then Jing after electromotor automatically adjusts device conversion, is sent to and sends out Motivation parameter acquisition equipment is acquired, and finally send recorder to be recorded.
Wherein, the output signal of engine parameter collecting device can be monitored by ground calibration facility;Auto-adjustment control The output signal of device can be by itself adjusting the monitoring of controller surface-monitoring equipment.
When electromotor drives to check, find to be gathered via engine sensor (same signal source), but from automatically adjusting Have differences between the engine parameter value that device controller surface-monitoring equipment and ground calibration facility show (this problem mainly by Input interface impedance is different caused between each airborne finished product).It is thus impossible to determine that can the data of the monitoring correctly reflect send out Motivation time of day, can not determine that (data in recorder need to be unloaded to winged ginseng for the engine parameter data of recorder trace Played back on the playback apparatus of ground) whether correctly reflect the time of day of electromotor.
In sum, because multiple monitoring terminals show that same parameter value is different under same state, illustrates according only to existing The data that monitoring method is obtained can not reflect the time of day of electromotor, can not determine the engine parameter of recorder trace Whether data correctly reflect electromotor time of day, need to repeatedly drive to verify whether the working condition of electromotor is correct, and repeatedly Driving checking also fails to solve this problem.In order to solve the problem, we find a kind of for aircraft fanjet parameter mark Determine method.
The content of the invention
It is an object of the invention to provide a kind of be used for aircraft fanjet parameter calibration method, for solving background skill There is error in the detection of the existing electromotor parameters described in art, it is impossible to true correct with real-world operation duty parameter The problem of reflection electromotor time of day, needs to carry out electromotor running experience repeatedly to further improve precision, many The drawbacks of secondary test can bring has:First, the working life of electromotor can shorten, energy consumption is big, high cost;Second, repeatedly test run Above-mentioned parameter distortion can not fundamentally be solved the problems, such as.
The present invention is achieved through the following technical solutions:
One kind is used for aircraft fanjet parameter calibration method, for demarcating the parameters of the electromotor, specifically Comprise the following steps:
Step one:It is determined that the engine parameter project demarcated is needed, and using ground calibration facility by accurate non electrical quantity Parameter value Xi is input into engine sensor as signal source;
Step 2:The non-electrical parameter value that ground calibration facility is input into is converted into into the signal of telecommunication simultaneously using engine sensor It is sent to engine parameter collecting device;
Step 3:Engine parameter collecting device is examined electric signal output described in step 2 to ground calibration facility It is Yi to survey and record the measured value, and Xi and Yi numerical value are carried out whether logic contrast completes to demarcate, complete mark by ground calibration facility Calibration value Xi record storages in a recorder, are not completed and demarcate repeat step one to step 3 by rule;
Step 4:Using ground calibration facility according to calibration value Xi demarcation coefficient of first order as corresponding with measured value Yi calculating0With Constant factor b, and select matched curveBy solution formulaIt is minimizing to be once Number a0With constant factor b;
Step 5:Using ground calibration facility coefficient of first order a0, a1 ... an and constant factor b, b1 ... bn are uploaded to Engine parameter collecting device, engine parameter collecting device completes the demarcation of engine parameter value according to coefficient;
The calibrated output of engine parameter collecting device
Preferably, matched curve is utilized in the step 4And formulaSolve one Ordered coefficients a0It is as follows with the concrete formula of constant factor b:
To a0Seek local derviation:
Local derviation is asked to b:
When
FormulaThere is minimum;
It is calculated according to formula 1 and formula 2:
Further preferably, the engine parameter project includes:Engine low-pressure compressor air-intake guide vane corner, send out Motivation high-pressure compressor air-intake guide vane corner, engine tail nozzle diameter, engine intake total airflow temperature, electromotor low pressure Fuel gas temperature, motor oil pressure, electromotor machine lock vibration velocity after turbine.What deserves to be explained is, existing turbofan starts The Items that machine is included including but not limited to above-mentioned parameter project, but for people in the art come for, as long as can lead to Cross standard device and accurate non electrical quantity calibrating parameters value Xi is provided, can carry out calculating by heretofore described method and demarcate school Accurate curve, is finally reached the objective reaction of parameters truly, the purpose of just data.
It is further preferred that the engine low-pressure compressor air-intake guide vane corner and engine high pressure compressor enter Mouth guide vane corner has pump truck to be input into engine low-pressure compressor air-intake guide vane corner and start by the way that electromotor is special Machine high-pressure compressor air-intake guide vane corner standard signal source parameter value Xi.
It is further preferred that the engine tail nozzle diameter is input into the standard of engine tail nozzle diameter by sensor Signal source parameter value Xi.
It is further preferred that the engine intake total airflow temperature is input into engine intake total airflow temperature mark by resistance box Calibration signal source parameter value Xi.
It is further preferred that fuel gas temperature is input into electromotor by sinusoidal signal generator after the electromotor low-pressure turbine Low-pressure turbine after-burning temperature degree standard signal source parameter value Xi.
It is further preferred that the motor oil pressure is input into motor oil pressure criteria by lubricating oil regulator Signal source parameter value Xi.
It is further preferred that the electromotor machine lock vibration velocity is input into electromotor machine lock by sinusoidal signal generator shaking Dynamic velocity standard signal source parameter value Xi.
The present invention compared with prior art, with advantages below and beneficial effect:
(1) present invention is by the way that by really, accurate calibration value Xi sets up logical function relation with actual measured value Yi, counts Calculate respective items purpose for amendment coefficient of first order and constant factor, obtain respective items purpose parameters revision coefficient curve letter Number, to eliminate the problem of the display distortion that projects occur in measurement and sensing process.
(2) the method for the invention can determine parameter value Xi suitable for various by providing accurate non electrical quantities, be calculated The curve of calibration is demarcated, the objective reaction of parameters is finally reached truly, the purpose of just data.
Description of the drawings
Fig. 1 is the FB(flow block) of the method for the invention;
Specific embodiment
The present invention is described in further detail with reference to embodiment, but embodiments of the present invention not limited to this.
Preferred embodiment 1:
With reference to shown in accompanying drawing 1, one kind is used for aircraft fanjet parameter calibration method, for demarcating the electromotor Parameters, specifically include following steps:
Step one:It is determined that the engine parameter project demarcated is needed, and using ground calibration facility by accurate non electrical quantity Parameter value Xi is input into engine sensor as signal source;
Step 2:The non-electrical parameter value that ground calibration facility is input into is converted into into the signal of telecommunication simultaneously using engine sensor It is sent to engine parameter collecting device;
Step 3:Engine parameter collecting device is examined electric signal output described in step 2 to ground calibration facility It is Yi to survey and record the measured value, and Xi and Yi numerical value are carried out whether logic contrast completes to demarcate, complete mark by ground calibration facility Calibration value Xi record storages in a recorder, are not completed and demarcate repeat step one to step 3 by rule;
Step 4:Using ground calibration facility according to calibration value Xi demarcation coefficient of first order as corresponding with measured value Yi calculating0With Constant factor b, and select matched curveBy solution formulaIt is minimizing to be once Number a0With constant factor b;
Step 5:Using ground calibration facility coefficient of first order a0, a1 ... an and constant factor b, b1 ... bn are uploaded to Engine parameter collecting device, engine parameter collecting device completes the demarcation of engine parameter value according to coefficient;
The calibrated output of engine parameter collecting device
Preferably, matched curve is utilized in the step 4And formulaSolve one Ordered coefficients a0It is as follows with the concrete formula of constant factor b:
To a0Seek local derviation:
Local derviation is asked to b:
When
FormulaThere is minimum;
It is calculated according to formula 1 and formula 2:
Further preferably, the engine parameter project includes:Engine low-pressure compressor air-intake guide vane corner, send out Motivation high-pressure compressor air-intake guide vane corner, engine tail nozzle diameter, engine intake total airflow temperature, electromotor low pressure Fuel gas temperature, motor oil pressure, electromotor machine lock vibration velocity after turbine.What deserves to be explained is, existing turbofan starts The Items that machine is included including but not limited to above-mentioned parameter project, but for people in the art come for, as long as can lead to Cross standard device and accurate non electrical quantity calibrating parameters value Xi is provided, can carry out calculating by heretofore described method and demarcate school Accurate curve, is finally reached the objective reaction of parameters truly, the purpose of just data.
It is further preferred that the engine low-pressure compressor air-intake guide vane corner and engine high pressure compressor enter Mouth guide vane corner has pump truck to be input into engine low-pressure compressor air-intake guide vane corner and start by the way that electromotor is special Machine high-pressure compressor air-intake guide vane corner standard signal source parameter value Xi.
It is further preferred that the engine tail nozzle diameter is input into the standard of engine tail nozzle diameter by sensor Signal source parameter value Xi.
It is further preferred that the engine intake total airflow temperature is input into engine intake total airflow temperature mark by resistance box Calibration signal source parameter value Xi.
It is further preferred that fuel gas temperature is input into electromotor by sinusoidal signal generator after the electromotor low-pressure turbine Low-pressure turbine after-burning temperature degree standard signal source parameter value Xi.
It is further preferred that the motor oil pressure is input into motor oil pressure criteria by lubricating oil regulator Signal source parameter value Xi.
It is further preferred that the electromotor machine lock vibration velocity is input into electromotor machine lock by sinusoidal signal generator shaking Dynamic velocity standard signal source parameter value Xi.
What deserves to be explained is:The special hydrant cart of the motivation, resistance box, lubricating oil regulator, sinusoidal signal generator etc. Device for being input into non-electric charge quantity signalling source belongs to existing equipment, prior art, therefore, as long as demarcation side of the invention can be provided Needed for method, the equipment of non electrical quantity accurate signal can meet requirement, so, it is in the present embodiment, just inaccurate to above-mentioned offer True non-electric charge quantity signalling equipment is described in detail.
Embodiment 2:
On the basis of embodiment 1, with reference to shown in accompanying drawing 1, by engine low-pressure compressor engine tail nozzle diameter Calibration value Xi=1100mm, measured value Yi is shown as=1072mm, brings above-mentioned calibration value X and measured value Yi into formula:
To a0Seek local derviation:
Local derviation is asked to b:
When
FormulaThere is minimum;
It is calculated according to formula 1 and formula 2:
A0=0.92 and b=88 are brought intoThen this time engine low-pressure compressor electromotor The demarcation check value of nozzle diameter is actual compensation error amount 28mm, i.e., compensate through correlation calibration, realizes actual displayed Value is identical with Theoretical Calibration value, that is, eliminate and existing directly display the situation that measured value has error.
It is accurate to reach in order to check value leveled off to into theoretical error value due to there is inevitable test error The purpose that verification shows, preferably by same project parameter in different condition, carries out multiple test run under different operating modes, and records change Change amount, weeds out pole value, seeks the meansigma methodss of the group verification error as the actual compensation error amount for verification.
The above, is only presently preferred embodiments of the present invention, not does any pro forma restriction to the present invention, it is every according to According to any simple modification, equivalent variations that the technical spirit of the present invention is made to above example, the protection of the present invention is each fallen within Within the scope of.

Claims (9)

1. it is a kind of to be used for aircraft fanjet parameter calibration method, for demarcating the parameters of the electromotor, its feature It is to specifically include following steps:
Step one:It is determined that the engine parameter project demarcated is needed, and using ground calibration facility by accurate non-electrical parameter Value Xi is input into engine sensor as signal source;
Step 2:Using engine sensor the non-electrical parameter value that ground calibration facility is input into is converted into the signal of telecommunication and is sent To engine parameter collecting device;
Step 3:Engine parameter collecting device is detected electric signal output described in step 2 simultaneously to ground calibration facility It is Yi to record the measured value, and Xi and Yi numerical value are carried out whether logic contrast completes to demarcate by ground calibration facility, complete to demarcate then By calibration value Xi record storages in a recorder, do not complete and demarcate repeat step one to step 3;
Step 4:Using ground calibration facility according to calibration value Xi demarcation coefficient of first order as corresponding with measured value Yi calculating0And constant Coefficient b, and select matched curveBy solution formulaMinimizing coefficient of first order a0 With constant factor b;
Step 5:Using ground calibration facility coefficient of first order a0, a1 ... an and constant factor b, b1 ... bn are uploaded to and start Machine parameter acquisition equipment, engine parameter collecting device completes the demarcation of engine parameter value according to coefficient;
The calibrated output of engine parameter collecting device
2. it is according to claim 1 a kind of for aircraft fanjet parameter calibration method, it is characterised in that the step Matched curve is utilized in rapid fourAnd formulaSolve coefficient of first order a0With constant factor b Concrete formula is as follows:
To a0Seek local derviation:
Local derviation is asked to b:
When
FormulaThere is minimum;
It is calculated according to formula 1 and formula 2:
3. it is according to claim 1 a kind of for aircraft fanjet parameter calibration method, it is characterised in that described Motivation Items include:Engine low-pressure compressor air-intake guide vane corner, engine high pressure compressor inlet directing vane Fuel gas temperature, electromotor are slided after piece corner, engine tail nozzle diameter, engine intake total airflow temperature, electromotor low-pressure turbine Oil pressure, electromotor machine lock vibration velocity.
4. it is according to claim 3 a kind of for aircraft fanjet parameter calibration method, it is characterised in that described Motivation low-pressure compressor air-intake guide vane corner and engine high pressure compressor inlet guide vane corner are special by electromotor Turned with having pump truck input engine low-pressure compressor air-intake guide vane corner and engine high pressure compressor inlet guide vane Angle standard signal source parameter value Xi.
5. it is according to claim 3 a kind of for aircraft fanjet parameter calibration method, it is characterised in that described Motivation nozzle diameter is input into the standard signal source parameter value Xi of engine tail nozzle diameter by sensor.
6. it is according to claim 3 a kind of for aircraft fanjet parameter calibration method, it is characterised in that described Motivation inlet air flow stagnation temperature is input into engine intake total airflow temperature standard signal source parameter value Xi by resistance box.
7. it is according to claim 3 a kind of for aircraft fanjet parameter calibration method, it is characterised in that described Fuel gas temperature is input into electromotor low-pressure turbine after-burning temperature scale calibration signal by sinusoidal signal generator after motivation low-pressure turbine Source parameter value Xi.
8. it is according to claim 3 a kind of for aircraft fanjet parameter calibration method, it is characterised in that described Motivation lubricating oil pressure is input into motor oil pressure criteria signal source parameter value Xi by lubricating oil regulator.
9. it is according to claim 3 a kind of for aircraft fanjet parameter calibration method, it is characterised in that described Motivation machine lock vibration velocity is input into electromotor machine lock vibration velocity standard signal source parameter value Xi by sinusoidal signal generator.
CN201710078194.0A 2017-02-14 2017-02-14 Parameter calibration method for airplane turbofan engine Pending CN106679983A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201710078194.0A CN106679983A (en) 2017-02-14 2017-02-14 Parameter calibration method for airplane turbofan engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201710078194.0A CN106679983A (en) 2017-02-14 2017-02-14 Parameter calibration method for airplane turbofan engine

Publications (1)

Publication Number Publication Date
CN106679983A true CN106679983A (en) 2017-05-17

Family

ID=58862661

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201710078194.0A Pending CN106679983A (en) 2017-02-14 2017-02-14 Parameter calibration method for airplane turbofan engine

Country Status (1)

Country Link
CN (1) CN106679983A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107764558A (en) * 2017-09-11 2018-03-06 重庆大学 A kind of experimental provision and experimental method for being used to simulate gear fanjet blade loss
CN109556877A (en) * 2018-12-21 2019-04-02 成都飞机工业(集团)有限责任公司 A kind of exhaust temperature of aircraft engine scaling method
CN110646212A (en) * 2019-10-23 2020-01-03 成都飞机工业(集团)有限责任公司 Novel method for calibrating aircraft engine
CN112319846A (en) * 2020-09-25 2021-02-05 中国航空工业集团公司上海航空测控技术研究所 Parameter calibration method for aircraft engine parameter acquisition equipment

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1595311A (en) * 2004-06-23 2005-03-16 浙江中控技术股份有限公司 System and method for calibrating analog signal measuring apparatus automatically
CN204439365U (en) * 2015-02-25 2015-07-01 霸州市华威发动机技术有限公司 A kind of engine operating parameter calibration facility based on wireless telecommunications
CN105571873A (en) * 2015-12-14 2016-05-11 中国北方发动机研究所(天津) Dual-opposed two-stroke engine external characteristic calibration method
CN105953946A (en) * 2016-04-26 2016-09-21 哈尔滨工程大学 Least squares algorithm based calibration method for temperature coefficient of fiber optic gyroscope temperature control device
US20160334304A1 (en) * 2013-12-17 2016-11-17 Toyota Jidosha Kabushiki Kaisha Control device for internal combustion engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1595311A (en) * 2004-06-23 2005-03-16 浙江中控技术股份有限公司 System and method for calibrating analog signal measuring apparatus automatically
US20160334304A1 (en) * 2013-12-17 2016-11-17 Toyota Jidosha Kabushiki Kaisha Control device for internal combustion engine
CN204439365U (en) * 2015-02-25 2015-07-01 霸州市华威发动机技术有限公司 A kind of engine operating parameter calibration facility based on wireless telecommunications
CN105571873A (en) * 2015-12-14 2016-05-11 中国北方发动机研究所(天津) Dual-opposed two-stroke engine external characteristic calibration method
CN105953946A (en) * 2016-04-26 2016-09-21 哈尔滨工程大学 Least squares algorithm based calibration method for temperature coefficient of fiber optic gyroscope temperature control device

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
杜宇人编著: "最小二乘法原理", 《现代电子测量技术》 *
邓乐武等: "一种基于全站仪的飞机惯导参数原位检测方法", 《新技术新工艺》 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107764558A (en) * 2017-09-11 2018-03-06 重庆大学 A kind of experimental provision and experimental method for being used to simulate gear fanjet blade loss
CN109556877A (en) * 2018-12-21 2019-04-02 成都飞机工业(集团)有限责任公司 A kind of exhaust temperature of aircraft engine scaling method
CN110646212A (en) * 2019-10-23 2020-01-03 成都飞机工业(集团)有限责任公司 Novel method for calibrating aircraft engine
CN112319846A (en) * 2020-09-25 2021-02-05 中国航空工业集团公司上海航空测控技术研究所 Parameter calibration method for aircraft engine parameter acquisition equipment

Similar Documents

Publication Publication Date Title
CN106679983A (en) Parameter calibration method for airplane turbofan engine
CN204085645U (en) With the gas flow standard device of self calibration structure
CN105571653B (en) Coal pulverizer air measuring method and system
CN108195447B (en) Flowmeter calibration system and calibration method
CN108680226B (en) Accurate method for detecting current oil quantity of oil tank
CN103541924B (en) Automatic test system of axial flow fans
CN110530597B (en) Wind speed calibration system under low pressure
CN106197559A (en) A kind of general aircraft engine parameter collecting method and device
CN201803838U (en) Multifunctional valve testing system
CN105526998A (en) Communication-based electronic gas meter detection device and method
CN103968919A (en) Equipment and method for metering and automatically calibrating electronic water meter in production process
CN203443786U (en) Device for detecting test-run parameter of aero-engine
CN107762638B (en) The method and apparatus of fanjet line inspection idling rating minimum fuel flow
CN104344862B (en) The detection method of FCM10A type fuel consumption meters
CN205352516U (en) Electron gas table calibrating installation
CN107289985A (en) On-line proving and the dynamic measurement system and method for compensation
CN102133496A (en) Dust filtering performance testing method and system of air filter for cab of vehicle on road
CN208873487U (en) A kind of device measuring nuclear power plant reactor coolant pump key phase
JP5815841B2 (en) Fuel flow measurement device and calibration device thereof
CN1952624A (en) Self-calibration control system of water flow standard apparatus
CN203641059U (en) Automatic test system for axial flow fan
CN105953870A (en) Automatic water meter test board
CN112525794A (en) Portable automatic tester and testing method for surface air permeability of material
US20170292872A1 (en) Flow sensor bit for motor driven compressor
CN103292872B (en) A kind of air flow meter performance detecting system

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
WD01 Invention patent application deemed withdrawn after publication

Application publication date: 20170517

WD01 Invention patent application deemed withdrawn after publication