CN104976981A - Flap position indicator verification system - Google Patents
Flap position indicator verification system Download PDFInfo
- Publication number
- CN104976981A CN104976981A CN201410143136.8A CN201410143136A CN104976981A CN 104976981 A CN104976981 A CN 104976981A CN 201410143136 A CN201410143136 A CN 201410143136A CN 104976981 A CN104976981 A CN 104976981A
- Authority
- CN
- China
- Prior art keywords
- flap
- indicator
- sensor
- position indicator
- zey
- 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
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/22—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapers; for testing the alignment of axes
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Audible And Visible Signals (AREA)
Abstract
The invention relates to a flap position indicator verification system which comprises a 4C-S291 test rotary table (1), a sensor (2), a DC regulated power supply (3), a buzzer frame (4) and a ZEY-1E flap position indicator (5). The formed flap position indicator verification system is simple and effective and reasonable in design; and when work personnel detect the sensor, external connection is simple and operation is simple, thereby meeting the demand for low-cost separate verification of a flap position indicator. The tester, on one hand, can test the performance of the sensor, thereby preventing fault products from being installed directly and improving efficiency and quality of airplane general assembly; and on the other hand, test procedure is simplified, thereby improving work efficiency; and the tester has compatibility.
Description
Technical field
The present invention relates to a kind of check system of flap indicator, belong to aircraft flap indicator field tests.
Background technology
Aircraft flap position indicator and flap position transducer support the use, and are used to indicate aircraft flap angle.If its instruction numerical value is inaccurate, driver's interpretation can be affected, therefore, must verify it before installation, ensure that it is functional.The verification of existing aircraft flap position indicator is generally completed by complicated aircraft position reporter calibration equipment, its complex structure, expensive, maintenance cost is high, when needs carry out verification detection to aircraft flap position indicator separately, not easy reliable special checking system, thus cause the problem of verification high expensive.
Summary of the invention
The technical problem to be solved in the present invention: the problem of aircraft flap position indicator not being carried out to the easy reliable system of verification separately traditionally.
Technical scheme of the present invention: a kind of check system of flap indicator, comprise 4C-S291 test turntable 1, sensor 2, D.C. regulated power supply 3, buzzing frame 4 and ZEY-1E flap indicator 5, wherein, 220V AC power is responsible for powering to D.C. regulated power supply 3 and buzzing frame 4, ZEY-1E flap indicator 5 is placed on buzzing frame 4, buzzing frame 4 shakes simulated aircraft vibrating state, D.C. regulated power supply 3 is responsible for powering to sensor 2, 4C-S291 test turntable 1 simulates flap angle signal, ZEY-1E flap indicator device 5 is inputted by sensor 2, finally on ZEY-1E flap indicator 5, demonstrate flap angle data, by to each Data Comparison, complete the precision checking work to ZEY-1E flap indicator 5.
Beneficial effect of the present invention: the present invention is by adopting 4C-S291 test turntable in conjunction with block combiner such as sensor special, buzzing frame, D.C. regulated power supplies, constitute simple and effective flap indicator check system, reasonable in design, staff is when detecting sensor, outside connection is simple, easy and simple to handle, solve and the demand that low cost verifies separately is carried out to flap indicator.This exerciser can be tested sensor performance on the one hand, avoids fault product directly to install, thus improves efficiency and the quality of aircraft general assembly, simplifies test routine on the other hand, improve work efficiency, and this exerciser also has compatibility.
Accompanying drawing explanation
Fig. 1 is system architecture schematic diagram of the present invention, and wherein, 1 is 4C-S291 test turntable, and 2 is sensor, and 3 is D.C. regulated power supply, and 4 is buzzing frame, and 5 is ZEY-1E flap indicator.
Embodiment
Below in conjunction with Figure of description, installation of the present invention and working method are described.
In global design process, selecting of components and parts all meets GJB546-1996 component quality guarantee specification.
With reference to figure 1, external 220V power supply, produces 28V voltage to system power supply through adjustable DC power supply.
1) check before energising
Connect the line by Fig. 1, check that whether wiring is firm.Rotate test turntable handle, make test turntable 1 pointer aim at index dial zero degree.Be arranged on by sensor on the support of 4C-S291 test turntable 1, rotation sensor 2 makes ZEY-1E indicator pointer indicate zero, then tightens the support of fixation of sensor.
2) energizing test
Rotate 4C-S291 test turntable 1 handle, make its dial needle aim at index dial zero degree, sensor 2 is arranged on 4C-S291 test turntable 1.Indicator 5 is arranged on buzzing frame 4, with private cable connecting sensor 2 and indicator 5, D.C. regulated power supply 3 is connected 220V AC power, power light ignites, switch is got to 27V position, by 27V switch connection, adjustment set screw, voltage table gauge outfit is made to indicate 27V, for sensor 2 is powered.Buzzing bridge joint is led to 220V power supply, should hear buzzer, simulated aircraft shakes.
Rotate 4C-S291 test turntable 1 handle, make that the pointer of indicator 5 points in the middle of 0 scale mark respectively, the end of 10 scale marks, the centre of 20 scale marks, at this moment the angle value reading 4C-S291 test turntable 1 is not more than 2 ° with the difference of 0 °, 72.7 °, 136 ° respectively, represents the index error passed examination of indicator 5.
Rotate 4C-S291 test turntable 1 handle, make that the pointer of indicator 5 points in the middle of 0 scale mark respectively, the end of 10 scale marks, the centre of 20 scale marks, and then inhour is rotated, and makes that the pointer of indicator 5 indicates in the middle of 20 scale marks respectively, the end of 10 scale marks, the centre of 0 scale mark, under these two kinds of environment, read the angle value of 4C-S291 test turntable 1 respectively, it is poor is accordingly lag error, error is not more than 4 °, represents the lag error passed examination of indicator 5.
Rotate 4C-S291 test turntable 1 handle, in the middle of pointed 0 scale mark making indicator 5, then by the working position of indicator respectively to left and right and turn forward 45 °, now the indicated value of indicator 5 and entopic indicated value error are not more than 2 °, represent the balance passed examination of indicator 5.
Namely above qualified thinks that indicator 5 meets aircraft installation requirement.
Claims (1)
1. the check system of a flap indicator, comprise 4C-S291 test turntable (1), sensor (2), D.C. regulated power supply (3), buzzing frame (4) and ZEY-1E flap indicator (5), wherein, 220V AC power is responsible for D.C. regulated power supply (3) and buzzing frame (4) power supply, ZEY-1E flap indicator (5) is placed on buzzing frame (4), buzzing frame (4) vibrations simulated aircraft vibrating state, D.C. regulated power supply (3) is responsible for powering to sensor (2), 4C-S291 test turntable (1) simulates flap angle signal, by sensor (2) input ZEY-1E flap indicator device (5), finally on ZEY-1E flap indicator (5), demonstrate flap angle data, by to each Data Comparison, complete the precision checking work to ZEY-1E flap indicator (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410143136.8A CN104976981A (en) | 2014-04-10 | 2014-04-10 | Flap position indicator verification system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410143136.8A CN104976981A (en) | 2014-04-10 | 2014-04-10 | Flap position indicator verification system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104976981A true CN104976981A (en) | 2015-10-14 |
Family
ID=54273720
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410143136.8A Pending CN104976981A (en) | 2014-04-10 | 2014-04-10 | Flap position indicator verification system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104976981A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108536175A (en) * | 2017-03-06 | 2018-09-14 | 陕西飞机工业（集团）有限公司 | A kind of flap configuration output mechanism angular adjustment apparatus |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4276702A (en) * | 1976-12-06 | 1981-07-07 | Pacer Systems, Inc. | Aircraft flight simulating trainer |
| CN101886994A (en) * | 2010-07-20 | 2010-11-17 | 武汉航达航空科技发展有限公司 | Large-torque actuator loading testboard |
| CN102686982A (en) * | 2009-11-26 | 2012-09-19 | 莱卡地球系统公开股份有限公司 | Calibration method and angle measuring method for an angle measuring device, and angle measuring device |
| CN202903130U (en) * | 2012-11-14 | 2013-04-24 | 中国科学院沈阳计算技术研究所有限公司 | Electric adjustment experiment testing device |
| CN203053397U (en) * | 2012-11-16 | 2013-07-10 | 哈尔滨飞机工业集团有限责任公司 | Tab position meter tester |
| CN103979112A (en) * | 2013-02-08 | 2014-08-13 | 通用电气航空系统有限公司 | Method for predicting a trailing edge flap fault |
-
2014
- 2014-04-10 CN CN201410143136.8A patent/CN104976981A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4276702A (en) * | 1976-12-06 | 1981-07-07 | Pacer Systems, Inc. | Aircraft flight simulating trainer |
| CN102686982A (en) * | 2009-11-26 | 2012-09-19 | 莱卡地球系统公开股份有限公司 | Calibration method and angle measuring method for an angle measuring device, and angle measuring device |
| CN101886994A (en) * | 2010-07-20 | 2010-11-17 | 武汉航达航空科技发展有限公司 | Large-torque actuator loading testboard |
| CN202903130U (en) * | 2012-11-14 | 2013-04-24 | 中国科学院沈阳计算技术研究所有限公司 | Electric adjustment experiment testing device |
| CN203053397U (en) * | 2012-11-16 | 2013-07-10 | 哈尔滨飞机工业集团有限责任公司 | Tab position meter tester |
| CN103979112A (en) * | 2013-02-08 | 2014-08-13 | 通用电气航空系统有限公司 | Method for predicting a trailing edge flap fault |
Non-Patent Citations (2)
| Title |
|---|
| 《航空制造工程手册》总编委会: "飞机调试与试验", 《航空制造工程手册•飞机装配》 * |
| 谢春华等: "襟翼位置指示器通用规范", 《中华人民共和国航空行业标准》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108536175A (en) * | 2017-03-06 | 2018-09-14 | 陕西飞机工业（集团）有限公司 | A kind of flap configuration output mechanism angular adjustment apparatus |
| CN108536175B (en) * | 2017-03-06 | 2019-11-15 | 陕西飞机工业（集团）有限公司 | A kind of flap configuration output mechanism angular adjustment apparatus |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101915902B (en) | Calibration method and calibration system for field test equipment | |
| CN106705823A (en) | Field calibration method for linear displacement sensor | |
| CN102155214B (en) | Detection device for gyrolevel | |
| CN103234698A (en) | Low-static pressure differential transmitter calibration instrument | |
| CN103837071B (en) | Bar displacement transducer angular surveying fixture | |
| CN203011706U (en) | Multi-variety microcomputer control unit brake test bench | |
| CN207650567U (en) | Mechanical watch precision tester | |
| CN204189034U (en) | A kind of engine pedestal centralising device | |
| CN104976981A (en) | Flap position indicator verification system | |
| CN103995153B (en) | A kind of elevator governor tester responsiveness calibrating installation | |
| CN105091834A (en) | Position indicator tester | |
| CN104359618A (en) | Device for field calibration of dynamometer torquemeter of rotary mechanical test bed | |
| CN102200778A (en) | Device for automatically calibrating parameters of regulators | |
| CN103023497A (en) | Digital signal and analog signal conversion accuracy test method of selsyn module | |
| CN202562619U (en) | Multi-point continuous on-line vibrating screen amplitude detector | |
| CN109238892A (en) | A kind of rotor-support-foundation system endless-ringlock bullet branch Structural Strength Design and on-line monitoring method | |
| CN201965485U (en) | Automatic verifying device for adjustor parameters | |
| CN109186498A (en) | A kind of integrated correction device | |
| CN103542876A (en) | Automatic testing device for resolver-to-digital converter | |
| CN207457373U (en) | A kind of test platform of portable control motor digital quantizer | |
| CN108153140A (en) | Mechanical watch precision tester | |
| CN109883793A (en) | A kind of true triaxial test undisturbed soil sample preparation facilities | |
| CN204027765U (en) | The locked rotor torque pick-up unit of running torque test board | |
| CN109533384A (en) | A kind of electric steering engine fast zero-setting method | |
| Huiru | Design and Implementation of Mechanical Instrument for Flight Simulator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20151014 |
|
| WD01 | Invention patent application deemed withdrawn after publication |