CN1456864A - Electronic flight instrument system detector - Google Patents
Electronic flight instrument system detector Download PDFInfo
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- CN1456864A CN1456864A CN 03118894 CN03118894A CN1456864A CN 1456864 A CN1456864 A CN 1456864A CN 03118894 CN03118894 CN 03118894 CN 03118894 A CN03118894 A CN 03118894A CN 1456864 A CN1456864 A CN 1456864A
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Abstract
A detector consists of main controller, power supply device, signal controll device I and signal control device II. The digital signal and analog signal generated by the main controller are transmitted to the control device and in the meantime, digital signal, analog signal and switching signal are inputted to EFIS system through signal control device I and II or outputting signal by EFIS to the signal control device for detection. The present invention utilizes industrial control computer as core integrated testing system to obtain complete display picture through simulating the operation state of EFIS on the aeroplane comprehensively.
Description
Technical field
The present invention relates to a kind of EFIS detector.
Background technology
EFIS is the external product of introducing, and installs and must accurately test it aboard.The present domestic EFIS detector that production domesticization is not also arranged, external checkout equipment is comprehensive, and costs an arm and a leg, and is inapplicable.
Summary of the invention
It is the electronic flight system integration testing equipment of core with the industrial control computer that purpose of the present invention is exactly design a kind of.
The present invention is achieved like this, it comprises main control computer, supply unit, signal control device I, signal control device II, flow to control device by main control computer generation digital quantity signal and analog signals, digital quantity signal, analog signals, switching value signal input to the EFIS system or output signal to signal control device by EFIS by signal control device I and signal control device II and detect simultaneously.For the accuracy that guarantees to test, main control computer is carried out following steps: 1. test macro is carried out self check, testing software not only when software startup automatically to the test macro self check, and provide report, and select self-checking function in the drop-down menu with the software operation interface, whether monitoring system is moved normally at any time; 2. carry out initialization operation; 3. respectively 429 signals of atmosphere data, TCN, LOC and the ADF of electronic flight system and the synchronizing signal of HZX system are tested, determined whether data-measuring, revise if desired, then feedback is made amendment; 4. data-measuring is sent to interface arrangement with the data after quantizing; 5. determine whether to interrupt self check, interrupt self check and then feed back to beginning, do not need to interrupt self check, then self check finishes.
The present invention is to be the core integrated test system with the industrial control computer, by equipment comprehensive simulated EFIS duty aboard, to obtain complete display frame, the operator can be detected by the program of computer settings various duties to EFIS.
Description of drawings
Fig. 1 is a fundamental diagram of the present invention.
Fig. 2 is a test procedure process flow diagram of the present invention.
Embodiment
As shown in Figure 1, the present invention includes main control computer, supply unit, signal control device I, signal control device II, flow to control device by main control computer generation digital quantity signal and analog signals, digital quantity signal, analog signals, switching value signal input to the EFIS system or output signal to signal control device by EFIS by signal control device I and signal control device II and measure simultaneously.
As shown in Figure 2, main control computer carries out according to following operation steps: (1) system carries out self check, opens computing machine, clicks " EFIS " shortcut menu, and system carries out self check, if self check is passed through, display then shows normal pictures (not having any information); (2) respectively 429 signals of electronic flight system atmosphere data, TCN, LOC and ADF and the synchronizing signal of HZX system are tested, click " ADC " of normal pictures drop-down menu, click then " NEXT ", then one group of data appears in display, click " NEXT " continuously and many group different pieces of informations then can occur, if will change data, after then can clicking " CUSTOM ", the mouse aligned data can be changed, after having changed, click again " OUTPUT ", data are promptly exported, after test finishes, click " CANCEL ", return normal pictures; (3) data quantize; (4) data after will quantizing are sent to interface arrangement; (5) determine whether to need to interrupt self check, interrupt self check, then feed back to beginning, do not need to interrupt self check, then finish test.
Claims (1)
1, a kind of EFIS detector, it comprises main control computer, supply unit, signal control device I, signal control device II, supply unit connects signal control device I, signal control device II and main control computer, signal control device I is connected EFIS with signal control device II, it is characterized in that computer program execution following steps:
1. test macro is carried out self check, testing software not only when software startup automatically to the test macro self check, and provide report, and from the drop-down menu at software operation interface, select self-checking function, whether monitoring system is moved normally at any time;
2. respectively 429 signals of atmosphere data, TCN, LOC and the ADF of electronic flight system and the synchronizing signal of HZX system are tested, determined whether to revise data, if do not need to revise, then carry out data-measuring, revise if desired, then feedback is made amendment;
3. data-measuring;
4. the data after will quantizing are sent to interface arrangement;
5. determine whether to interrupt self check, interrupt self check and then feed back to beginning, do not need to interrupt self check, then self check finishes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 03118894 CN1230665C (en) | 2003-04-02 | 2003-04-02 | Electronic flight instrument system detector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 03118894 CN1230665C (en) | 2003-04-02 | 2003-04-02 | Electronic flight instrument system detector |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1456864A true CN1456864A (en) | 2003-11-19 |
| CN1230665C CN1230665C (en) | 2005-12-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 03118894 Expired - Fee Related CN1230665C (en) | 2003-04-02 | 2003-04-02 | Electronic flight instrument system detector |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1230665C (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101082641B (en) * | 2006-05-31 | 2010-09-08 | 空中客车德国有限公司 | Signal line tester of flight control system for testing airplane THS motor |
| CN102050226A (en) * | 2009-10-30 | 2011-05-11 | 航天科工惯性技术有限公司 | Aviation emergency instrument, and system initial alignment method and combined navigation algorithm thereof |
| CN102092479A (en) * | 2010-12-30 | 2011-06-15 | 中国商用飞机有限责任公司 | Plane mechanical trip simulator |
| CN102120088A (en) * | 2011-01-28 | 2011-07-13 | 深圳市格兰之特科技有限公司 | System and method for state detection and safety control of flying toy |
| CN102721426A (en) * | 2012-07-17 | 2012-10-10 | 上海市计量测试技术研究院 | Digital display counter calibration system and method |
| CN103033210A (en) * | 2012-12-13 | 2013-04-10 | 中国航空无线电电子研究所 | Simulation testing system of electronic flight instrument system |
| CN103278176A (en) * | 2013-04-27 | 2013-09-04 | 哈尔滨飞机工业集团有限责任公司 | GPS and GNC navigation system test equipment of helicopter |
| CN103913177A (en) * | 2014-03-28 | 2014-07-09 | 吉林大学 | Monitoring device for flying state of rotor craft |
| CN106527397A (en) * | 2016-10-27 | 2017-03-22 | 天利航空科技深圳有限公司 | Aircraft dispenser detection system |
| CN107010222A (en) * | 2016-01-28 | 2017-08-04 | 陕西飞机工业（集团）有限公司 | A kind of photoelectricity drops sighting device |
-
2003
- 2003-04-02 CN CN 03118894 patent/CN1230665C/en not_active Expired - Fee Related
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101082641B (en) * | 2006-05-31 | 2010-09-08 | 空中客车德国有限公司 | Signal line tester of flight control system for testing airplane THS motor |
| CN102050226A (en) * | 2009-10-30 | 2011-05-11 | 航天科工惯性技术有限公司 | Aviation emergency instrument, and system initial alignment method and combined navigation algorithm thereof |
| CN102092479A (en) * | 2010-12-30 | 2011-06-15 | 中国商用飞机有限责任公司 | Plane mechanical trip simulator |
| CN102120088A (en) * | 2011-01-28 | 2011-07-13 | 深圳市格兰之特科技有限公司 | System and method for state detection and safety control of flying toy |
| CN102120088B (en) * | 2011-01-28 | 2012-08-22 | 深圳市格兰之特科技有限公司 | System and method for state detection and safety control of flying toy |
| CN102721426B (en) * | 2012-07-17 | 2015-03-25 | 上海市计量测试技术研究院 | Digital display counter calibration system and method |
| CN102721426A (en) * | 2012-07-17 | 2012-10-10 | 上海市计量测试技术研究院 | Digital display counter calibration system and method |
| CN103033210A (en) * | 2012-12-13 | 2013-04-10 | 中国航空无线电电子研究所 | Simulation testing system of electronic flight instrument system |
| CN103278176A (en) * | 2013-04-27 | 2013-09-04 | 哈尔滨飞机工业集团有限责任公司 | GPS and GNC navigation system test equipment of helicopter |
| CN103278176B (en) * | 2013-04-27 | 2015-10-28 | 哈尔滨飞机工业集团有限责任公司 | A kind of helicopter GPS and GNC navigation system test equipment |
| CN103913177A (en) * | 2014-03-28 | 2014-07-09 | 吉林大学 | Monitoring device for flying state of rotor craft |
| CN107010222A (en) * | 2016-01-28 | 2017-08-04 | 陕西飞机工业（集团）有限公司 | A kind of photoelectricity drops sighting device |
| CN107010222B (en) * | 2016-01-28 | 2019-08-02 | 陕西飞机工业（集团）有限公司 | A kind of photoelectricity air-drop sighting device |
| CN106527397A (en) * | 2016-10-27 | 2017-03-22 | 天利航空科技深圳有限公司 | Aircraft dispenser detection system |
| CN106527397B (en) * | 2016-10-27 | 2018-10-30 | 天利航空科技深圳有限公司 | Aircraft dispenser detecting system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1230665C (en) | 2005-12-07 |
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| C06 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20051207 |