CN201242442Y - Aeroplane magnetic compass calibration equipment employing split type structure - Google Patents
Aeroplane magnetic compass calibration equipment employing split type structure Download PDFInfo
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- CN201242442Y CN201242442Y CNU2008200298307U CN200820029830U CN201242442Y CN 201242442 Y CN201242442 Y CN 201242442Y CN U2008200298307 U CNU2008200298307 U CN U2008200298307U CN 200820029830 U CN200820029830 U CN 200820029830U CN 201242442 Y CN201242442 Y CN 201242442Y
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Abstract
The utility model belongs to a plane magnetic compass calibration device with split structure in measuring instruments, which is mainly formed by a sensor component which is mainly used to collect geomagnetism and gravity acceleration signals, and a hand-operated device component which is mainly used to resolve, display and store the magnetic azimuth, wherein the sensor component and the hand-operated device component exchange data through a wireless data set or an R S 422 bus. The utility model does not need special personnel to read the azimuth of the compass calibration device, reduces the dangers of calibrating the compass, can continuously calculate the current magnetic reference azimuth real-timely, and can facilitate the calibration staff in an engine compartment to real-timely check the values on a calibration instrument and a magnetic compass on a plane, namely compass errors.
Description
Technical field
The utility model belongs to the measurement instrument technical field, particularly to the calibration equipment of magnetic compass, is mainly used in Aeronautics and Astronautics, measurement, geology, field of mining.
Background technology:
The demarcation of aircraft magnetic compasses is to bother also to be absolutely necessary one most in the aircraft flight meter calibration to work always, even the Small Universal aircraft of a similar eaglet 500 of verification sometimes, 5 skilled strong labour powers also can only finish 1 at one day time
-3 compass calibration.Because magnetic compass could be calibrated magnetic deviation after must installing aboard, rotate 360 ° to verify the accuracy of airborne compass so will promote aircraft on the ground, be commonly called as " pushing away aircraft ", and the compass correcting device just provides the magnetic azimuth benchmark.The using method of original mechanical type prover (as Fig. 1), be to be fixed in (2 are the vector datum line among Fig. 1) on the directional reference line of course, when rotating aircraft, the direction that direction that prover provides and airborne compass provide is poor, is exactly the magnetic heading error of aircraft airborne magnetic compass.Because azimuth mirror need be installed in the place of aircraft magnetic interference minimum, generally be at tail (baby plane, 1 is somascope among Fig. 1) or machine back (large aircraft), the people (the represented personnel of b, c among Fig. 1) that (be commonly called as and push away aircraft) needs the people (the represented personnel of a among Fig. 1) of observation and inspection instrument, the people (the represented personnel of d among Fig. 1) who observes the cabin compass and ground to promote aircraft when rotating aircraft closely cooperates, shift aircraft onto certain course by a commander earlier, observe compass heading by d again, determine the course error of compass, b, c are responsible for rotating aircraft.The swing a compass error has following problem like this:
1, in use, mechanical type magnetic deviation azimuth mirror needs a people specially at the other reading of compass prover, and in the measurement of large aircraft, the tester need stand in apart from several meters high on ground and the airframe that rotates at any time, finish 360 ° of courses and demarcate, certain danger is arranged.
2, in the fuselage rotating process, machinery refers to and can rock, and can't read current magnetic reference bearing continuously, also can't pass through the real-time transmission magnetic reference bearing of sound.
Summary of the invention
Consider that existing aircraft magnetic compasses calibrating installation is the mechanical type prover, adopt the most original compass principle, special messenger's meter reading must be arranged,, just can address the above problem if can adopt digital sensor and adopt split-type design.
Therefore first purpose of the present invention is arranged separately on the fuselage with digitized sensor, does not need the professional to read the orientation of compass prover, reduces the danger of swing a compass.
Second purpose of the present invention can be calculated current magnetic reference bearing continuously, in real time with three axis fluxgate sensors and two axis accelerometers.
The 3rd purpose of the present invention passes the difference that the calibration person that can make in the cabin checks magnetic compass on prover and the machine in real time, i.e. compass error by split design, wireless data sending or RS422 number of buses.
Technical scheme: adopting the device for calibrating aircraft magnetic compasses of split-type structural, is to be made of the pick-up transducers of mainly finishing earth magnetism, acceleration of gravity signal and two parts of the manual operator that resolves, shows and store of mainly finishing the magnetic azimuth; Carry out exchanges data by wireless data sending or RS422 bus between sensor element and the manual operator parts.
Sensor element inside comprises: one three axis fluxgate sensor, two axle acceleration sensors, signal conditioning circuit, multi-sampling circuit, microprocessor, wireless data transmission module, RS422 bus switching circuit, battery and an electric power management circuit; One three axis fluxgate sensor and one two axle acceleration sensor insert signal conditioning circuit, multi-sampling circuit, microprocessor simultaneously successively; Microprocessor carries out exchanges data by wireless data transmission module or RS422 bus and manual operator parts simultaneously.
The manual operator components interior comprises: the wide temperature display of OLED, keyboard, microprocessor board mass storage, wireless data transmission module, RS422 bus switching circuit, battery and electric power management circuit, and for expanding other bus spare interface; Wireless data transmission module wherein and RS422 bus switching circuit are accepted to calculate position angle liquor charging crystal display demonstration in real time from the microprocessor by manual operator after the digital signal of sensor element.The manual operator parts are reserved with interfaces such as RS232, RS485, for the calibration digital compass is made design margin.
The utility model beneficial effect:
The utility model does not need the professional to read the orientation of compass prover, reduces the danger of swing a compass; Can calculate current magnetic reference bearing continuously, in real time, and can make calibration person in the cabin check the difference of magnetic compass on prover and the machine, i.e. compass error in real time.
Description of drawings:
Fig. 1 is a synoptic diagram, and present aircraft compass calibration steps is described;
Fig. 2 is a synoptic diagram, and aircraft compass calibration steps of the present invention is described;
Fig. 3 is a circuit block diagram, and theory structure of the present invention is described;
Embodiment:
As shown in Figure 3, the utility model is divided into manual operator and two parts of sensor, sensor element is mainly finished the collection of earth magnetism, acceleration of gravity signal, the manual operator parts are mainly finished resolving, show and storing of magnetic azimuth, carry out exchanges data by wireless data sending or RS422 bus between two parts.
Sensor element inside comprises: one three axis fluxgate sensor, two axle acceleration sensors, signal conditioning circuit, multi-sampling circuit, microprocessor, wireless data transmission module, RS422 bus switching circuit, battery and an electric power management circuit.Magnetic Sensor level (course), tilt (roll), tilt forward and back (pitching) three axially on signal magnetic field sensitively, send to manual operator by wireless data transmission module after being converted to digital signal by signal condition, sample circuit.Because sensor is installed level fully, add the sensor that two velographs also arrive sensitivity and the angle of earth surface level, send to manual operator by wireless data transmission module after also being converted to digital signal by signal condition, sample circuit.
The manual operator components interior comprises: the wide temperature display of 0LED, keyboard, microprocessor board, mass storage, wireless data transmission module, RS422 bus switching circuit, battery and electric power management circuit, and for expanding other bus spare interface.Manual operator for the Magnetic Sensor sensitivity to the ground magnetic signal and accelerometer sensitive to the horizontal sextant angle signal set up a trigonometric function, just can calculate current magnetic azimuth (being commonly referred to as the strapdown algorithm) by resolving trigonometric function.Because pushing away aircraft is a motion process, magnetic signal and horizontal signal are also in dynamic change, and by the mathematical model of setting up, the CUP of manual operator calculates position angle liquor charging crystal display in real time and shows.The user determines the compass error of aircraft compass according to the displayed value of compass on the manual operator displayed value contrast machine.
Compass compensation method of the present invention as shown in Figure 2, sensor element of the present invention is fixed on the directional reference line of course by sensor axis (1 is somascope among Fig. 2,2 is the vector datum line among Fig. 1), open probe power, people (the represented personnel of d among Fig. 2) the band manual operator of observing the cabin compass when rotating aircraft is sitting in the cabin, directly command ground to promote the people (b among Fig. 2 of aircraft by the magnetic heading value that shows on the manual operator, the personnel that c is represented), and check that manual operator shows and the difference of airborne magnetic compass demonstration, determine the course error of compass, b, c is responsible for rotating aircraft.
If what need correction is digital compass, then the digital interface of digital compass can be connected (needing digital compass digital interface relation) with the manual operator interface, d it goes without doing any work, only needing b, c to push away aircraft by certain speed rotates a circle, prover just can be imported airborne magnetic compass to correct magnetic azimuth, finishes the compass compensation of aircraft.The people (the represented personnel of a among Fig. 1) who in proofreading and correct the magnetic compass process, no longer needs the observation and inspection instrument
The utility model principle: the terrestrial magnetic field of three directions of three axis fluxgate sensor sensings, the responsive earth acceleration of gravity of two axle acceleration sensors direction, because surface level is vertical with gravity direction, so can obtain angle component when three directions of front sensor and horizontal direction.The signal of acceleration transducer and Magnetic Sensor is very faint, needs to convert digital signal to by carrying out the A/D sampling after the modulate circuit amplification, outwards sends by RS422 bus or wireless data transmission module then.
Because sensor is horizontal positioned fully, so there are angle in the magnetic signal and the surface level of Magnetic Sensor induction.Manual operator is received the data that sensor is sent by wireless data transmission module or RS422 bus interface, and the angle component that utilizes acceleration measuring to measure can be revised three magnetic signal, calculates correct horizontal magnetic field intensity, further calculates the magnetic azimuth.On the wide temperature display of 0LED, show at last, can count record in mass storage simultaneously.Also be reserved with interfaces such as RS232, RS485 on the manual operator, for the calibration digital compass is made design margin.
Claims (4)
1, adopts the device for calibrating aircraft magnetic compasses of split-type structural, it is characterized in that constituting by the pick-up transducers of mainly finishing earth magnetism, acceleration of gravity signal and two parts of the manual operator that resolves, shows and store of mainly finishing the magnetic azimuth; Carry out exchanges data by wireless data sending or RS422 bus between sensor element and the manual operator parts.
2, the device for calibrating aircraft magnetic compasses of employing split-type structural according to claim 1 is characterized in that sensor element inside comprises: one three axis fluxgate sensor, two axle acceleration sensors, signal conditioning circuit, multi-sampling circuit, microprocessor, wireless data transmission module, RS422 bus switching circuit, battery and an electric power management circuit; One three axis fluxgate sensor and one two axle acceleration sensor insert signal conditioning circuit, multi-sampling circuit, microprocessor simultaneously successively; Microprocessor carries out exchanges data by wireless data transmission module or RS422 bus and manual operator parts simultaneously.
3, the device for calibrating aircraft magnetic compasses of employing split-type structural according to claim 1, it is characterized in that the manual operator components interior comprises: the wide temperature display of OLED, keyboard, microprocessor board, mass storage, wireless data transmission module, RS422 bus switching circuit, battery and electric power management circuit, and for expanding other bus spare interface; Wireless data transmission module wherein and RS422 bus switching circuit are accepted to calculate position angle liquor charging crystal display demonstration in real time from the microprocessor by manual operator after the digital signal of sensor element.
4, the device for calibrating aircraft magnetic compasses of employing split-type structural according to claim 3 is characterized in that the manual operator parts are reserved with interfaces such as RS232, RS485, for the calibration digital compass is made design margin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008200298307U CN201242442Y (en) | 2008-07-29 | 2008-07-29 | Aeroplane magnetic compass calibration equipment employing split type structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008200298307U CN201242442Y (en) | 2008-07-29 | 2008-07-29 | Aeroplane magnetic compass calibration equipment employing split type structure |
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| Publication Number | Publication Date |
|---|---|
| CN201242442Y true CN201242442Y (en) | 2009-05-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNU2008200298307U Expired - Lifetime CN201242442Y (en) | 2008-07-29 | 2008-07-29 | Aeroplane magnetic compass calibration equipment employing split type structure |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN102305624A (en) * | 2011-05-11 | 2012-01-04 | 西安飞机工业（集团）有限责任公司 | Method for calibrating compass |
| CN102520263A (en) * | 2011-12-12 | 2012-06-27 | 中国航空无线电电子研究所 | Identifying method for electromagnetic environment of loader |
| CN106324557A (en) * | 2016-09-23 | 2017-01-11 | 江西洪都航空工业集团有限责任公司 | Radio compass deviation compensation system |
| JP2017173315A (en) * | 2016-03-03 | 2017-09-28 | イノベイティブ ソリューション アンド サポート，インコーポレイティド | Calibration of direction reference system, adjustment system, and method |
| CN108922309A (en) * | 2018-08-14 | 2018-11-30 | 中国人民解放军空军工程大学航空机务士官学校 | A kind of aircraft magnetic deviation calibrated analog training system |
| CN109916385A (en) * | 2019-04-11 | 2019-06-21 | 中国民航大学 | A kind of multi-operation mode aircraft standby compass tester |
| CN112729265A (en) * | 2021-01-21 | 2021-04-30 | 李树峰 | Beidou positioning and orienting method for helicopter compass field calibration |
-
2008
- 2008-07-29 CN CNU2008200298307U patent/CN201242442Y/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN102305624A (en) * | 2011-05-11 | 2012-01-04 | 西安飞机工业（集团）有限责任公司 | Method for calibrating compass |
| CN102305624B (en) * | 2011-05-11 | 2013-10-23 | 西安飞机工业（集团）有限责任公司 | Method for calibrating compass |
| CN102520263A (en) * | 2011-12-12 | 2012-06-27 | 中国航空无线电电子研究所 | Identifying method for electromagnetic environment of loader |
| CN102520263B (en) * | 2011-12-12 | 2014-03-19 | 中国航空无线电电子研究所 | Identifying method for electromagnetic environment of loader |
| JP2017173315A (en) * | 2016-03-03 | 2017-09-28 | イノベイティブ ソリューション アンド サポート，インコーポレイティド | Calibration of direction reference system, adjustment system, and method |
| CN106324557A (en) * | 2016-09-23 | 2017-01-11 | 江西洪都航空工业集团有限责任公司 | Radio compass deviation compensation system |
| CN108922309A (en) * | 2018-08-14 | 2018-11-30 | 中国人民解放军空军工程大学航空机务士官学校 | A kind of aircraft magnetic deviation calibrated analog training system |
| CN108922309B (en) * | 2018-08-14 | 2024-05-28 | 中国人民解放军空军工程大学航空机务士官学校 | Airplane compass calibration simulation training system |
| CN109916385A (en) * | 2019-04-11 | 2019-06-21 | 中国民航大学 | A kind of multi-operation mode aircraft standby compass tester |
| CN109916385B (en) * | 2019-04-11 | 2021-03-05 | 中国民航大学 | Standby compass check meter for airplane with multiple working modes |
| CN112729265A (en) * | 2021-01-21 | 2021-04-30 | 李树峰 | Beidou positioning and orienting method for helicopter compass field calibration |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20090520 |