CN2621289Y - Instrument for calibrating dynamic balance measuring equipment of helicopter - Google Patents
Instrument for calibrating dynamic balance measuring equipment of helicopter Download PDFInfo
- Publication number
- CN2621289Y CN2621289Y CN 03257120 CN03257120U CN2621289Y CN 2621289 Y CN2621289 Y CN 2621289Y CN 03257120 CN03257120 CN 03257120 CN 03257120 U CN03257120 U CN 03257120U CN 2621289 Y CN2621289 Y CN 2621289Y
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- housing
- prover
- wave
- circuit board
- keyboard
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Abstract
The utility model belongs to the technical field of measurement, and relates to an instrument used to calibrate helicopter dynamic balance measurement equipments. The utility model comprises an enclosure, a circuit board, a power supply circuit, a keyboard outlet and a display. The utility model is characterized in that a CPU 1, a memorizer 2, an interface circuit 3 and four parallel signal output circuits are provided on the circuit board; each of the signal output circuits consists of a D/A convertor 4 and an amplifier 5, which are connected in series. The calibration device can meet the requirement to calibrate dynamic balance measurement equipments of helicopters of various specifications, and is important for ensuring overall quality of the plane and flight safety.
Description
Technical field
The utility model belongs to field of measuring technique, relates to a kind of instrument that is used to calibrate helicopter dynamic balancing measurement equipment.
Background technology
Rotor cone and dynamic balancing measurement be helicopter production, the important inspection item in using, to the calibration relation of these surveying instruments production and the flight safety to helicopter.At home, owing to still there is not the research of exploitation, production and calibration steps that unit is engaged in dynamic balancing measurement instrument correcting device, there are not calibration criterion and special-purpose correcting device.Abroad, the exploitation of rotor cone and dynamic balancing measurement equipment mainly concentrates on the U.S. and Britain, countries such as France, some of them company develops and safeguards the needs of cone, dynamic balancing measurement equipment for oneself, developed the simple and easy calibration equipment of product special use, for example U.S. CHADWICK company is simple calibrating equipment---the dynamic balance check device MODEL11 of 177M series dynamic balancing measurement equipment configuration.This kind equipment uses hardware to produce needed signal more, and output function is single, it is adjusted be provided with and the relatively difficulty of upgrading.
Summary of the invention
The purpose of this utility model is: a kind of prover that has the multichannel output signal, is used to calibrate helicopter dynamic balancing measurement equipment is provided, the balance of the dynamic balancing measurement equipment of current application on helicopter and PH phasemeter are calibrated and safeguarded, the requirement of flight safety with the urgent need that satisfies helicopter production, scientific research and in using.
The technical solution of the utility model is: helicopter dynamic balancing measurement Equipment Alignment instrument, comprise a housing, be installed in circuit board and power circuit in the housing, a keyboard 10 that is connected with prover by the keyboard socket that is fixed on the housing, a display that is connected with prover by the display socket that is fixed on the housing, it is characterized in that, the embedded type CPU 1 that the work of a control prover is arranged on circuit board, storing for producing sinusoidal wave for one, square wave, four kinds of waveform relative programs of random wave and pulsating wave and memory of data 2, waveform with generation is transported to the interface circuit 3 of D/A converter, CPU1 and storer 2, the input end of interface circuit 3, connect by bus between the keyboard 10; Four tunnel parallel signal output apparatus are arranged on circuit board, every road signal output apparatus is composed in series by a D/A converter 4 and an amplifier 5, the input end of each D/A converter 4 is connected by the output terminal of bus with interface circuit 3, the output terminal of four amplifiers 5 respectively be fixed on housing on tach signal lead-out terminal 6, sinewave output terminal 7, square wave lead-out terminal 8 and random wave lead-out terminal 9 be connected.
The utility model has the advantages that: this prover function is many, precision is high, solved the domestic situation that can not calibrate lifting airscrew cone and dynamic balancing measurement equipment for a long time, can satisfy the needs of production and the use and the scientific research of any model helicopter, overall quality and the flight safety that guarantees aircraft had significance.
Description of drawings
Fig. 1: helicopter dynamic balancing measurement Equipment Alignment instrument schematic diagram.
Fig. 2: helicopter dynamic balancing measurement Equipment Alignment instrument housing stereographic map.
Fig. 3: helicopter dynamic balancing measurement Equipment Alignment instrument main program flow chart.
Embodiment
Below the utility model is described in further details.Referring to Fig. 1,2, the utility model comprises a housing, is installed in circuit board and power circuit in the housing, a keyboard 10 that is connected with prover by the keyboard socket that is fixed on the housing.It is characterized in that, the embedded type CPU 1 that the work of a control prover is arranged on circuit board, storing for producing 2, one interface circuits 3 that the waveform that produces are transported to D/A converter of sine wave, square wave, random wave and four kinds of waveform relative programs of pulsating wave and memory of data for one.Connect by bus between the input end of CPU1 and storer 2, interface circuit 3, the keyboard 10.Four tunnel parallel signal output apparatus are arranged on circuit board, and every road signal output apparatus is composed in series by a D/A converter 4 and an amplifier 5.The input end of each D/A converter 4 is connected by the output terminal of bus with interface circuit 3, the output terminal of four amplifiers 5 respectively be fixed on housing on tach signal lead-out terminal 6, sinewave output terminal 7, square wave lead-out terminal 8 and random wave lead-out terminal 9 be connected.
This prover is the multiparameter special signal source of an employing embedded computer control, it is output as four tunnel synchronous standard signals, wherein the output of lead-out terminal 7,8,9 is respectively sine wave, square wave and random wave, it is the vibration simulate signal, be used for the output of analog acceleration sensor, carry out the calibration and the filter characteristic inspection of dynamic balance measuring instrument rotating speed, amplitude precision.Lead-out terminal 6 output TTL pulsating waves are rotating speed simulate signals, the output of simulation Magnetic Sensor, and it carries out the calibration of balance performance monitor phase accuracy jointly with the vibration simulate signal.Various signals are embedded computer control by CPU, produce needed waveform signal by software.
An embodiment of the present utility model, adopt 80486DX as embedded computer CPU1, storer 2 adopts 71C18160CJ6, and interface circuit 3 adopts the 82C55A chip, D/A converter 4 adopts 16 high-precision chip DAC712U, guarantees that output signal has enough precision and stability.Amplifier adopts high precision operating amplifier OP37G.Can also adopt other chipsets to become circuit of the present utility model.
For the ease of expanded function, on housing, fixing a serial line interface and a parallel interface, they are connected with CPU1 by bus.The utility model can utilize serial paralled interface to be connected with external computing machine, further to carry out program development, obtains more function.
Fig. 3 is a software flow pattern of the present utility model.Master routine is made up of system initialization, generation waveform signal, main body circulation and four parts that log off.System initialization comprises and reads parameter configuration files (channel number, unit, coefficient etc.), initialization graphical interfaces; Generate waveform signal and comprise and read waveform parameter (frequency, amplitude, phase place) file, generate sinusoidal wave, square wave and pulsating wave waveform array, 82C55A bus duty is set, to 82C55A bus I/O port output waveform data; In the main body circulation, check the keyboard input, when keyboard input variable Keynum=#13 (Enter), according to the call parameters setting respectively of the value of menucommand variable Order, dimension setting, the random wave waveform is provided with and system adjusts four subroutines: be provided with in parameter and change in the subroutine and preserve waveform parameters such as frequency, phase place, amplitude; In dimension the unit of display of selecting waveform parameter in the subroutine is set; Be provided with in the subroutine by the various random signals of data file generation ice demonstration any wave-wave shape; Adjust the calibration factor of adjusting each signalling channel in the subroutine in system.With parameter subroutine being set is example, and behind the call subroutine, waveform signal stops output, enter parameter the interface is set, the user preserves data after changing waveform parameter, and system writes the waveform parameter file with amended parameter, regenerate and output waveform signals, return master routine at last.It is when being checked through keyboard input variable Keynum=#24 (Ctrl+X) that system withdraws from the main body circulation.Logging off comprises the output that stops waveform signal, closes graphical interfaces, termination routine.
The course of work of this prover is, program and data that embedded computer CPU1 calls storer 2 stored produce digital signal by converting four road analog voltage signals to by four 16 D/A converters 4 respectively after the parallel interface 3, and simulating signal outputs to corresponding lead-out terminal 6,7,8,9 after amplifier 5 is adjusted.When using the calibration of this prover, tach signal output terminal 6 is connected with the magnetic sensor signal input end of tested dynamic balance measuring instrument, and sinewave output terminal 7 or square wave lead-out terminal 8 are connected with the acceleration transducer signals input end of tested dynamic balance measuring instrument.By keyboard 10 and the display that is connected with prover, can adjust on demand signal parameter such as rotating speed, amplitude, phase place etc.Adjust the rotating speed of prover output signal, rotating speed, amplitude precision and the filter characteristic that amplitude can be calibrated tested instrument; Adjust phase differential between two input signals and can calibrate the phase accuracy of tested instrument.
Claims (2)
1, helicopter dynamic balancing measurement Equipment Alignment instrument, comprise a housing, be installed in circuit board and power circuit in the housing, a keyboard [10] that is connected with prover by the keyboard socket that is fixed on the housing, a display that is connected with prover by the display socket that is fixed on the housing, it is characterized in that, the embedded type CPU [1] that the work of a control prover is arranged on circuit board, storing for producing sinusoidal wave for one, square wave, four kinds of waveform relative programs of random wave and pulsating wave and memory of data [2], waveform with generation is transported to the interface circuit [3] of D/A converter, CPU[1] and storer [2], the input end of interface circuit [3], keyboard connects by bus between [10]; Four tunnel parallel signal output apparatus are arranged on circuit board, every road signal output apparatus is composed in series by a D/A converter [4] and an amplifier [5], the input end of each D/A converter [4] is connected by the output terminal of bus with interface circuit [3], the output terminal of four amplifiers [5] respectively be fixed on housing on tach signal lead-out terminal [6], sinewave output terminal [7], square wave lead-out terminal [8] and random wave lead-out terminal [9] be connected.
2, prover according to claim 1 is characterized in that, is fixing a serial line interface and a parallel interface on housing, and they are by bus and CPU[1] be connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 03257120 CN2621289Y (en) | 2003-05-09 | 2003-05-09 | Instrument for calibrating dynamic balance measuring equipment of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 03257120 CN2621289Y (en) | 2003-05-09 | 2003-05-09 | Instrument for calibrating dynamic balance measuring equipment of helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2621289Y true CN2621289Y (en) | 2004-06-23 |
Family
ID=34254132
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 03257120 Expired - Fee Related CN2621289Y (en) | 2003-05-09 | 2003-05-09 | Instrument for calibrating dynamic balance measuring equipment of helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2621289Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102410905A (en) * | 2011-12-14 | 2012-04-11 | 中国人民解放军总参谋部第六十研究所 | Rotational inertia and center of gravity integrated measuring apparatus for unmanned helicopter |
| CN104569885A (en) * | 2013-10-21 | 2015-04-29 | 哈尔滨飞机工业集团有限责任公司 | Onsite calibration method for synchro transmitter or analyzer |
| CN108627190A (en) * | 2017-07-28 | 2018-10-09 | 无锡思泰迪半导体有限公司 | A kind of high-precision Magnetic Sensor correcting structure and bearing calibration based on integrated circuit |
-
2003
- 2003-05-09 CN CN 03257120 patent/CN2621289Y/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102410905A (en) * | 2011-12-14 | 2012-04-11 | 中国人民解放军总参谋部第六十研究所 | Rotational inertia and center of gravity integrated measuring apparatus for unmanned helicopter |
| CN102410905B (en) * | 2011-12-14 | 2014-03-26 | 中国人民解放军总参谋部第六十研究所 | Rotational inertia and center of gravity integrated measuring apparatus for unmanned helicopter |
| CN104569885A (en) * | 2013-10-21 | 2015-04-29 | 哈尔滨飞机工业集团有限责任公司 | Onsite calibration method for synchro transmitter or analyzer |
| CN104569885B (en) * | 2013-10-21 | 2017-07-25 | 哈尔滨飞机工业集团有限责任公司 | A kind of method for realizing synchrotransmitter/resolver field calibration |
| CN108627190A (en) * | 2017-07-28 | 2018-10-09 | 无锡思泰迪半导体有限公司 | A kind of high-precision Magnetic Sensor correcting structure and bearing calibration based on integrated circuit |
| CN108627190B (en) * | 2017-07-28 | 2023-12-19 | 杭州思泰微电子有限公司 | High-precision magnetic sensor correction structure and correction method based on integrated circuit |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20040623 Termination date: 20120509 |