CN201580560U - Anti-skid control recorder - Google Patents
Anti-skid control recorder Download PDFInfo
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- CN201580560U CN201580560U CN 200920245948 CN200920245948U CN201580560U CN 201580560 U CN201580560 U CN 201580560U CN 200920245948 CN200920245948 CN 200920245948 CN 200920245948 U CN200920245948 U CN 200920245948U CN 201580560 U CN201580560 U CN 201580560U
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Abstract
The utility model relates to an anti-skid control recorder. Main circuits and devices comprise a power supply module, a conversion circuit, a digital signal processor (DSP), a storage module, a communication interface and a clock circuit, wherein the conversion circuit is mainly used for carrying out conversion on an aircraft brake instruction signal, a wheel speed signal and a servo valve current signal; the aircraft brake instruction signal is a direct-current voltage signal which is less than 5V and output by a brake instruction sensor, and forms an amplitude limiting circuit by a diode and then AD acquisition is carried out by the DSP; and the storage module and a DSP chip are connected by a data bus. The anti-skid control recorder leads an aircraft electronic anti-skid brake system to have a function of recording state parameter/data. According to the brake data of every landing of an aircraft recorded in the recorder, ground crews can judge the working state of an aircraft brake system, or judge fault causes when the system fails, and carry out fault location, so as to ensure removal of the faults at farthest speed, adapt to the development of the modern process technology level, and improve the level of use and maintenance of the aircraft.
Description
Technical field
The invention belongs to aircraft antiskid control apparatus field, specifically is a kind of anti-skidding control logger.
Background technology
Present generation aircraft generally all has been equipped with electronic anti-skid braking system, in order to prevent the quick-fried tire of stopping, shortens landing distance, improves braking efficiency and safety in utilization.Be in operation, anti-skidding control capsule is according to the signal of wheel spin-up transducer input, judge whether wheel skids or soon skid, after treatment to servovalve output corresponding control current signal, in time regulate wheel braking pressure, make wheel braking moment remain on the maximum torque level (tire-ground maximum combined factor just) that this moment, runway ground can provide.Existing anti-skidding control capsule does not have writing function to aircraft landing brake and the various state parameters of ground taxi manipulation brake process, this is to the use monitoring of the anti-skidding control of brake system, trouble-shooting, and the aircraft accident investigation is made troubles, press for brake system in the practice and also have writing function, recording parameters is wheel speed and servovalve electric current at least.
Summary of the invention
For overcoming the deficiency that can not write down aircraft landing brake and the various state parameters of ground taxi manipulation brake process that exists in the prior art, the present invention proposes a kind of anti-skidding control logger.
The technology of the present invention solution is: be core with DSP, gather in real time, handle, the various state parameters of storage brake process, when needing, the data of recording storage are unloaded, for analyzing use.
Main circuit of the present invention and device comprise power module, change-over circuit, digital signal processor, memory module, communication interface and clock circuit, and change-over circuit is mainly used in to be changed aircraft brake command signal, wheel speed signal and servovalve current signal; The aircraft brake command signal is the d. c. voltage signal less than 5V by the output of brake instruction sensor, by the limiter circuit that diode is formed, carries out AD by DSP then and gathers; It is characterized in that memory module is connected by data bus with dsp chip, realize the transmission of data storage.
D0～the D14 of memory module inserts the D0～D14 of data bus respectively; A0～A14 inserts the A0～A14 of data bus respectively; / CE ,/OE is connected with PC0, PC1, the PC2 pin of TMS320F240 respectively with/WE.
10 bit A/D converters built-in by DSP carry out data acquisition; Each AD input port all must have limiter circuit.
Clock circuit is selected DS1302 for use; DS1302 and dsp chip carry out communication by spi bus, on I/O mouth PB1, the PB2 and PB3 that clock pin SCLK, the resetting pin RET of DS1302, data line I/O are connected on TMS320F240 respectively.
Communication interface adopts RS485 bus MAX485 chip; MAX485 and dsp chip TMS320F240 carry out communication by the SCI bus.
The DI pin of MAX485 connects the SCITXD pin of TMS320F240; The RO pin of MAX485 connects the SCIRXD pin of TMS320F240; MAX485 /RE and DE short circuit meet the PB0 of TMS320F240.
The present invention is used for fax brake, minimumly can write down brake instruction, wheel speed and three parameters of servovalve electric current; And traditional electronic anti-skid braking system does not have the record data function.DSP of the present invention is used to receive, the next signal of computing load module transmission, output result, the coordinated operation of control each several part; Memory module is used to preserve the data of needs record; Communication interface is used to unload record data.The anti-skidding control logger that the present invention proposes is built in the anti-skidding control capsule, to make full use of existing resources, is easy to realize.If increase brake temperature sensor, brake pressure sensor, or utilize the brake pressure sensor that has now on the pipeline, can also write down brake temperature and brake pressure, make recording parameters more comprehensively.
Pin of the present invention makes the aircraft electronic anti-skid braking system have state parameter/data recording function.The brake data that the ground crew rises and falls according to the aircraft that writes down in this logger at every turn, can judge the mode of operation of airplane brake system, perhaps when the system failure, the failure judgement reason, carry out fault localization, guarantee with the fastest speed trouble-shooting, adapt to the development of modern technology level, improve the aircraft utilization maintenance levels.
Description of drawings
Accompanying drawing 1 is the structured flowchart of anti-skidding control logger.
The specific embodiment
Anti-skidding control logger is according to the difference of aircraft type, and particular content is different.
Embodiment one
Present embodiment is a kind of anti-skidding control logger that is used for certain type aircraft, and the data of essential record are brake instruction, wheel speed, servovalve electric current.
Present embodiment is made up of three integrated circuit boards and box body, independently is installed in outside the anti-skidding control capsule, and main circuit and device comprise power module, change-over circuit, digital signal processor, memory module, communication interface and clock circuit.
Change-over circuit is mainly used in to be changed aircraft brake command signal, wheel speed signal and servovalve current signal.
The aircraft brake command signal is the d. c. voltage signal less than 5V by the output of brake instruction sensor, by the limiter circuit that diode is formed, carries out AD by DSP then and gathers.
The wheel speed signal near sinusoidal ripple signal, by the square wave level, produces the square-wave signal of the Transistor-Transistor Logic level identical with frequency input signal from wheel spin-up transducer, and this signal is directly gathered by the capturing unit of DSP.
Servovalve is a current device.Converse the valve electric current at first by collection servovalve valve voltage, and then by Ohm's law.The bleeder circuit that the valve voltage signal is formed by the buffer circuit be made up of emitter follower and resistance just can enter into the AD input port of DSP.
The microcontroller that the control logger of present embodiment adopts is digital signal processor (DSP) the SMJ320F240 chip of TI company.10 bit A/D converters built-in by DSP carry out data acquisition, and in order to protect dsp chip, each AD input port all must have limiter circuit.
Memory module adopts auspicious wound (Ramtron) FM1808 of company, 32k ferroelectric memory.
FM1808 is connected by data bus with dsp chip TMS320F240.D0～D14 inserts the D0～D14 of TMS320F240 data bus respectively; A0～A14 inserts the A0～A14 of TMS320F240 data bus respectively; / CE ,/OE is connected with PC0, PC1, the PC2 pin of TMS320F240 respectively with/WE.
Power module adopts voltage changer, will provide 28 volts direct supplys of anti-skidding control capsule to be transformed to required voltage+15V and+5V.
Clock circuit is selected the DS1302 of Dallas company for use.
DS1302 and dsp chip TMS320F240 carry out communication by spi bus, on I/O mouth PB1, the PB2 and PB3 that clock pin SCLK, the resetting pin RET of DS1302, data line I/O are connected on TMS320F240 respectively.
Communication interface adopts RS485 bus, MAX485 chip.
MAX485 and dsp chip TMS320F240 carry out communication by the SCI bus.The DI pin of MAX485 connects the SCITXD pin of TMS320F240; The RO pin of MAX485 connects the SCIRXD pin of TMS320F240; MAX485 /RE and DE short circuit meet the PB0 of TMS320F240.
Brake parameter recorder operating software adopts the C language compilation, to realize state parameter real-time signal acquisition, record.Wait when needed, read with the data that notebook PC will brake in the parameter recorder by the RS485 bus, and the data of reading are handled and analyzed, the electronic anti-skid braking system operation conditions is made an appraisal by application software.The operation of anti-skidding control logger is as follows: after system's energising, and promptly by certain time interval, for example, with the parameter of gathering in 0.02 second, record will write down.If adopt a ferroelectric memory as memory module, the parameter of record just leaves in this ferroelectric memory, only preserves a brake reference record of rising and falling; The brake parameter recorder will cut off the power supply after undercarriage is packed up, and re-powers when aircraft landing again, therefore, after the brake parameter recorder powers on, must differentiate takeoff condition and landing state, so that carry out the reference record of different conditions.If adopt a ferroelectric memory and a flash media as memory module, ferroelectric memory storage current data, flash media is used for store historical data.Logger is only preserved 6 minutes with interior brake data.
Embodiment two
Present embodiment is a kind of anti-skidding control logger that is used for certain another model aircraft, and the data of essential record are brake instruction, wheel speed, servovalve electric current.
The aircraft brake command signal is converted to and the proportional vdc of sinusoidal waveform amplitude by effective value conversion chip AD536 by the sinusoidal waveform of the adjustable amplitude of brake instruction sensor output, and then carries out AD by DSP and gather.
The wheel speed signal is from wheel spin-up transducer, for near sinusoidal ripple signal,, produce the square-wave signal of the Transistor-Transistor Logic level identical with frequency input signal by the square wave level, this signal is converted to and the proportional d. c. voltage signal of wheel speed by frequency-voltage conversion circuit.AD by DSP gathers again.
Servovalve is a current device.Converse the valve electric current at first by collection servovalve valve voltage, and then by Ohm's law.The bleeder circuit that the valve voltage signal is formed by the buffer circuit be made up of emitter follower and resistance just can enter into the AD input port of DSP.
The microcontroller that the control logger of present embodiment adopts is digital signal processor (DSP) the SMJ320F240 chip of TI company.10 bit A/D converters built-in by DSP carry out data acquisition, and in order to protect dsp chip, each AD input port all must have limiter circuit.
Memory module adopts auspicious wound (Ramtron) FM1808 of company, 32k ferroelectric memory.
FM1808 is connected by data bus with dsp chip TMS320F240.D0～D14 inserts the D0～D14 of TMS320F240 data bus respectively; A0～A14 inserts the A0～A14 of TMS320F240 data bus respectively; / CE ,/OE is connected with PC0, PC1, the PC2 pin of TMS320F240 respectively with/WE.
Power module adopts voltage changer, will provide 28 volts direct supplys of anti-skidding control capsule to be transformed to required voltage+15V and+5V.
Clock circuit is selected the DS1302 of Dallas company for use.
DS1302 and dsp chip TMS320F240 carry out communication by spi bus, on I/O mouth PB1, the PB2 and PB3 that clock pin SCLK, the resetting pin RET of DS1302, data line I/O are connected on TMS320F240 respectively.
Communication interface adopts RS485 bus, MAX485 chip.
MAX485 and dsp chip TMS320F240 carry out communication by the SCI bus.The DI pin of MAX485 connects the SCITXD pin of TMS320F240; The RO pin of MAX485 connects the SCIRXD pin of TMS320F240; MAX485 /RE and DE short circuit meet the PB0 of TMS320F240.
Brake parameter recorder operating software adopts the C language compilation, to realize state parameter real-time signal acquisition, record.Wait when needed, read with the data that notebook PC will brake in the parameter recorder by the RS485 bus, and the data of reading are handled and analyzed, the electronic anti-skid braking system operation conditions is made an appraisal by application software.The operation of anti-skidding control logger is as follows: after system's energising, and promptly by certain time interval, for example, with the parameter of gathering in 0.02 second, record will write down.If adopt a ferroelectric memory as memory module, the parameter of record just leaves in this ferroelectric memory, only preserves a brake reference record of rising and falling; The brake parameter recorder will cut off the power supply after undercarriage is packed up, and re-powers when aircraft landing again, therefore, after the brake parameter recorder powers on, must differentiate takeoff condition and landing state, so that carry out the reference record of different conditions.Logger is only preserved 6 minutes with interior brake data.
Claims (6)
1. anti-skidding control logger, main circuit and device comprise power module, change-over circuit, digital signal processor, memory module, communication interface and clock circuit, and change-over circuit is mainly used in to be changed aircraft brake command signal, wheel speed signal and servovalve current signal; The aircraft brake command signal is the d. c. voltage signal less than 5V by the output of brake instruction sensor, by the limiter circuit that diode is formed, carries out AD by DSP then and gathers; It is characterized in that memory module is connected by data bus with dsp chip.
2. a kind of according to claim 1 anti-skidding control logger is characterized in that the D0～D14 of memory module inserts the D0～D14 of data bus respectively; A0～A14 inserts the A0～A14 of data bus respectively; / CE ,/OE is connected with PC0, PC1, the PC2 pin of TMS320F240 respectively with/WE.
3. a kind of according to claim 1 anti-skidding control logger is characterized in that 10 bit A/D converters built-in by DSP carry out data acquisition; Each AD input port all must have limiter circuit.
4. a kind of according to claim 1 anti-skidding control logger is characterized in that clock circuit is selected DS1302 for use; DS1302 and dsp chip carry out communication by spi bus, on I/O mouth PB1, the PB2 and PB3 that clock pin SCLK, the resetting pin RET of DS1302, data line I/O are connected on TMS320F240 respectively.
5. a kind of according to claim 1 anti-skidding control logger is characterized in that, communication interface adopts RS485 bus MAX485 chip; MAX485 and dsp chip TMS320F240 carry out communication by the SCI bus.
6. as a kind of anti-skidding control logger as described in the claim 5, it is characterized in that the DI pin of MAX485 connects the SCITXD pin of TMS320F240; The RO pin of MAX485 connects the SCIRXD pin of TMS320F240; MAX485 /RE and DE short circuit meet the PB0 of TMS320F240.
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| Application Number | Priority Date | Filing Date | Title |
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| CN 200920245948 CN201580560U (en) | 2009-12-23 | 2009-12-23 | Anti-skid control recorder |
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| CN 200920245948 CN201580560U (en) | 2009-12-23 | 2009-12-23 | Anti-skid control recorder |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102426311A (en) * | 2011-10-13 | 2012-04-25 | 西安航空制动科技有限公司 | Method for determining low-temperature working stress limit of airplane antiskid brake control box |
| CN102426451A (en) * | 2011-12-21 | 2012-04-25 | 西安航空制动科技有限公司 | Acceleration reliability test method for airplane antiskid brake control box |
| CN102426111A (en) * | 2011-10-13 | 2012-04-25 | 西安航空制动科技有限公司 | Method for determining high-temperature working stress limit of airplane antiskid brake control box |
| CN102426313A (en) * | 2011-10-20 | 2012-04-25 | 西安航空制动科技有限公司 | Method for screening high-acceleration stress of aircraft anti-skid brake control box |
| CN102507117A (en) * | 2011-10-13 | 2012-06-20 | 西安航空制动科技有限公司 | Method for determining vibration working stress limit of aircraft anti-skidding braking control box |
| CN104200541A (en) * | 2014-08-25 | 2014-12-10 | 贵州新安航空机械有限责任公司 | Parameter recording device for antiskid braking system of wheel type take-off and landing aircraft |
| CN106005411A (en) * | 2016-07-14 | 2016-10-12 | 辽宁猎鹰航空科技有限公司 | Intelligent warning system for unmanned aerial vehicle |
| CN112093034A (en) * | 2020-09-22 | 2020-12-18 | 青海奥珞威信息科技有限公司 | Rotor magnetomotive unmanned aerial vehicle undercarriage retraction system |
-
2009
- 2009-12-23 CN CN 200920245948 patent/CN201580560U/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102426311A (en) * | 2011-10-13 | 2012-04-25 | 西安航空制动科技有限公司 | Method for determining low-temperature working stress limit of airplane antiskid brake control box |
| CN102426111A (en) * | 2011-10-13 | 2012-04-25 | 西安航空制动科技有限公司 | Method for determining high-temperature working stress limit of airplane antiskid brake control box |
| CN102507117A (en) * | 2011-10-13 | 2012-06-20 | 西安航空制动科技有限公司 | Method for determining vibration working stress limit of aircraft anti-skidding braking control box |
| CN102426311B (en) * | 2011-10-13 | 2013-09-04 | 西安航空制动科技有限公司 | Method for determining low-temperature working stress limit of aircraft anti-skid braking control box |
| CN102426313A (en) * | 2011-10-20 | 2012-04-25 | 西安航空制动科技有限公司 | Method for screening high-acceleration stress of aircraft anti-skid brake control box |
| CN102426451A (en) * | 2011-12-21 | 2012-04-25 | 西安航空制动科技有限公司 | Acceleration reliability test method for airplane antiskid brake control box |
| CN104200541A (en) * | 2014-08-25 | 2014-12-10 | 贵州新安航空机械有限责任公司 | Parameter recording device for antiskid braking system of wheel type take-off and landing aircraft |
| CN106005411A (en) * | 2016-07-14 | 2016-10-12 | 辽宁猎鹰航空科技有限公司 | Intelligent warning system for unmanned aerial vehicle |
| CN112093034A (en) * | 2020-09-22 | 2020-12-18 | 青海奥珞威信息科技有限公司 | Rotor magnetomotive unmanned aerial vehicle undercarriage retraction system |
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Granted publication date: 20100915 |
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