CN106768299A - A kind of real-time vibration monitor system of aircraft based on acceleration transducer and method - Google Patents

Abstract

A kind of real-time vibration monitor system of aircraft based on acceleration transducer, belongs to aviation field, it is characterised in that：The system includes acceleration transducer, signal conditioning circuit, AD Acquisition Circuit, zero calibration circuit, data prediction circuit FPGA and data analysis warning circuit composition partially, system constitutes simple structure, stable system performance, real-time monitoring is functional, is suitable to popularization and application.

Description

A kind of real-time vibration monitor system of aircraft based on acceleration transducer and method

Technical field

The invention belongs to aviation field, more particularly to the real-time vibrating alert system of aircraft based on acceleration transducer.

Background technology

In aviation field, the vibratory output of aircraft is a significant data for concerning flight safety, and especially helicopter, shakes Momentum exception, gently then cause in aircraft personnel fatigue and equipment attrition, it is heavy then cause the housing construction of aircraft and part appearance Resonance, fracture, directly result in aviation accident.So, the monitor in real time for the vibratory output of aircraft is particularly important.This is just needed A real-time monitoring system is wanted, the vibratory output of aircraft can be in real time monitored and alarm letter is sent when aircraft vehicle vibrations amount occurs abnormal Number, so that maintenance personal carries out malfunction elimination to aircraft or pilot takes safe disposal measure.

The content of the invention

In order to achieve the above object, the present invention uses following technical scheme：

The present invention provides a real-time vibrating alert system of aircraft, and the system includes acceleration transducer, signal conditioning circuit, AD Acquisition Circuit, zero calibration circuit, data prediction circuit FPGA and data analysis warning circuit composition partially；

After system electrification, capable calibration is biased by zero data acquisition zero of the calibration circuit to system partially first.It is achieved in that, when After system electrification, FPGA controls the zero analog switch SW1 calibrated partially in circuit that the input of AD Acquisition Circuit is connected into system first In zero-bit, pinpointed by FPGA control AD Acquisition Circuits collection one（32768）System zero bit value, the then system to collecting Zero-bit numerical value averagely, the average value is stored in the internal register of FPGA, used as the zero adjustment value of system；Then The input of AD Acquisition Circuit is accessed sensor signal by the analog switch in the calibration circuit partially of FPGA controls zero, and system completes upper electricity Zero calibration partially, into working condition.

When system works, first, the acceleration transducer on airframe is carried out by sensor drive driving circuit Drive, measure the acceleration signal of aircraft vehicle vibrations after driving by acceleration transducer（0V~2.5V）, after acceleration signal is passed through The signal amplification circuit that end is made up of amplifier carries out 2 times of amplifications to signal（0V~5V）, the acceleration signal feeding quadravalence after amplification Low pass filter is filtered（0 ~ 5KHz of low pass filtered frequency）, filter noise in acceleration signal and beyond frequency range Signal, after filtering after signal feeding AD Acquisition Circuit be acquired, the data of collection are read out by the FPGA of rear end.

After FPGA reads acceleration information, the acceleration information of reading is subtracted into zero adjustment value first, after calibration Acceleration information feeding subsection integral module carries out subsection integral.The Main Function of subsection integral module is to turn acceleration information Speed data is changed to, it is achieved in that every 1024 are divided into one section by the acceleration information of reading, to each point of the segment data Successively with the data summation put before, again divided by sampling period, the as speed data after integration, this is partially completed meter to its result The formula of calculation is as follows：

(k =1,2,3…1024)

(wherein V (k) is current point integrating rate value, and Ai is current point acceleration magnitude, and cal is zero adjustment value, T is sampling week Phase)

Speed data feeding virtual value computing module after subsection integral, having for this section of speed data is gone out by virtual value computing module Valid value, it is achieved in that carries out area summation to rate signal, and concrete methods of realizing is to ask for definitely this section of speed data After value, it is multiplied with the sampling period, then multiplied result adds up, the cumulative and result of output is to represent having for this section of speed data Valid value.The formula that this is partially completed calculating is as follows：

(wherein Sum is this section of virtual value of speed data, and Vi is current point velocity amplitude, and T is the sampling period)

After the virtual value computing module of FPGA calculates the virtual value of the segment data, the data analysis alarm electricity of rear end is sent to Road；

CPU in data analysis warning circuit reads the virtual value of the segment data, and every 10 virtual values are carried out once averagely, averagely Result afterwards is compared as current vibration value with default vibrating alert value, if current vibration value is more than vibrating alert Value, then produce alarm signal.

The real-time vibration monitor system of aircraft based on acceleration transducer of the present invention and method, by by acceleration Sensor, signal conditioning circuit, AD Acquisition Circuit, zero calibration circuit, data prediction circuit FPGA and data analysis alarm partially The combination composition monitoring system of circuit, constitutes simple structure, and stable system performance, real-time monitoring is functional, is suitable to promote and answers With.

Brief description of the drawings

Fig. 1 is circuit theory schematic diagram of the invention；

Fig. 2 is the circuit diagram of embodiment of the present invention.

Specific embodiment

Below in conjunction with the accompanying drawings and the further illustrated in greater detail technical scheme of embodiment

The present invention provides a real-time vibrating alert system of aircraft, as shown in figure 1, the system includes acceleration transducer, signal Modulate circuit, AD Acquisition Circuit, zero calibration circuit, data prediction circuit FPGA and data analysis warning circuit composition partially.

As shown in Fig. 2 in embodiments of the present invention, first from IEPE types acceleration transducer as vibration-measuring device Part.By U3（LT3092）The constant-current source circuit of composition is driven to the acceleration transducer on airframe, by adding Velocity sensor measures the acceleration magnitude of aircraft vehicle vibrations, and acceleration magnitude sends into rear end by capacitance C2, signal condition amplifier U4（AD628）The signal amplifying and conditioning circuit of composition is removed direct current biasing to acceleration signal and signal amplifies, after amplification Acceleration signal send into by U5（MAX274）The fourth order low-pass wave filter of composition carries out LPF, filters the noise in signal With the signal beyond frequency range, after filtering after signal send into by U6（AD7606）The AD Acquisition Circuit of composition is adopted Collection, the data of collection are read out by the FPGA (XCS400AN) of rear end.After FPGA reads acceleration information, data are carried out Subsection integral（Every 1024 points）, acceleration signal is converted into rate signal.Then this section of virtual value of rate signal is calculated And send into the processor of rear end（TMS320F2812）Processed, back-end processor is to every 10 groups of speed virtual value reading Carry out it is average, it is average after result be compared with default vibrating alert value as current vibration value, if current vibration value During more than vibrating alert value, connection alarm indicator on a processor is lighted, send alarm.

Claims (2)

1. the real-time vibration monitor system of a kind of aircraft based on acceleration transducer, it is characterised in that：The system includes acceleration Sensor, signal conditioning circuit, AD Acquisition Circuit, zero calibration circuit, data prediction circuit FPGA and data analysis alarm partially Circuit is constituted.

2. a kind of real-time vibration monitoring method of aircraft based on acceleration transducer, it is characterised in that methods described includes：

First, the acceleration transducer on airframe is driven by sensor drive driving circuit, is passed by acceleration Sensor measures the acceleration voltage value of aircraft vehicle vibrations（0V—2.5V）,

Acceleration voltage value is amplified by the signal amplification circuit that rear end is made up of amplifier to signal（0V—5V）,

Signal feeding low pass filter after amplification is filtered, and filters noise in signal and beyond frequency range（Low pass filtered 0 ~ 5KHz of wave frequency rate,）Signal,

Signal feeding AD Acquisition Circuit after after filtering is acquired, and the data of collection are read out by the FPGA of rear end；

After FPGA reads acceleration information, the data of reading are carried out into zero calibration partially first, the acceleration information after calibration send Entering subsection integral module carries out subsection integral；The Main Function of subsection integral module is that acceleration information is converted into number of speed According to, it is achieved in that every 1024 are divided into one section by the acceleration information of reading, to the segment data each point successively with before The data summation of point, its result is again divided by the sampling period, and the speed data after as integrating, its formula is as follows：

(k =1,2,3…1024)

(wherein V (k) is current point integrating rate value, and Ai is current point acceleration magnitude, and cal is zero adjustment value, T is sampling week Phase)

Speed data feeding virtual value computing module after subsection integral, the effective of this section of speed data is calculated by virtual value Value, it is achieved in that carries out area summation to rate signal, and concrete methods of realizing is that this section of speed data is asked for into absolute value Afterwards, it is multiplied with the sampling period, then multiplied result adds up, the cumulative and result of output is represent this section of speed data effective Value；The formula that this is partially completed calculating is as follows：

(wherein Sum is this section of virtual value of speed data, and Vi is current point velocity amplitude, and T is the sampling period)

After the virtual value computing module of FPGA calculates the virtual value of the segment data, the data analysis alarm electricity of rear end is sent to Road；

Data analysis warning circuit reads the virtual value of the segment data, is compared with warning value set in advance, when the value is big When warning value, alarm signal is produced.