CN101900554A - Method for digitally driving and detecting multi-gauge head gyroscope - Google Patents
Method for digitally driving and detecting multi-gauge head gyroscope Download PDFInfo
- Publication number
- CN101900554A CN101900554A CN 201010210303 CN201010210303A CN101900554A CN 101900554 A CN101900554 A CN 101900554A CN 201010210303 CN201010210303 CN 201010210303 CN 201010210303 A CN201010210303 A CN 201010210303A CN 101900554 A CN101900554 A CN 101900554A
- Authority
- CN
- China
- Prior art keywords
- frequency
- gyro
- signal
- amplitude
- frequency sweep
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Abstract
The invention discloses a method for digitally driving and detecting a multi-gauge head gyroscope, and belongs to the field of micro-mechanical gyroscope signal processing. The method comprises the following steps of: generating a carrier wave Vi by a digital method, simultaneously generating drive signals Vd1, Vd2,..., and VdN by a drive circuit, and loading the carrier wave Vi and the drive signals Vd1, Vd2,..., and VdN on the gauge head 1, the gauge head 2,..., and the gauge head N of the gyroscope in sequence, wherein N is more than or equal to 2; detecting drive mode capacitors C1, C2,..., and CN, adjusting the drive signals Vd1, Vd2,..., and VdN according to the detected signals so as to make the N gauge heads of the gyroscope work at resonance points; and based on the driving of the gyroscope, detecting sensitive mode capacitors C'1, C'2,..., and C'N, obtaining N angular velocity signals of the gyroscope, and according to N frequency sweeping states S1, S2,..., and SN of the gyroscope, processing the detected angular velocity signals and outputting the final angular velocity by a controller. The method is mainly characterized by locking the resonance frequency by a method of detecting the amplitude of the drive output signal by sweep frequency and has the advantages of the realization of self correction, high frequency stability and high anti-interference ability.
Description
One, technical field
The present invention relates to a kind of more top header digitizing driving and detection method, belong to micromechanical gyro signal Processing field.
Two, background technology
Micromechanical gyro is typical inertia device.It is for traditional mechanical gyro, optical fibre gyro and laser gyro, have physical dimension little, in light weight, low in energy consumption, start fast, cost is low, reliability is high and be easy to advantage such as digitizing, therefore range of application enlarges rapidly, can be used for car for guarding against side turned over, flight attitude control, attitude of satellite control, camera is anti-shake, auto-navigation system, various aspects such as Micro Aerial Vehicle.The gyro circuit is the important component part of micromechanical gyro.Traditional mimic channel because the characteristic of analog device itself is inevitably introduced temperature and floated, be difficult to accurately realize from demarcation and self calibration, and digital circuit can not exist temperature to float at calculating process, realizes easily from demarcating and self calibration yet.The micromechanical gyro driving circuit divides open loop and closed loop: the open loop driving circuit all is that the signal with fixed frequency goes to drive gyro work; Closed-loop driving circuit is to use the method for self-sustained oscillation or phaselocked loop that the gyro gauge outfit is operated on the resonance frequency.For the micromechanical gyro system, after the work, total system is floated with regard to there being serious temperature for a long time, can not be used for long work so open loop drives.The number of applying for a patent is 200810223041 patent, propose a kind of micromechanical gyroscope self-exciting and drive demodulating equipment, obtain the vibration displacement voltage signal that micromechanical gyro drives mass and detects mass by input signal interface circuits, singlechip chip extracts level automatic gaining controling algorithm generation gain control signal by amplitude and passes to AGC (automatic gain control) system, AGC (automatic gain control) system produces variable voltage according to the drive displacement signal that gain control signal and input signal interface circuits send, feed back to the adjustment of gyro drive end realization, calculate input angular velocity in the inner demodulation of single-chip microcomputer simultaneously the gyro drive signal.This invention uses single-chip microcomputer to make signal Processing, can reduction system temperature float, and it is integrated to be beneficial to realization.But also exist not enough: system stability was poor when gyro gauge outfit resonance frequency deviation was big.
Three, summary of the invention
In order to overcome the defective on the prior art, the present invention proposes a kind of more top header digitizing driving and detection method, utilize the locking of the method realization gyro gauge outfit resonance frequency of frequency sweep, and drive signal amplitude size is in time proofreaied and correct, detect angular velocity signal simultaneously.
Consult Fig. 1, this method produces carrier wave V by numerical approach
i, produce drive signal V by driving circuit simultaneously
D1, V
D2V
DN, with carrier wave V
iWith drive signal V
D1, V
D2V
DNBe loaded into gyro gauge outfit 1 successively, gyro gauge outfit 2 ... above the gyro gauge outfit N, N 〉=2 are detected and are driven the mode capacitor C
1, C
2C
N, adjust drive signal V according to detected signal
D1, V
D2V
DN, make N gyro gauge outfit be operated in tuning-points.On the basis that gyro drives, detect responsive mode capacitor C '
1, C '
2C '
N, obtain the angular velocity signal of N gyro
By the frequency sweep state S of controller according to N gyro
1, S
2S
N, handle detected angular velocity signal
Export final angular velocity
For each gyro gauge outfit n, the n value is 1,2 ..., N, its back-end circuit is mainly driven by gyro and two parts of angular velocity detection constitute.This paper except that output control, is called gyro n with the driving and the testing circuit of gyro gauge outfit n and its postposition.
A kind of more top header digitizing driving method comprises the steps:
Step 1: on gyro gauge outfit n, load initial driving signal V
DnWith carrier signal V
i, the mass after the signal loading in the gyro gauge outfit can vibrate, and the amplitude of vibration is reflected as capacitor C between two pole plates
n
Wherein, drive signal V
DnFrequency be ω
DnThe inner NCO of digit chip (numerically-controlled oscillator) produces the fixed frequency sine wave signal
Handle the sinusoidal signal V that obtains simulating through rearmounted then
iThe rearmounted processing comprises D/A conversion (digital signal is to analog signal conversion), low-pass filtering, amplification process successively, and this paper rearmounted processing procedure cited below is also identical.And the digital signal of the simulating signal X correspondence of mentioning herein all is expressed as
Step 2: detect gyro gauge outfit n and drive the mode capacitor C
nBy charge amplifier or trans-impedance amplifier, carry out C/V conversion (electric capacity is to the conversion of voltage signal), will drive the plates capacitance C of mode
nVariation delta C
n, be converted into voltage signal C
An
Step 3: the voltage signal V of the gyro n that previous step is obtained
An,, change into digital signal by A/D conversion (simulating signal is to the digital signal conversion)
Send into digital signal processing chip.
Step 4: the digital signal that previous step is obtained
Detect through amplitude, obtain signal
Amplitude
Step 5: data storage.For gyro n, when being in the frequency sweep process, every variation frequency once, with detected signal amplitude
Store.When gyrocontrol was worked, amplitude of every detection was all incited somebody to action
Put into storer, storage detects nearest M the drive signal amplitude of coming
M 〉=2 wherein.
Step 6: when gyro starts, frequency sweep caging n resonance frequency, the frequency control word W that it is corresponding
DnInput NCO produces driving frequency.Every frequency control word that changes then produces the amplitude-frequency correction coefficient k corresponding with frequency simultaneously
N1When gyro is worked,, export instant correction coefficient k according to the amplitude information of monitoring
N2With k
N1And k
N2Addition gets the amplitude rectification coefficient k
nExport.Output frequency sweep status word S when frequency sweep
n, S wherein
nOn behalf of gyro n, value 0 or 1,0 do not have frequency sweep, and 1 represents gyro n just in frequency sweep.Simultaneously in the reading system just at the number S of frequency sweep gyro
NumK wherein
N1, k
N2And k
nBe B position scale-of-two, B 〉=4,
Set F
0Be the amplitude of driving force, ω
dFor driving angular frequency, m
xBe the equivalent mass of driving mode,
Be the resonance angular frequency of driving mode,
For driving the damping ratio of mode, then drive the amplitude B of mode stable oscillation
xFor:
The phase control word bit number of setting NCO is N, and frequency control word is W, and input clock frequency is F
Clk, output signal frequency F then
OutFor:
This step mainly comprises four parts:
1. total system frequency sweep State Control
If experiment records the minimum and the maximal value of the resonance angular frequency of gyro and is followed successively by ω
Min, ω
MaxFor any gyro gauge outfit n, get by formula 1, work as ω
d=ω
x=ω
MinThe time, B
xGet maximal value, promptly detected amplitude is got maximal value, is designated as
When system start-up, gyro n carries out the resonance frequency of frequency sweep locking gauge outfit, S at this moment arbitrarily
Num=N.
After any gyro n frequency sweep is finished, immediately with the standard amplitude
Amplitude with this detection
It is poor to get
Promptly
Set
Be frequency sweep criterion, and
Concrete judgement control is as follows:
(1) works as S
Num〉=h, gyro n do not carry out frequency sweep, and wherein h is that maximum is allowed frequency sweep gyro number, 1≤h N-1;
(2) work as S
Num≤ h-1, and
Gyro n does not carry out frequency sweep, and has and work as
The time, adjust instant amplitude correction coefficient k
N2Adjust amplitude;
2. the generation of frequency control word
Circuit produces the frequency control word of change in the frequency sweep process, input NCO produces corresponding signal, according to driving the mode detected amplitude, finds the frequency control word W of maximum amplitude correspondence
Dn, export.
When gyro starts, get the frequency sweep frequency control word scope W of gyro n correspondence by formula 2
Min_n~W
Max_n, wherein
When gyro starts the back frequency sweep, W
Min_n=W
X_n-Δ W
n, W
Max_n=W
X_n+ Δ W
n, W wherein
X_nBe the frequency control word of the gyro resonance frequency correspondence before this frequency sweep of gyro n,
A complete J level frequency sweep locking resonance frequency workflow is as follows:
During first order frequency sweep, frequency control word is from W
Min_nBeginning is every the time Δ T bigger range delta W that adds up
N1, input NCO produces drive signal input gyro gauge outfit, waits stable back to gather amplitude, sends into storer, through K
N1After inferior, then gather K
N1+ 1 drives amplitude
By controller relatively
Find out maximal value and its corresponding frequency control word W
N11≤Δ W wherein
N1≤ 0.5 (W
Max_n-W
Min_n), K
N1>(W
Max_n-W
Min_n)/Δ W
N1, Δ T>2 π/ω
X_min, M=K
N1+ 1.
Carry out second level frequency sweep then, swept frequency range is from W
N1-Δ W
N1To W
N1+ Δ W
N1, every the time Δ T Δ W that adds up
N2, input NCO produces drive signal input gyro gauge outfit, waits stable back to gather amplitude, through K
N2, inferior after, gather K
N2+ 1 drives amplitude
Find out amplitude maximal value and its corresponding frequency control word W
N21≤Δ W wherein
N2<0.5 Δ W
N1, K
N2>2 Δ W
N1/ Δ W
N2, M=K
N2+ 1.
Carry out third level frequency sweep by same process then, fourth stage frequency sweep ... J level frequency sweep, then the frequency control word W of detected maximum amplitude correspondence in the J level frequency sweep
NJThe frequency control word W of resonance frequency correspondence then
Dn=W
NJOutput.
3. amplitude-frequency correction coefficient k
N1Generation
k
N1Be accompanied by the variation of frequency sweep process medium frequency control word and change.
Push away by formula 1 and 2, when the resonance, i.e. ω
d=ω
x, detected amplitude:
Wherein, G
nBe constant, W
DnFrequency control word during for resonance.Work as ω
Dn=ω
MinThe time,
Get maximal value
Be decided to be the standard amplitude, at this moment the respective frequencies control word
By formula 3 the amplitude-frequency correction coefficient of frequency control word when being W is:
4. instant correction coefficient k
N2Be created in gyro frequency sweep n the time, with k
N2Zero clearing.When gyro n does not have frequency sweep, whenever detect and once drive amplitude
All with the standard amplitude
Compare: when
k
N2On the basis of original value, add Δ k
n, Δ k wherein
n〉=1; When
k
N2On the basis of original value, subtract Δ k
n
Step 7: the frequency control word W of the resonance frequency correspondence that step 6 is obtained
nInput NCO, control NCO produces drive signal
Step 8: with the drive signal of step 7 generation
With the correction coefficient K that produces in the step 6
n, send into the amplitude rectification module, the drive signal behind the output calibration
Then:
Step 9: the rearmounted processing.Digital drive signals after previous step must be proofreaied and correct
Through D/A converter, behind low-pass filter and the amplifier, form final drive signal V
Dn, be added on the gyro gauge outfit n.
A kind of more top header detection method comprises the steps:
Step 1: the responsive mode capacitor C of detection gyro gauge outfit n '
nBy charge amplifier or trans-impedance amplifier, carry out C/V conversion, with responsive mode capacitor C '
nVariation delta C '
n, be converted into voltage signal V
Bn
Step 2: the voltage signal V that previous step is obtained
Bn,, change into digital signal by the A/D conversion
Output.
Step 3: use carrier signal V
iThe digital signal that previous step is obtained
Carry out demodulation, get signal
Step 4: the signal that previous step is obtained
Adopt the logical or low-pass filter elimination radio-frequency component of band, then obtain signal
Step 5: use the drive signal that NCO directly produces in the more top header digitizing driving method step 7
The signal that previous step is obtained
Carry out demodulation, get signal
Step 6: the signal that previous step is obtained
Adopt low-pass filtering elimination radio-frequency component, obtain angular velocity signal
Step 7: the angular velocity signal that previous step is obtained
Drive the frequency sweep status word S that step 6 obtains in the implementation method with gyro
n, carry out computing, obtain final angular velocity signal
Advantage of the present invention is:
1. can realize self-correcting.For with a kind of gyro, when the frequency sweep precision being made as when multistage, the locking certainly in the time of can realizing the frequency large-scope change, and do not need artificial a large amount of debugging, and allow to occur bigger mismachining tolerance, be convenient to commercial production.
2. frequency stability is good.The frequency of all signals of entire circuit all depends on crystal oscillator, and crystal oscillator has very high frequency stability.The stability of this programme itself does not rely on the phase matching degree that gyro drives, and it can realize the locking of wide range of frequencies drift, so be more suitable for working under the long-time and changeable environment.
3. good in anti-interference performance.When gyro is subjected to sudden interference, as the violent impulse of emergentness, because the drive signal of native system is produced by chip internal, the amplitude regulation and control are to gradually change, and do not carry out frequency sweep simultaneously in the work and the stable output of maintenance at any time, so be subjected to very little interference.
Four, description of drawings
Fig. 1 more top header system works block diagram
Fig. 2 gyro n fundamental diagram
Five, embodiment
It is 3 that this example adopts the micromechanical gyro gauge outfit to count N, n value 1,2,3.The resonance angular frequency scope ω of three gyro gauge outfits
XminTo ω
Xmax, ω wherein
Xmin=2 π 2990rad/s, ω
Xmax=2 π 3010rad/s.The quality factor of gyro are Q
x=1000, m
x=m
y=10
-6Kg, driving force F
0=10
-6N, carrier frequency is 100KHz.32 of the phase control words of numeral NCO, clock frequency F
ClkBe 1MHz.Digital signal processing chip is FPGA.The sample frequency of A/D and D/A conversion is 1MHz, 16 of sampling resolutions.
Specific implementation divides gyro to drive and angular velocity detection two parts:
A kind of more top header digitizing driving method comprises the steps:
Step 1: load carrier signal V at gyro gauge outfit n
iWith drive signal V
Dn, the gyro gauge outfit can be vibrated on directions X after the signal loading, and the amplitude of vibration is reflected as two capacitor C between the pole plate
n
The drive signal V that loads during system start-up
D1=V
D2=V
D3=2sin (2 π 2990t) V.
Carrier signal produces frequency 100KHz sine wave signal by the inner NCO of digit chip
Then
T=0/10 wherein
6, 1/10
6, 2/10
6, and the time t in the digital signal is identical below this example.Will
Handle the sinusoidal signal V that obtains simulating through back-end circuit
i=5sin (2 π 10
5T).
Step 2: detect gyro gauge outfit n and drive the mode capacitor C
nBy charge amplifier, carry out the C/V conversion, with Δ C
n, be converted into voltage signal V
An, adopt differential mode to detect electric capacity, feedback capacity C
Fn=1pf, then output voltage is:
Step 3: the voltage signal V that previous step is obtained
An,, change into digital signal by the A/D conversion
If voltage+1V transforms digital signal value 2
14, then
Amplitude 2
14
Step 4: the digital signal that previous step is obtained
Detect through amplitude, obtain signal amplitude
The current amplitude of three gyros then
Step 5: data storage.In the frequency sweep process, every variation frequency is once deposited the drive signal amplitude one time.Amplitude of every detection when steady operation is all incited somebody to action
Put into storer, deposit nearest 128 drive signal amplitudes.For gyro n, the drive signal amplitude of 128 corresponding detections is followed successively by;
Step 6: when gyro starts, frequency sweep locking resonance frequency, the frequency control word W that it is corresponding
DnInput NCO produces drive signal.Every frequency control word that changes then produces the amplitude-frequency correction coefficient k corresponding with frequency simultaneously
N1When gyro is worked,, export instant correction coefficient k according to amplitude information
N2With k
N1And k
N2Addition gets the amplitude rectification coefficient k
nExport.Output frequency sweep status word S when frequency sweep
n, simultaneously in the reading system just at the number S of frequency sweep gyro
NumK wherein
N1, k
N2And k
nAll be 16 scale-of-two, S
Num=S
1+ S
2+ S
3
This step mainly comprises four parts:
1. total system frequency sweep State Control
For any gyro gauge outfit n, work as ω
d=ω
x=ω
MinThe time, B
xGet maximal value, promptly detected amplitude is got maximal value, is made as
When system start-up, 3 gyros all carry out frequency sweep locking resonance frequency, S at this moment
Num=3.
After the whole startups of 3 gyros are finished, when any gyro n is worked, instant amplitude with standard amplitude 20000 and this detection
It is poor to get
Then
Set frequency sweep criterion
To any gyro n, concrete judgement control is as follows:
(1) works as S
Num〉=2, gyro n does not carry out frequency sweep;
(2) work as S
Num≤ 1, and
Gyro n does not carry out frequency sweep, and has and work as
The time, adjust instant amplitude correction coefficient k
N2Adjust amplitude;
When gyro n carries out frequency sweep, S
n=1; Otherwise, S
n=0.
2. the generation of frequency control word
Circuit produces the frequency control word of change in the frequency sweep process, input NCO produces corresponding signal, according to driving the mode detected amplitude, finds the frequency control word W of maximum amplitude correspondence
Dn, export.
If ω
Min=2 π 2990rad/s, ω
Max=2 π 3010rad/s.When gyro starts, the frequency sweep frequency control word scope W of any gyro n correspondence
Min_n~W
Max_n, wherein
When gyro starts the back frequency sweep, W
Min_n=W
X_n-Δ W
n, W
Max_n=W
X_n+ Δ W
n, W wherein
X_nBe the frequency control word of the gyro resonance frequency correspondence before this frequency sweep of gyro n,
Be made as 128 in this example.Adopt the level Four frequency sweep during startup, for gyro 1, complete level Four frequency sweep locking resonance frequency workflow is as follows:
First order frequency sweep, frequency control word are from 12841952, and each interval time 1 μ s progressively increases 4096, progressively increases 21 times, up to 12927968.Each frequency variation all can be with a maximum amplitude storage, after this frequency sweep finishes, find maximal value and its pairing frequency control word, as frequency control word is 12884960 (respective frequencies 3000.1353Hz), determines that then second level frequency sweep frequency control word scope is 12880864 (12884960-4096)~12889056 (12884860+4096).
Second level frequency sweep, the original frequency control word is 12880864, each interval time 1 μ s frequency control word adds 256, add 32 times, find the pairing frequency control word of maximum amplitude, as 12880370, determine third level swept frequency range 12880114 (12880370-256)~12880626 (1284370+256);
Third level frequency sweep, the original frequency control word is 12880114, each interval time 1 μ s frequency control word adds 16, add 32 times, find the pairing frequency control word of maximum amplitude, as 12880365, true word fourth stage swept frequency range 12880349 (12880365-16)~12880381 (12880365+16);
Fourth stage frequency sweep, original frequency control word are 12880349, and each interval time 1 μ s frequency control word adds 1, adds 32 times, finds the pairing frequency control word W of maximum amplitude
1=12880363,12880363 input NCO are produced sine wave, the resonance frequency of gyro gauge outfit 1 is 2998.9432Hz at this moment.
Equally, the resonance frequency of caging 2,3 is 2996.6482Hz, 3001.9348Hz, respective frequencies control word W
2=12870506 and W
3=12893212.Then the resonance angular frequency of three gyros is ω
X1=2 π 2998.9432rad/s, ω
X2=2 π 2996.6482rad/s, ω
X3=2 π 3001.9348rad/s.
To any gyro n, after system works because of
During frequency sweep, swept frequency range is W
Min_n=W
X_n-128 to W
Max_n=W
X_n+ 128, W wherein
X_nBe the driving frequency control word before the frequency sweep.Then, carry out the secondary frequency sweep up to the locking resonance frequency from top third level frequency sweep.
3. amplitude-frequency correction coefficient k
N1Generation
k
N1Be accompanied by the variation of frequency sweep process medium frequency control word and change.
When resonance, i.e. ω
d=ω
x, detected amplitude:
Wherein, G
nBe constant, W
DnFrequency control word during for resonance.Work as ω
Dn=ω x
MinThe time,
Get maximal value
Be decided to be the standard amplitude, be made as 20000, at this moment respective frequencies control word W
Min_n=12841952.
Getting frequency control word by formula 2 is W
DnThe time the amplitude-frequency correction coefficient be:
To gyro 1, frequency control word is 12880363 o'clock, k
11=390; To gyro 2, frequency control word is 12870506 o'clock, k
21=290; To gyro 3, frequency control word is 12893212 o'clock, k
31=520.
4. instant correction coefficient k
N2Generation
When gyro frequency sweep n, with k
N2Zero clearing.When gyro n does not have frequency sweep, whenever detect and once drive amplitude
All with the standard amplitude
Compare: when
k
N2On the basis of original value, add 1; When
k
N2On the basis of original value, subtract 1.
When just frequency sweep finished, driving frequency equaled resonance frequency, then k
12=k
22=k
32=0.So k
1=390, k
2=290, k
3=520.
Step 7: the frequency control word W that previous step is obtained
D1, W
D2, W
D3Input NCO produces drive signal
The signal amplitude of setting NCO is 20000, then has:
Step 8: with the signal of previous step generation
K with the generation of the 6th step
nSend into the amplitude rectification module successively, output signal
When just frequency sweep finished, driving frequency equaled resonance frequency, then has:
Step 9: the rearmounted processing.Will
Through D/A converter, low-pass filter, amplifier are converted into simulating signal V
Dn, be added on the gauge outfit gyro n.If 2
14Be converted into+1V voltage, then:
A kind of more top header detection method comprises the steps:
Step 1: the responsive mode capacitor C of detection gyro gauge outfit n '
nBy charge amplifier or trans-impedance amplifier, adopt differential mode to carry out the C/V conversion, with C '
nVariation delta C '
n, be converted into voltage signal V
Bn, can be expressed as:
C '
FnBe feedback capacity, Δ C '
nBe capacitance change, V
iBe carrier wave.
If be through the signal after amplifying:
ω
iBe carrier frequency,
Be drive signal phase place, ω
DnBe driving signal frequency, V
0Be signal amplitude, K
nBe the detection angular velocity signal of gyro n (ω), establish the motion of angle of stability speed, and K
n(ω)=0.1+ δ
n, δ
nBe stochastic error.If ω
i=2 π 10
5Rad/s, V
0=5V.
Step 2: the voltage signal V that previous step is obtained
Bn,, change into digital signal by the A/D conversion
Step 3: use carrier signal V
iThe digital signal that previous step is obtained
Carry out demodulation, promptly
With
Pursue sampled point and multiply each other, get signal
Then:
For being carried in the carrier phase on the gyro n, be consistent in order to make three gyros, make carrier phase difference
Step 4: the signal that previous step is obtained
Adopt the logical or low-pass filter elimination radio-frequency component of band, then obtain signal
Step 5: use the drive signal that NCO directly produces in the gyro driving method step 7
The signal that previous step is obtained
Carry out demodulation,
In order to guarantee three gyro output signal unanimities, make phase differential
Then have:
Step 6: the signal that previous step is obtained
Adopt low-pass filtering elimination radio-frequency component, obtain angular velocity signal
If the gain of low-pass filter is 1/20000, then:
Step 7: angular velocity control output.
When not having the gyro frequency sweep,
As and when gyro 1 frequency sweep is only arranged,
As and when only having gyro 1 not have frequency sweep, then
Claims (2)
1. a more top header digitizing driving method is characterized in that comprising the steps:
Step 1: on gyro gauge outfit n, load initial driving signal V
DnWith carrier signal V
i, the mass after the signal loading in the gyro gauge outfit can vibrate, and the amplitude of vibration is reflected as capacitor C between two pole plates
n
Wherein, drive signal V
DnFrequency be ω
DnThe inner NCO of digit chip (numerically-controlled oscillator) produces the fixed frequency sine wave signal
, handle the sinusoidal signal V that obtains simulating through rearmounted then
iThe rearmounted processing comprises D/A conversion (digital signal is to analog signal conversion), low-pass filtering, amplification process successively, and this paper rearmounted processing procedure cited below is also identical; And the digital signal of the simulating signal X correspondence of mentioning herein all is expressed as
Step 2: detect gyro gauge outfit n and drive the mode capacitor C
nBy charge amplifier or trans-impedance amplifier, carry out C/V conversion (electric capacity is to the conversion of voltage signal), will drive the plates capacitance C of mode
nVariation delta C
n, be converted into voltage signal V
An
Step 3: the voltage signal V of the gyro n that previous step is obtained
An,, change into digital signal by A/D conversion (simulating signal is to the digital signal conversion)
Send into digital signal processing chip;
Step 4: the digital signal that previous step is obtained
Detect through amplitude, obtain signal amplitude
Step 5: data storage; For gyro n, when being in the frequency sweep process, every variation frequency once, with detected signal amplitude
Store; When gyrocontrol was worked, amplitude of every detection was all incited somebody to action
Put into storer, storage detects nearest M the drive signal amplitude of coming
M 〉=2 wherein;
Step 6: when gyro starts, frequency sweep caging n resonance frequency, the frequency control word W that it is corresponding
DnInput NCO produces driving frequency; Every frequency control word that changes then produces the amplitude-frequency correction coefficient k corresponding with frequency simultaneously
N1When gyro is worked,, export instant correction coefficient k according to the amplitude information of monitoring
N2With k
N1And k
N2Addition gets the amplitude rectification coefficient k
nExport; Output frequency sweep status word S when frequency sweep
n, S wherein
nOn behalf of gyro n, value 0 or 1,0 do not have frequency sweep, and 1 represents gyro n just in frequency sweep; Simultaneously in the reading system just at the number S of frequency sweep gyro
NumK wherein
N1, k
N2And k
nBe B position scale-of-two, B 〉=4,
Set F
0Be the amplitude of driving force, ω
dFor driving angular frequency, m
xBe the equivalent mass of driving mode,
Be the resonance angular frequency of driving mode,
For driving the damping ratio of mode, then drive the amplitude B of mode stable oscillation
xFor:
The frequency plot control word figure place of setting NCO is N, and frequency control word is W, and input clock frequency is F
Clk, output signal frequency F then
OutFor:
This step mainly comprises four parts:
First: total system frequency sweep State Control
If experiment records the minimum and the maximal value of the resonance angular frequency of gyro and is followed successively by ω
Min, ω
MaxFor any gyro gauge outfit n, get by formula 1, work as ω
d=ω
x=ω
MinThe time, B
xGet maximal value, promptly detected amplitude is got maximal value, is designated as
When system start-up, gyro n carries out the resonance frequency of frequency sweep locking gauge outfit, S at this moment arbitrarily
Num=N;
After any gyro n frequency sweep is finished, immediately with the standard amplitude
Amplitude with this detection
It is poor to get
Promptly
Set
Be frequency sweep criterion, and
Concrete judgement control is as follows:
(1) works as S
Num〉=h, gyro n do not carry out frequency sweep, and wherein h is that maximum is allowed frequency sweep gyro number, 1≤h N-1;
(2) work as S
Num≤ h-1, and
Gyro n does not carry out frequency sweep, and has and work as
The time, adjust instant amplitude correction coefficient k
N2Adjust amplitude;
Second portion: the generation of frequency control word
Circuit produces the frequency control word of change in the frequency sweep process, input NCO produces corresponding signal, according to driving the mode detected amplitude, finds the frequency control word W of maximum amplitude correspondence
Dn, export;
When gyro starts, get the frequency sweep frequency control word scope W of gyro n correspondence by formula 2
Min_n~W
Max_n, wherein
When gyro starts the back frequency sweep, W
Min_n=W
X_n-Δ W
n, W
Max_n=W
X_n+ Δ W
n, W wherein
X_nBe the frequency control word of the gyro resonance frequency correspondence before this frequency sweep of gyro n,
A complete J level frequency sweep locking resonance frequency workflow is as follows:
During first order frequency sweep, frequency control word is from W
Min_nBeginning is every the time Δ T bigger range delta W that adds up
N1(1≤Δ W
N1≤ 0.5 (W
Max_n-W
Min_n)), input NCO produces drive signal input gyro gauge outfit, waits stable back to gather amplitude, sends into storer, through K
N1After inferior, then gather K
N1+ 1 drives amplitude
By controller relatively
Find out maximal value and its corresponding frequency control word W
N1K wherein
N1>(W
Max_n-W
Min_n)/Δ W
N1, Δ T>2 π/ω
X_min, this process M=K
N1+ 1;
Carry out second level frequency sweep then, swept frequency range is from W
N1-Δ W
N1To W
N1+ Δ W
N1, every the time Δ T Δ W that adds up
N2, 1≤Δ W wherein
N2<0.5 Δ W
N1, input NCO produces drive signal input gyro gauge outfit, waits stable back to gather amplitude, through K
N2, inferior after, gather K
N2+ 1 drives amplitude
Find out amplitude maximal value and its corresponding frequency control word W
N2K wherein
N2>2 Δ W
N1/ Δ W
N2, this process M=K
N2+ 1;
Carry out third level frequency sweep by same process then, fourth stage frequency sweep ... J level frequency sweep, then the frequency control word W of detected maximum amplitude correspondence in the J level frequency sweep
NJThe frequency control word W of resonance frequency correspondence then
Dn=W
NJOutput;
Third part: amplitude-frequency correction coefficient k
N1Generation
k
N1Be accompanied by the variation of frequency sweep process medium frequency control word and change;
Push away by formula 1 and 2, when the resonance, i.e. ω
d=ω
x, detected amplitude:
Wherein, G
nBe constant, W
DnFrequency control word during for resonance; Work as ω
Dn=ω
MinThe time,
Get maximal value
Be decided to be the standard amplitude, at this moment the respective frequencies control word
By formula 3 the amplitude-frequency correction coefficient of frequency control word when being W is:
The 4th part: instant correction coefficient k
N2Generation
When gyro frequency sweep n, with k
N2Zero clearing; When gyro n does not have frequency sweep, whenever detect and once drive amplitude
All with the standard amplitude
Compare: when
k
N2On the basis of original value, add Δ k
n, Δ k wherein
n〉=1; When
k
N2On the basis of original value, subtract Δ k
n
Step 7: the frequency control word W of the resonance frequency correspondence that step 6 is obtained
nInput NCO, control NCO produces drive signal
Step 8: with the drive signal of step 7 generation
With the correction coefficient k that produces in the step 6
n, send into the amplitude rectification module, the drive signal behind the output calibration
Then:
2. a more top header detection method comprises the steps:
Step 1: the responsive mode capacitor C of detection gyro gauge outfit n '
nBy charge amplifier or trans-impedance amplifier, carry out C/V conversion, with responsive mode capacitor C '
nVariation delta C '
n, be converted into voltage signal V
Bn
Step 2: the voltage signal V that previous step is obtained
Bn,, change into digital signal by the A/D conversion
Output;
Step 3: use carrier signal V
iThe digital signal that previous step is obtained
Carry out demodulation, get signal
Step 4: the signal that previous step is obtained
Adopt the logical or low-pass filter elimination radio-frequency component of band, then obtain signal
Step 5: use the drive signal that NCO directly produces in the more top header digitizing driving method step 7
The signal that previous step is obtained
Carry out demodulation, get signal
Step 6: the signal that previous step is obtained
Adopt low-pass filtering elimination radio-frequency component, obtain angular velocity signal
Step 7: the angular velocity signal that previous step is obtained
Drive the frequency sweep status word S that step 6 obtains in the implementation method with gyro
n, carry out computing, obtain final angular velocity signal
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN 201010210303 CN101900554B (en) | 2010-06-24 | 2010-06-24 | Method for digitally driving and detecting multi-gauge head gyroscope |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN 201010210303 CN101900554B (en) | 2010-06-24 | 2010-06-24 | Method for digitally driving and detecting multi-gauge head gyroscope |
Publications (2)
Publication Number | Publication Date |
---|---|
CN101900554A true CN101900554A (en) | 2010-12-01 |
CN101900554B CN101900554B (en) | 2013-08-14 |
Family
ID=43226305
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN 201010210303 Expired - Fee Related CN101900554B (en) | 2010-06-24 | 2010-06-24 | Method for digitally driving and detecting multi-gauge head gyroscope |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN101900554B (en) |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102109345A (en) * | 2010-12-13 | 2011-06-29 | 谢元平 | Digital signal processing method and device for micro-mechanical gyroscope |
CN102299712A (en) * | 2011-03-23 | 2011-12-28 | 中国科学院上海应用物理研究所 | Self-adaptive method for acquiring frequency control word of digital frequency mixing orthogonal local oscillator signal |
CN102519444A (en) * | 2011-11-25 | 2012-06-27 | 上海交通大学 | Automatic gain control (AGG) self-excited oscillation driving circuit of micro-solid modal gyroscope |
CN102519617A (en) * | 2012-01-09 | 2012-06-27 | 北京理工大学 | Digitalized detection method for temperature information of micromechanical quartz gyroscope sensitive device |
CN102749090A (en) * | 2012-07-25 | 2012-10-24 | 浙江大学 | Method for temperature drift of fiber optic gyroscope |
CN103674026A (en) * | 2013-12-06 | 2014-03-26 | 上海新跃仪表厂 | Miniaturized liquid-floated inertial attitude sensor suitable for microsatellite |
CN104697511A (en) * | 2013-12-05 | 2015-06-10 | 精工爱普生株式会社 | Detection device, sensor, electronic apparatus and moving object |
WO2015197030A1 (en) * | 2014-06-26 | 2015-12-30 | 无锡华润上华半导体有限公司 | Method and system for correcting driving amplitude of gyro sensor |
CN106092145A (en) * | 2016-08-30 | 2016-11-09 | 南京理工大学 | A kind of silicon micro-gyroscope measure and control device separated based on gauge outfit plate |
CN106840145A (en) * | 2016-12-19 | 2017-06-13 | 北京时代民芯科技有限公司 | A kind of micromechanics speed integrates the control system of ring gyro |
CN111505398A (en) * | 2020-04-23 | 2020-08-07 | 华中科技大学 | Isolated conductor charge estimation method and system based on motion observation |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20040088127A1 (en) * | 2002-06-25 | 2004-05-06 | The Regents Of The University Of California | Integrated low power digital gyro control electronics |
WO2004046650A1 (en) * | 2002-11-20 | 2004-06-03 | Bae Systems Plc | Method and apparatus for measuring scalefactor variation in a vibrating structure gyroscope |
CN101021418A (en) * | 2006-12-30 | 2007-08-22 | 西安中星测控有限公司 | Angular speed rate and angle gyroscope |
CN101382425A (en) * | 2008-09-26 | 2009-03-11 | 北京航空航天大学 | Micromechanical gyroscope self-exciting driving and demodulating apparatus |
-
2010
- 2010-06-24 CN CN 201010210303 patent/CN101900554B/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20040088127A1 (en) * | 2002-06-25 | 2004-05-06 | The Regents Of The University Of California | Integrated low power digital gyro control electronics |
WO2004046650A1 (en) * | 2002-11-20 | 2004-06-03 | Bae Systems Plc | Method and apparatus for measuring scalefactor variation in a vibrating structure gyroscope |
CN101021418A (en) * | 2006-12-30 | 2007-08-22 | 西安中星测控有限公司 | Angular speed rate and angle gyroscope |
CN101382425A (en) * | 2008-09-26 | 2009-03-11 | 北京航空航天大学 | Micromechanical gyroscope self-exciting driving and demodulating apparatus |
Non-Patent Citations (1)
Title |
---|
《传感技术学报》 20080331 蒋庆华 等 一种改进的振动式微机械陀螺驱动电路 536-538 1 第21卷, 第3期 2 * |
Cited By (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102109345A (en) * | 2010-12-13 | 2011-06-29 | 谢元平 | Digital signal processing method and device for micro-mechanical gyroscope |
CN102109345B (en) * | 2010-12-13 | 2012-12-12 | 谢元平 | Digital signal processing method and device for micro-mechanical gyroscope |
CN102299712A (en) * | 2011-03-23 | 2011-12-28 | 中国科学院上海应用物理研究所 | Self-adaptive method for acquiring frequency control word of digital frequency mixing orthogonal local oscillator signal |
CN102519444A (en) * | 2011-11-25 | 2012-06-27 | 上海交通大学 | Automatic gain control (AGG) self-excited oscillation driving circuit of micro-solid modal gyroscope |
CN102519444B (en) * | 2011-11-25 | 2015-08-26 | 上海交通大学 | The AGC self-sustained oscillation driving circuit of micro-solid mode gyroscope |
CN102519617A (en) * | 2012-01-09 | 2012-06-27 | 北京理工大学 | Digitalized detection method for temperature information of micromechanical quartz gyroscope sensitive device |
CN102749090A (en) * | 2012-07-25 | 2012-10-24 | 浙江大学 | Method for temperature drift of fiber optic gyroscope |
CN102749090B (en) * | 2012-07-25 | 2015-01-14 | 浙江大学 | Method for temperature drift of fiber optic gyroscope |
CN104697511A (en) * | 2013-12-05 | 2015-06-10 | 精工爱普生株式会社 | Detection device, sensor, electronic apparatus and moving object |
CN103674026A (en) * | 2013-12-06 | 2014-03-26 | 上海新跃仪表厂 | Miniaturized liquid-floated inertial attitude sensor suitable for microsatellite |
WO2015197030A1 (en) * | 2014-06-26 | 2015-12-30 | 无锡华润上华半导体有限公司 | Method and system for correcting driving amplitude of gyro sensor |
US10466065B2 (en) | 2014-06-26 | 2019-11-05 | Csmc Technologies Fab2 Co., Ltd. | Method and system for correcting driving amplitude of gyro sensor |
US10782148B2 (en) | 2014-06-26 | 2020-09-22 | Csmc Technologies Fab2 Co., Ltd. | Method and system for correcting driving amplitude of gyro sensor |
CN106092145A (en) * | 2016-08-30 | 2016-11-09 | 南京理工大学 | A kind of silicon micro-gyroscope measure and control device separated based on gauge outfit plate |
CN106092145B (en) * | 2016-08-30 | 2019-01-18 | 南京理工大学 | A kind of silicon micro-gyroscope measure and control device based on the separation of gauge outfit plate |
CN106840145A (en) * | 2016-12-19 | 2017-06-13 | 北京时代民芯科技有限公司 | A kind of micromechanics speed integrates the control system of ring gyro |
CN106840145B (en) * | 2016-12-19 | 2020-03-27 | 北京时代民芯科技有限公司 | Control system of micro-mechanical rate integrating ring gyroscope |
CN111505398A (en) * | 2020-04-23 | 2020-08-07 | 华中科技大学 | Isolated conductor charge estimation method and system based on motion observation |
Also Published As
Publication number | Publication date |
---|---|
CN101900554B (en) | 2013-08-14 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN101900554B (en) | Method for digitally driving and detecting multi-gauge head gyroscope | |
CN110108266B (en) | Gyro real-time automatic closed-loop mode matching method based on mechanical VCO phase-locked loop | |
CN108519498B (en) | Self-adaptive closed-loop measurement system of resonant accelerometer | |
CN100489454C (en) | Method and system for exciting main control vibration of oscillator | |
CN110426025B (en) | Real-time automatic mode matching method for micromechanical gyroscope | |
CN102538774B (en) | Closed-loop phase lock fixed amplitude drive circuit of micro-solid modal gyroscope | |
CN102607546B (en) | Orthogonal error processing method for micromechanical gyroscope and device | |
CN106370172B (en) | Micro gyroscope driving and detecting device and method based on digital embedded system | |
CN109029409B (en) | Parameter amplification method and device in micromechanical gyroscope with tunable gate structure | |
CN105203132A (en) | Output frequency detection method of resonant mode vibrating gyro | |
CN103162680A (en) | Silicon microgyroscope performance improving method and device based on force balance closed-loop control | |
CN112747730B (en) | Self-excitation drive-based nonlinear control system and method for micromechanical gyroscope | |
CN104197923A (en) | Micro-capacitance gyroscope signal detecting method based on carrier wave detection | |
CN104567849A (en) | Silicon micromechanical line vibrating gyroscope and bandwidth expanding method thereof | |
US20130025368A1 (en) | Microelectromechanical gyroscope with improved reading stage and method | |
CN115824181A (en) | Resonance gyro time-sharing multiplexing capacitance detection method, control system and resonance gyro | |
CN206378139U (en) | A kind of micro-mechanical gyroscope of quadrature bias from elimination | |
CN102692221B (en) | Micro-solid mode gyroscope close-loop driven and coriolis force testing circuit | |
CN106017450B (en) | Digital signal processing system of piezoelectric hemispherical resonance micro gyroscope | |
CN109029498B (en) | Digital measurement and control system for modal reciprocity of vibrating ring silicon micro gyroscope | |
CN113607150A (en) | Quartz gyro error suppression method of time division driving and orthogonal force feedback closed loop | |
CN106441359A (en) | High precision on-site mode matching method of micromechanical gyroscope | |
CN210198392U (en) | Novel MEMS resonant gyroscope measurement and control device | |
CN111380561B (en) | Micro-electromechanical gyro scale factor compensation method based on multi-parameter fusion | |
CN108827346B (en) | Resonant sensor temperature compensation method based on continuous ring-down |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
C14 | Grant of patent or utility model | ||
GR01 | Patent grant | ||
CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130814 Termination date: 20150624 |
|
EXPY | Termination of patent right or utility model |