CN106596013B - A kind of measurement method of helicopter vibration active control system time lag - Google Patents
A kind of measurement method of helicopter vibration active control system time lag Download PDFInfo
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- CN106596013B CN106596013B CN201611068513.1A CN201611068513A CN106596013B CN 106596013 B CN106596013 B CN 106596013B CN 201611068513 A CN201611068513 A CN 201611068513A CN 106596013 B CN106596013 B CN 106596013B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
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Abstract
The invention discloses a kind of measurement methods of helicopter vibration active control system time lag.The measurement method of the helicopter vibration active control system time lag includes the following steps: step 1, installs vibration acceleration sensor on vibration active control system execution unit；Step 2: sending preset signals for the vibration active control system, and acquire the first signal value received by the vibration acceleration sensor；Step 3: preset signals being substituted into correlation formula, to obtain the first non-stationary value Ia, the first signal value is brought into correlation formula, to obtain the second non-stationary value If；Step 4: the first non-stationary value and the second non-stationary value being compared, to obtain helicopter vibration active control system Slack time.This application provides a kind of measurement methods of helicopter vibration active control system time lag, and so as to measure helicopter vibration active control system time lag, the development for helicopter vibration active control system provides basis.
Description
Technical field
The present invention relates to helicopter vibration active control technology fields, more particularly to a kind of helicopter vibration active control
The measurement method of system time lags.
Background technique
Time response test is control system own hardware and software in helicopter vibration active control system ground experiment
And the transfer function characteristics of controlled device, for vibration active control system, the time response that need to be considered mainly includes control
The time response and actuator of device hardware and software to signal transmission path between error pick-up time response, also
It is the amplitude and phase characteristic in each frequency content, wherein account for leading role is phase characteristic, that is, system input
It is helicopter vibration active control system key parameter to the time delay of output.
In the prior art, there is no the method for helicopter vibration active control system time lag.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
The purpose of the present invention is to provide a kind of measurement methods of helicopter vibration active control system time lag overcoming or
At least mitigate at least one drawbacks described above of the prior art.
To achieve the above object, the present invention provides a kind of measurement method of helicopter vibration active control system time lag,
The measurement method of the helicopter vibration active control system time lag includes the following steps:
Step 1, vibration acceleration sensor is installed on vibration active control system execution unit；
Step 2: sending preset signals for the vibration active control system, and acquire the vibration acceleration sensor institute
The first signal value received；
Step 3: preset signals being substituted into correlation formula, to obtain the first non-stationary value Ia, the first signal value is brought into
Correlation formula, to obtain the second non-stationary value If；
Step 4: the first non-stationary value and the second non-stationary value being compared, actively controlled to obtain helicopter vibration
The system time lags time processed.
Preferably, the correlation formula are as follows:
Wherein,
F ' transmission sinusoidal signal；
A ' acceleration value；
I is the non-stationary value of signal；
N-signal Z always counts；
| | | | Euclidean distance；
R reference distance；
H unit saves function；
Z clock signal, here to be respectively f ', a '；
IaThe non-stationary value of signal a '；
IfThe non-stationary value of signal f '；
Calculate signal plateau
F=f '-If；
A=a '-Ia；
In formula
A signal a ' plateau；
F signal f ' plateau.
Preferably, the step 2 specifically: step 21: vibration acceleration sensor is connected to data acquisition transmission and is set
It is standby upper, the signal sending end of data acquisition sending device is connected to vibration active control system signal receiving end；Step 22: by
PC machine controls data acquisition sending device and sends preset signals to vibration active control system；Step 23: same with the step 22
Step, data acquisition sending device acquire the first signal value received by vibration acceleration sensor in the step 22.
Preferably, the preset signals are sinusoidal signal f '；First signal value is adding for vibration acceleration sensor
Velocity amplitude a '.
This application provides a kind of measurement methods of helicopter vibration active control system time lag, straight so as to measure
Machine vibration active control system time lag is risen, the development for helicopter vibration active control system provides basis.
Detailed description of the invention
Fig. 1 is that the process of the measurement method of helicopter vibration active control system time lag according to an embodiment of the invention is shown
It is intended to.
Fig. 2 is the waveform of the preset signals in the measurement method of helicopter vibration active control system time lag shown in FIG. 1
Figure.
Fig. 3 is the wave of the first signal value in the measurement method of helicopter vibration active control system time lag shown in FIG. 1
Shape figure.
Fig. 4 be the first non-stationary value in the measurement method of helicopter vibration active control system time lag shown in FIG. 1 with
And second non-stationary value waveform diagram.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
Fig. 1 is that the process of the measurement method of helicopter vibration active control system time lag according to an embodiment of the invention is shown
It is intended to.Fig. 2 is the waveform diagram of the preset signals in the measurement method of helicopter vibration active control system time lag shown in FIG. 1.
Fig. 3 is the waveform diagram of the first signal value in the measurement method of helicopter vibration active control system time lag shown in FIG. 1.Fig. 4
It is the first non-stationary value and the second non-stationary in the measurement method of helicopter vibration active control system time lag shown in FIG. 1
The waveform diagram of value.
The measurement method of helicopter vibration active control system time lag as shown in Figure 1 includes the following steps:
Step 1, vibration acceleration sensor is installed on vibration active control system execution unit；
Step 2: sending preset signals for vibration active control system, and acquire received by vibration acceleration sensor
First signal value；
Step 3: preset signals being substituted into correlation formula, to obtain the first non-stationary value Ia, the first signal value is brought into
Correlation formula, to obtain the second non-stationary value If；
Step 4: the first non-stationary value and the second non-stationary value being compared, actively controlled to obtain helicopter vibration
The system time lags time processed.
This application provides a kind of measurement methods of helicopter vibration active control system time lag, straight so as to measure
Machine vibration active control system time lag is risen, the development for helicopter vibration active control system provides basis.
In the present embodiment, correlation formula are as follows:
Wherein,
F ' transmission sinusoidal signal；
A ' acceleration value；
I is the non-stationary value of signal；
N-signal Z always counts；
| | | | Euclidean distance；
R reference distance；
H unit saves function；
Z clock signal, here to be respectively f ', a '；
IaThe non-stationary value of signal a '；
IfThe non-stationary value of signal f '；
Calculate signal plateau
F=f '-If；
A=a '-Ia；
In formula
A signal a ' plateau；
F signal f ' plateau.
In the present embodiment, step 2 specifically:
Step 21: vibration acceleration sensor being connected in data acquisition sending device, data are acquired into sending device
Signal sending end be connected to vibration active control system signal receiving end；
Step 22: preset signals are sent to vibration active control system by PC machine control data acquisition sending device；
Step 23: synchronous with step 22, data acquire sending device and acquire vibration acceleration sensor in the step 22
The first received signal value.
In the present embodiment, the preset signals are sinusoidal signal f '；First signal value is vibration acceleration sensing
The acceleration value a ' of device.
The application is further elaborated by way of example below.It is understood that the citing is not constituted to this
Any restrictions of application.
It being formed according to certain type machine vibration active control system, the execution unit of vibration active control system is actuator,
The vertical upper installation vibration acceleration sensor of actuator.
Vibration acceleration sensor is connected to data acquisition sending device, the signal of data acquisition sending device is sent
End is connected to vibration active control system signal receiving end.
Sinusoidal signal f '=2sin (2 π 20) is sent to active vibration control system by PC machine control data acquisition sending device
System.Sinusoidal signal is as shown in Figure 2.
Synchronous, data acquire the first signal received by vibration acceleration sensor in sending device acquisition step 22
Value, first signal value are as shown in Figure 3.
It is calculated by formula, obtains the first non-stationary value I of signalaAnd the second non-stationary value If, in order to more convenient,
First non-stationary value and the second non-stationary value can be showed using diagramatic way as shown in Figure 4, finally, comparing the
One non-stationary value IaAnd the second non-stationary value IfIt is 30.22ms that vibration active control system time lag, which can be obtained,.
Finally it is noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, those skilled in the art should understand that: it is still
It is possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is equally replaced
It changes；And these are modified or replaceed, the essence for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
Mind and range.
Claims (3)
1. a kind of measurement method of helicopter vibration active control system time lag, which is characterized in that the helicopter vibration is actively
The measurement method of control system time lag includes the following steps:
Step 1, vibration acceleration sensor is installed on vibration active control system execution unit；
Step 2: sending preset signals for the vibration active control system, and acquire the vibration acceleration sensor and received
The first signal value arrived；
Step 3: preset signals being substituted into correlation formula, to obtain the first non-stationary value Ia, bring the first signal value into related public affairs
Formula, to obtain the second non-stationary value If；Wherein, the correlation formula are as follows:Wherein,
F ' transmission sinusoidal signal；
A ' acceleration value；
I is the non-stationary value of signal；
N-signal Z always counts；
| | | | Euclidean distance；
R reference distance；
H unit saves function；
Z clock signal, here to be respectively f ', a '；
IaThe non-stationary value of signal a '；
IfThe non-stationary value of signal f '；
Calculate signal plateau
F=f '-If；
A=a '-Ia；
In formula
A signal a ' plateau；
F signal f ' plateau；
Step 4: the first non-stationary value and the second non-stationary value being compared, to obtain helicopter vibration active control system
System Slack time.
2. the measurement method of helicopter vibration active control system time lag as described in claim 1, which is characterized in that the step
Rapid 2 specifically:
Step 21: vibration acceleration sensor being connected in data acquisition sending device, by the letter of data acquisition sending device
Number transmitting terminal is connected to vibration active control system signal receiving end；
Step 22: preset signals are sent to vibration active control system by PC machine control data acquisition sending device；
Step 23: synchronous with the step 22, data acquire sending device and acquire vibration acceleration sensor in the step 22
The first received signal value.
3. the measurement method of helicopter vibration active control system time lag as claimed in claim 2, which is characterized in that described pre-
If signal is sinusoidal signal f '；First signal value is the acceleration value a ' of vibration acceleration sensor.
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| CN201611068513.1A CN106596013B (en) | 2016-11-29 | 2016-11-29 | A kind of measurement method of helicopter vibration active control system time lag |
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| CN110928180B (en) * | 2019-12-04 | 2023-03-28 | 中国直升机设计研究所 | Hysteresis compensation method and device for actuator |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5381692A (en) * | 1992-12-09 | 1995-01-17 | United Technologies Corporation | Bearing assembly monitoring system |
| CN102736518A (en) * | 2012-07-24 | 2012-10-17 | 北京航空航天大学 | Composite anti-interference controller comprising measurement and input time delay for flexible spacecraft |
| CN103852101A (en) * | 2014-02-20 | 2014-06-11 | 中国商用飞机有限责任公司 | Measuring device for lag time of airplane airspeed system |
-
2016
- 2016-11-29 CN CN201611068513.1A patent/CN106596013B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5381692A (en) * | 1992-12-09 | 1995-01-17 | United Technologies Corporation | Bearing assembly monitoring system |
| CN102736518A (en) * | 2012-07-24 | 2012-10-17 | 北京航空航天大学 | Composite anti-interference controller comprising measurement and input time delay for flexible spacecraft |
| CN103852101A (en) * | 2014-02-20 | 2014-06-11 | 中国商用飞机有限责任公司 | Measuring device for lag time of airplane airspeed system |
Non-Patent Citations (1)
| Title |
|---|
| 基于速度-加速度时滞反馈的振动主动控制;安方 等;《振动、测试与诊断》;20120630;第32卷(第3期);全文 |
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