CN104978450B - A kind of helicopter vibration active control position preferred method - Google Patents
A kind of helicopter vibration active control position preferred method Download PDFInfo
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- CN104978450B CN104978450B CN201510205423.1A CN201510205423A CN104978450B CN 104978450 B CN104978450 B CN 104978450B CN 201510205423 A CN201510205423 A CN 201510205423A CN 104978450 B CN104978450 B CN 104978450B
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- bump leveller
- transmission function
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The present invention relates to a kind of helicopter vibration active control position preferred method, pass through foundation, correct helicopter finite element model, it establishes transmission function and calculates model, actuator/passive bump leveller to evaluation point transmission function is calculated later, optimization actuator/passive bump leveller installation site, actuator installation number, and provide corresponding damping efficiency, optimal actuator/passive bump leveller installation site and actuator installation number are finally filtered out using the method that comprehensive damping efficiency combines, this method uses simple, it is easy to operate, the installation site of optimization is accurate, optimization process time-consuming is short, and independently of helicopter body structure, suitable for different types without making any modification.
Description
Technical field
The invention belongs to structural vibration reduction design fields, preferred more particularly to a kind of active/passive vibration absorber optimal location.
Background technique
In order to carry out helicopter vibration active control system design, the choosing in position, quantity, the direction that is used as power of actuator etc.
Selecting is key link.Since Helicopter Dynamic Model node size is big, the artificial sample point chosen that calculates is very limited, may
It is relatively low to lead to calculate damping efficiency, actuator installation site there may be deviation etc., therefore improve the preferred reliability in position and
Accuracy improves computational efficiency, and reduces the calculation amount repeatedly of active vibration control position preferred process, to entire vibration master
Autocontrol system design has very important significance.
In the prior art, using multiple-objection optimization and PCL development technique, for Structural Vibration Control for Helicopter control actuator/
Passive bump leveller installation site is preferred, is applied to best vibration damping effect and designs, finds in actual use: actuator/quilt
Dynamic bump leveller installation site implementation method engineer application is low, and method complexity is high, and the data volume of intermediate treatment is very big, obtains
Result it is substantially not implementable in engineering.
Summary of the invention
To solve the above-mentioned problems, the present invention provides a kind of helicopter vibration active control position preferred method, can have
Effect preferably goes out actuator/passive bump leveller installation site.Position preferred method is mainly calculated by aggregation of data, transmission function, is excellent
Change, database and analysis are formed with result treatment.
Helicopter vibration active control position preferred method of the invention, it is main by helicopter finite element model, it establishes and passes
Delivery function, it is characterised in that further include following steps:
Using transmission function and helicopter flight load as input, optimization actuator/passive bump leveller installation site is made
Dynamic device installation number, and provide corresponding damping efficiency；
According to different flight loads, state of flight, optimal actuation is filtered out using the method that comprehensive damping efficiency combines
Device/passive bump leveller installation site and actuator installation number.
Preferably, according to Modal Test data, by rigidity, quality and the quality point of correcting helicopter finite element model
Cloth matches the calculating mode of finite element model with Modal Test, extracts transmission function using amendment finite element model and calculates mould
Type matrix.
In any of the above-described scheme preferably, model matrix calculating various combination actuation is being calculated according to transmission function
The transmission function matrix of consequence of device/passive bump leveller installation site, actuator installation number.
In any of the above-described scheme preferably, flight load data are input in helicopter amendment finite element model,
Helicopter body response matrix is calculated, by helicopter body response matrix, transmission function matrix of consequence is input to excellent as data
Change in algorithm, using damping efficiency as Optimal Parameters, actuator/passive bump leveller installation site, actuator installation number are carried out
Evaluation optimization, evaluation optimize formula and are,
Wherein, giTo be responded at i-th of evaluation point,For initial i-th of evaluation point initial communication, η is damping efficiency, it
By asking, the minimum value of η obtains optimal actuator/passive bump leveller installation site, actuator installation number combines afterwards.
In any of the above-described scheme preferably, by obtained optimal actuator/passive bump leveller installation site, actuator
Installation number combination is input in formula as input,
compare(MAX(Fj))
In formula: κ is damping efficiency ratio, η1、η2...ηiFor damping efficiency, FiFor actuator power output, w1、w2...wiTo add
Weight coefficient respectively corresponds different flying speeds.
Key point of the invention:
1) finite element model improves the accuracy of transmission function calculating in conjunction with test data；
2) by files of constrained multi-objective optimization method apply helicopter vibration actively/by control position it is preferred；
3) weighting vibration damping efficiency calculation has been entered.
This practical approach is using simply, and easy to operate, the installation site of optimization is accurate, and optimization process time-consuming is short.This hair
It is bright independently of helicopter body structure, suitable for different types without making any modification.In large-scale optimization, manually
Workload increases less, and optimization can be rapidly completed.
Detailed description of the invention
Fig. 1 is the flow chart according to a preferred embodiment of helicopter vibration active control of the present invention position preferred method.
The Z of each point when Fig. 2 is calculating actuator/passive bump leveller to evaluation point transmission function of embodiment illustrated in fig. 1
To response distribution map.
Specific embodiment
Helicopter vibration active control according to the present invention position preferred method is done further in detail with reference to the accompanying drawing
It describes in detail bright.
As shown in Figure 1, first, establish helicopter finite element model, according to the mountable position of practical actuator and evaluation
Position primarily determines 18 actuator installation position candidates, helicopter finite element model is established, according to Modal Test data correction
Helicopter limited element calculation model establishes transmission function using revised helicopter finite element and calculates model；After amendment
Helicopter transmission function calculates model, calculates actuator/passive bump leveller to evaluation point transmission function；
Later, using transmission function and helicopter flight load as input, optimization actuator/passive bump leveller installation position
It sets, actuator installation number, and provides corresponding damping efficiency；
In this step, optimization actuator/passive bump leveller installation site, actuator installation number first, optimization side
Method and formula are as follows:
Propeller hub power is Fr, transmission function of the propeller hub at each evaluation point be expressed as T0, evaluation point initial communication is G0=T0Fr,
The transmission function for combining its corresponding actuator to each evaluation point to one group of given n actuator is T1、T2…
Tn, actuator power output is F1、F2…Fn, G is responded at evaluation point
Interpretational criteria
Wherein, giTo be responded at i-th of evaluation point,For initial i-th of evaluation point initial communication, η is damping efficiency.
Therefore, which is attributed to the minimum value for seeking η, is expressed as
minη(f),abs(fi)≤fastrict, i=1 ... n
Finally, being filtered out using the method that comprehensive damping efficiency combines optimal according to different flight loads, state of flight
Actuator/passive bump leveller installation site and actuator installation number.
In this step, optimal actuator/passive bump leveller installation is filtered out using the method that comprehensive damping efficiency combines
Position and actuator installation number, formula are as follows:
compare(MAX(Fj))
In formula: κ is damping efficiency ratio, η1、η2...ηiFor damping efficiency, FiFor actuator power output, w1、w2...wiTo add
Weight coefficient respectively corresponds different flying speeds, is specifically shown in Table 1.
1 this paper preferred result of table
It should be noted that helicopter vibration active control of the present invention position preferred method includes appointing in above-described embodiment
What one and any combination thereof, but the above-described embodiments are merely illustrative of preferred embodiments of the present invention, and
It is non-that the scope of the invention is defined, without departing from the spirit of the design of the present invention, this field ordinary engineering and technical personnel pair
The various changes and improvements that technical solution of the present invention is made should all fall into the protection scope that claims of the present invention determines
It is interior.
Claims (3)
1. a kind of helicopter vibration active control position preferred method establishes transmission function by helicopter finite element model,
It is characterized in that further including following steps:
Using transmission function and helicopter flight load as input, optimization actuator/passive bump leveller installation site, actuator
Installation number, and corresponding damping efficiency is provided, specifically: flight load data are input to helicopter amendment finite element model
In, helicopter body response matrix is calculated, by helicopter body response matrix, transmission function matrix of consequence is input to as data
In optimization algorithm, using damping efficiency as Optimal Parameters, to actuator/passive bump leveller installation site, actuator installation number into
Row evaluation optimization, evaluation optimize formula and are,
Wherein, giTo be responded at i-th of evaluation point,For initial i-th of evaluation point initial communication, η is damping efficiency, Zhi Houtong
It crosses and the minimum value of η is asked to obtain optimal actuator/passive bump leveller installation site, the combination of actuator installation number；
According to different flight loads, state of flight, optimal actuator/quilt is filtered out using the method that comprehensive damping efficiency combines
Dynamic bump leveller installation site and actuator installation number, specifically: by obtained optimal actuator/passive bump leveller installation position
It sets, the combination conduct input of actuator installation number, is input in formula,
In formula: κ is damping efficiency ratio, η1、η2...ηiFor damping efficiency, FiFor actuator power output, w1、w2...wiFor weighting system
Number, respectively corresponds different flying speeds.
2. helicopter vibration active control according to claim 1 position preferred method, it is characterised in that: according to test mould
State data, rigidity, quality and Mass Distribution by correcting helicopter finite element model make the calculating mode of finite element model
It is matched with Modal Test, extracts transmission function using amendment finite element model and calculate model matrix.
3. helicopter vibration active control according to claim 1 position preferred method, it is characterised in that: according to transmitting letter
Number computation model matrix calculates various combination actuator/passive bump leveller installation site, the transmission function of actuator installation number
Matrix of consequence.
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105843270A (en) * | 2016-03-31 | 2016-08-10 | 南京航空航天大学 | Helicopter multi-frequency vibration active control method |
| DE102017203959A1 (en) * | 2017-03-10 | 2018-09-13 | KSB SE & Co. KGaA | Method for operating a variable-speed circulating pump and circulating pump for process execution |
| CN108090262B (en) * | 2017-12-03 | 2021-09-21 | 中国直升机设计研究所 | Particle pair construction method based on SPH theory helicopter hydrofoil load calculation |
| CN108945405B (en) * | 2018-04-23 | 2021-08-06 | 南京航空航天大学 | Helicopter body vibration self-adaptive harmonic feedforward-sliding mode feedback hybrid control method |
| CN108984917A (en) * | 2018-07-20 | 2018-12-11 | 北京航空航天大学 | Large aircraft flies control actuating system intelligent design and evaluation method |
| CN110879528A (en) * | 2019-08-23 | 2020-03-13 | 中国船舶重工集团公司第七一九研究所 | Method for simultaneously optimizing number and position of sensors and actuators of active vibration reduction system |
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| US20120292434A1 (en) * | 2011-04-29 | 2012-11-22 | Sikorsky Aircraft Corporation | Six Degrees Of Freedom Vibration Suppression |
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| US6467723B1 (en) * | 2000-10-10 | 2002-10-22 | Lord Corporation | Active vibration control system for helicopter with improved actustor placement |
| CN102369140A (en) * | 2009-02-27 | 2012-03-07 | 贝尔直升机泰克斯特龙公司 | System and method for vibration control in a rotorcraft using an adaptive reference model algorithm |
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