CN106599403A - Method for acquiring kinetic parameter of helicopter hub center - Google Patents
Method for acquiring kinetic parameter of helicopter hub center Download PDFInfo
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- CN106599403A CN106599403A CN201611068445.9A CN201611068445A CN106599403A CN 106599403 A CN106599403 A CN 106599403A CN 201611068445 A CN201611068445 A CN 201611068445A CN 106599403 A CN106599403 A CN 106599403A
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- hub center
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- propeller hub
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
Abstract
The invention discloses a method for acquiring a kinetic parameter of a helicopter hub center. The method for acquiring the kinetic parameter of the helicopter hub center comprises the following steps: step 1, establishing a helicopter finite element model including a helicopter rotor and an airframe; step 2, setting a calculation frequency bandwidth, performing modal analysis on the helicopter finite element model, and acquiring frequency response data of the overall mode; step 3, performing kinetic characteristic response simulation calculation on the hub center to obtain frequency response data of the hub center, and drawing an amplitude-frequency response curve and a phase-frequency response curve based on the frequency response data of the hub center and the frequency response data of the overall mode; and step 4, acquiring the kinetic parameter of the helicopter hub center. The method for acquiring the kinetic parameter of the helicopter hub center can provide a parameter for preliminary design phase analysis of helicopter ground resonance.
Description
Technical field
The present invention relates to Helicopter Technology field, more particularly to a kind of helicopter body quality allocation method.
Background technology
Helicopter integrated ground test platform mainly carries out synthetic operation harmony inspection, function to system and three big dynamic components
Property test, endurancing and the scientific research and testing of development stage, helicopter integrated ground test platform has the power knowledge of complexity
Topic, wherein ground resonance is a kind of wherein most dangerous situation, its essence is that lifting airscrew/body (stage body) kinetics are matched
Problem.
When lifting airscrew/body (stage body) ground resonance is solved the problems, such as, lifting airscrew/body (stage body) kinetics
Parameter mainly recognizes acquisition by way of dynamic test at this stage.Also do not have one kind to be gone straight up to by computational methods
(helicopter hub center power parameter includes propeller hub center effective mass Mf, has the method for machine propeller hub center kinetic parameter
Effect stiffness K f, effective damping Cf).
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
The content of the invention
It is an object of the invention to provide a kind of method for obtaining helicopter hub center power parameter is overcoming or extremely
Mitigate at least one drawbacks described above of prior art less.
For achieving the above object, the present invention provides a kind of method for obtaining helicopter hub center power parameter, described
Helicopter oar Grains center powers parameter is for the input value that calculates as ground resonance, aroused in interest in the acquisition helicopter hub
The method of mechanics parameter comprises the steps：Step 1：Set up helicopter FEM (finite element) model, the helicopter FEM (finite element) model bag
Include lifting airscrew and body；Step 2：Arrange and calculate frequency bandwidth, mode point is carried out to the helicopter FEM (finite element) model
Analysis, and obtain the frequency response data of Integral modes；Step 3：Dynamicss response emulation meter is carried out to the Jiang Grains centers
Calculate, so as to obtain the frequency response data of propeller hub center, and the frequency response data according to the Jiang Grains centers and the entirety
The frequency response data of mode draws amplitude-frequency response curve and phase frequency response curve；Step 4：According to the step
Rapid 1 data obtained to the step 3 and formula, obtain helicopter hub center power parameter.
Preferably, model analyses selection and ground resonance are carried out to the helicopter FEM (finite element) model in the step 1
The Integral modes of related helicopter FEM (finite element) model.
Preferably, the step 3 is specially：Arrange and calculate frequency bandwidth, and the X-direction in propeller hub center applies unit
Load, obtains frequency corresponding data of the propeller hub center under the corresponding mode of X-direction；Arrange and calculate frequency bandwidth, and in propeller hub
The Y direction at center applies specific loading, obtains frequency response data of the propeller hub center under the corresponding mode of Y direction；Choose
The frequency response data of the Integral modes in the step 2, makes X-direction frequency response curve and Y direction frequency is rung
Answer curve.
Preferably, the propeller hub center includes amplitude-frequency response data and phase in the frequency corresponding data of X-direction
Position-frequency response data；Include amplitude-frequency response data and phase frequency response number in the frequency response data of Y direction
According to.
Preferably, the setting calculating frequency bandwidth in the step 3 is consistent with the step 2.
Preferably, the helicopter hub center power parameter in the step 4 includes propeller hub center effective mass Mf, has
Effect stiffness K f, effective damping Cf.
Preferably, propeller hub center effective mass Mf is calculated using equation below：
Wherein,
Wherein,
X1Represent the amplitude of any point near propeller hub center；X2RepresentOutside 1The width of any point
Value；Represent X1The propeller hub center phase place of point；Represent X2The propeller hub center phase place of point；ω1Represent X1Point propeller hub center swash
Vibration frequency；ω2Represent X2The excited frequency of the propeller hub center of point.
Preferably, the propeller hub center effective rigidity Kf is calculated using equation below：
Wherein,
Wherein,
X1Represent the amplitude of any point near propeller hub center；X2RepresentOutside 1The width of any point
Value；Represent X1The propeller hub center phase place of point；Represent X2The propeller hub center phase place of point；ω1Represent X1Point propeller hub center swash
Vibration frequency；ω2Represent X2The excited frequency of the propeller hub center of point.
Preferably, the propeller hub center effective damping Cf is calculated using equation below：
Wherein,
Wherein,
X1Represent the amplitude of any point near propeller hub center；X2RepresentOutside 1The width of any point
Value；Represent X1The propeller hub center phase place of point；Represent X2The propeller hub center phase place of point；ω1Represent X1Point propeller hub center swash
Vibration frequency；ω2Represent X2The excited frequency of the propeller hub center of point.
The method of the acquisition helicopter hub center power parameter of the application provides a kind of acquisition in helicopter hub
The method of cardiodynamics parameter, the method can be used for the helicopter and rotor/platform body structure of current all configurations, be helicopter
The analysis of ground resonance concept phase provides parameter, the part design direction related to helicopter ground resonance.
Description of the drawings
Fig. 1 is that the flow process of the method for obtaining helicopter hub center power parameter according to an embodiment of the invention is illustrated
Figure.
Specific embodiment
To make purpose, technical scheme and the advantage of present invention enforcement clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than the embodiment of whole.It is exemplary below with reference to the embodiment of Description of Drawings, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment obtained under the premise of creative work is not made by member, belongs to the scope of protection of the invention.Under
Face combines accompanying drawing and embodiments of the invention is described in detail.
In describing the invention, it is to be understood that term " " center ", " longitudinal direction ", " horizontal ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " is based on accompanying drawing institute
The orientation for showing or position relationship, are for only for ease of the description present invention and simplify description, rather than indicate or imply the dress of indication
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The restriction of scope.
Fig. 1 is that the flow process of the method for obtaining helicopter hub center power parameter according to an embodiment of the invention is illustrated
Figure.
The method of acquisition helicopter hub center power parameter as shown in Figure 1 is defeated for what is calculated as ground resonance
Enter value, the method for the acquisition helicopter hub center power parameter comprises the steps：
Step 1：Helicopter FEM (finite element) model is set up, helicopter FEM (finite element) model includes lifting airscrew and body；
Step 2：Arrange and calculate frequency bandwidth, model analyses are carried out to helicopter FEM (finite element) model, and obtains Integral modes
Frequency response data；
Step 3：Dui Jiang Grains centers carry out dynamicss response simulation calculation, so as to obtain the frequency response of propeller hub center
Data, and the frequency response data according to Jiang Grains centers is bent with frequency response data drafting amplitude-frequency response of Integral modes
Line and phase frequency response curve；
Step 4：The data obtained according to step 1 to step 3 and formula, obtain helicopter hub center power ginseng
Number.
The method of the acquisition helicopter hub center power parameter of the application provides a kind of acquisition in helicopter hub
The method of cardiodynamics parameter, the method can be used for the helicopter and rotor/platform body structure of current all configurations, be helicopter
The analysis of ground resonance concept phase provides parameter, the part design direction related to helicopter ground resonance.
In the present embodiment, the model analyses that carry out to the helicopter FEM (finite element) model in the step 1 are chosen and ground
The Integral modes of the related helicopter FEM (finite element) model of face resonance.
In the present embodiment, the step 3 is specially：Arrange and calculate frequency bandwidth, and the X-direction in propeller hub center is applied
Plus specific loading, obtain frequency corresponding data of the propeller hub center under the corresponding mode of X-direction；Arrange and calculate frequency bandwidth, and
Apply specific loading in the Y direction of propeller hub center, obtain frequency response number of the propeller hub center under the corresponding mode of Y direction
According to；The frequency response data of the Integral modes in the step 2 is chosen, X-direction frequency response curve and Y direction is made
Frequency response curve.
In the present embodiment, the propeller hub center includes amplitude-frequency response data in the frequency corresponding data of X-direction
With phase frequency response data；Include that amplitude-frequency response data and Phase-Frequency ring in the frequency response data of Y direction
Answer data.
In the present embodiment, the setting calculating frequency bandwidth in the step 3 is consistent with the step 2.
In the present embodiment, the helicopter hub center power parameter in the step 4 includes the effective matter of propeller hub center
Amount Mf, effective rigidity Kf, effective damping Cf.
In the present embodiment, propeller hub center effective mass Mf is calculated using equation below：
Wherein,
Wherein,
X1Represent the amplitude of any point near propeller hub center；X2RepresentOutside 1The width of any point
Value；Represent X1The propeller hub center phase place of point；Represent X2The propeller hub center phase place of point；ω1Represent X1Point propeller hub center swash
Vibration frequency；ω2Represent X2The excited frequency of the propeller hub center of point.
In the present embodiment, the propeller hub center effective rigidity Kf is calculated using equation below：
Wherein,
Wherein,
X1Represent the amplitude of any point near propeller hub center；X2RepresentOutside 1The width of any point
Value；Represent X1The propeller hub center phase place of point；Represent X2The propeller hub center phase place of point；ω1Represent X1Point propeller hub center swash
Vibration frequency；ω2Represent X2The excited frequency of the propeller hub center of point.
In the present embodiment, the propeller hub center effective damping Cf is calculated using equation below：
Wherein,
Wherein,
X1Represent the amplitude of any point near propeller hub center；X2RepresentOutside 1The width of any point
Value；Represent X1The propeller hub center phase place of point；Represent X2The propeller hub center phase place of point；ω1Represent X1Point propeller hub center swash
Vibration frequency；ω2Represent X2The excited frequency of the propeller hub center of point.
It is last it is to be noted that：Above example only to illustrate technical scheme, rather than a limitation.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：Which is still
Technical scheme described in foregoing embodiments can be modified, or equivalent is carried out to which part technical characteristic and replace
Change；And these modifications or replacement, do not make the essence of appropriate technical solution depart from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (9)
1. a kind of method for obtaining helicopter hub center power parameter, the helicopter Jiang Grains center power parameters are used for
As the input value that ground resonance is calculated, it is characterised in that the method bag of the acquisition helicopter hub center power parameter
Include following steps：
Step 1：Helicopter FEM (finite element) model is set up, the helicopter FEM (finite element) model includes lifting airscrew and body；
Step 2：Arrange and calculate frequency bandwidth, model analyses are carried out to the helicopter FEM (finite element) model, and obtains Integral modes
Frequency response data；
Step 3：Dynamicss response simulation calculation is carried out to the Jiang Grains centers, so as to obtain the frequency response of propeller hub center
Data, and the frequency response data of the frequency response data according to the Jiang Grains centers and the Integral modes draws amplitude-frequency
Rate response curve and phase frequency response curve；
Step 4：The data obtained to the step 3 according to the step 1 and formula, obtain helicopter hub center power
Learn parameter.
2. the method for obtaining helicopter hub center power parameter as claimed in claim 1, it is characterised in that the step
The model analyses selection helicopter FEM (finite element) model related to ground resonance is carried out to the helicopter FEM (finite element) model in 1
Integral modes.
3. the method for obtaining helicopter hub center power parameter as claimed in claim 2, it is characterised in that the step
3 are specially：Arrange and calculate frequency bandwidth, and the X-direction in propeller hub center applies specific loading, propeller hub center is obtained in X-axis
Frequency corresponding data under the corresponding mode in direction；Arrange and calculate frequency bandwidth, and the Y direction in propeller hub center applies unit load
Lotus, obtains frequency response data of the propeller hub center under the corresponding mode of Y direction；Choose Integral modes in the step 2
Frequency response data, makes X-direction frequency response curve and Y direction frequency response curve.
4. the method for obtaining helicopter hub center power parameter as claimed in claim 3, it is characterised in that the propeller hub
Center includes amplitude-frequency response data and phase frequency response data in the frequency corresponding data of X-direction；In Y direction
Frequency response data include amplitude-frequency response data and phase frequency response data.
5. the method for obtaining helicopter hub center power parameter as claimed in claim 4, it is characterised in that the step
It is consistent with the step 2 that setting in 3 calculates frequency bandwidth.
6. the method for obtaining helicopter hub center power parameter as claimed in claim 5, it is characterised in that the step
Helicopter hub center power parameter in 4 includes propeller hub center effective mass Mf, effective rigidity Kf, effective damping Cf.
7. the method for obtaining helicopter hub center power parameter as claimed in claim 6, it is characterised in that the propeller hub
Center effective mass Mf is calculated using equation below：
Wherein,
Wherein,
X1Represent the amplitude of any point near propeller hub center；X2RepresentOutside 1The amplitude of any point；Generation
Table X1The propeller hub center phase place of point；Represent X2The propeller hub center phase place of point；ω1Represent X1The excited frequency of the propeller hub center of point；
ω2Represent X2The excited frequency of the propeller hub center of point.
8. the method for obtaining helicopter hub center power parameter as claimed in claim 7, it is characterised in that the propeller hub
Center effective rigidity Kf is calculated using equation below：
Wherein,
Wherein,
X1Represent the amplitude of any point near propeller hub center；X2RepresentOutside 1The amplitude of any point；Generation
Table X1The propeller hub center phase place of point；Represent X2The propeller hub center phase place of point；ω1Represent X1The excited frequency of the propeller hub center of point；
ω2Represent X2The excited frequency of the propeller hub center of point.
9. the method for obtaining helicopter hub center power parameter as claimed in claim 8, it is characterised in that the propeller hub
Effective damping Cf in center is calculated using equation below：
Wherein,
Wherein,
X1Represent the amplitude of any point near propeller hub center；X2RepresentOutside 1The amplitude of any point；Generation
Table X1The propeller hub center phase place of point；Represent X2The propeller hub center phase place of point；ω1Represent X1The excited frequency of the propeller hub center of point；
ω2Represent X2The excited frequency of the propeller hub center of point.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108108531A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of coaxial double-rotor helicopter ground resonance modeling method |
-
2016
- 2016-11-29 CN CN201611068445.9A patent/CN106599403A/en active Pending
Non-Patent Citations (4)
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| 凌爱民: "《纵列式旋翼直升机在起落架上的振动特性试验方法研究》", 《直升机技术》 * |
| 凌爱民: "无轴承旋翼直升机气动机械稳定性分析", 《南京航空航天大学学报》 * |
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| 宁嘉: "基于有限元的直升机机体动力学建模与优化研究", 《中国优秀硕士学位论文全文数据库工程科技II辑》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108108531A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of coaxial double-rotor helicopter ground resonance modeling method |
| CN108108531B (en) * | 2017-12-03 | 2021-11-02 | 中国直升机设计研究所 | Ground modeling method for coaxial dual-rotor helicopter |
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Application publication date: 20170426 |