CN106353033B - A kind of aero-engine centroid computing method - Google Patents
A kind of aero-engine centroid computing method Download PDFInfo
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- CN106353033B CN106353033B CN201611007353.XA CN201611007353A CN106353033B CN 106353033 B CN106353033 B CN 106353033B CN 201611007353 A CN201611007353 A CN 201611007353A CN 106353033 B CN106353033 B CN 106353033B
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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
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/12—Static balancing; Determining position of centre of gravity
- G01M1/122—Determining position of centre of gravity
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Abstract
The present invention discloses a kind of aero-engine centroid computing method；This method has many advantages, such as that computational accuracy is high, universality is strong, convenient and efficient；The technical scheme is that：A kind of aero-engine centroid computing method, mainly includes the following steps that：A. transformation matrix of the component local coordinate system relative to relative coordinate system is established；B. transformation matrix of the component local coordinate system relative to master coordinate system is established；C. Motor Mass Centre is sought；Purposes of the present invention：One, the enough barycenter parameters for accurately calculating engine complete machine of the present invention, facilitate lifting and the work such as the design of transport frock and the assembly of complete machine；Two, the present invention has very strong universality, can calculate the barycenter parameter of any one component；Three, the present invention equally has reference and reference for other rotation classes machinery.
Description
Technical field
The present invention relates to aero-engine field more particularly to a kind of computational methods of aero-engine barycenter.
Background technology
Aero-engine barycenter is an important feature parameter of engine, is that influence Engine Hoisting and transporting equipment are set
One important technology index of the work such as meter.Design feature and installation of the calculating of Motor Mass Centre at present generally according to parts
Angular position classify：Fan, Middle casing, compressor, combustion chamber, turbine etc. had into axial symmetry feature and rotating shaft
The host part overlapped with engine axis is classified as one kind；Oil tank, combustion oil cooler, switching gear-box etc. had into non-axis
Symmetrical feature and the unfixed attachment of angular position are classified as another kind of.It, can be by three-dimensionals such as Pro/E, UG for host part
Modeling software directly reads its quality characteristics data, and computational accuracy is higher；But for attachment, then difficulty is larger, due to attachment number
Amount is more, complicated, and it includes local coordinate system that the manufacturer of attachment, which generally only provides a simplified accessory model and one,
Mass property file, therefore can not read by three-dimensional software merely.For problems, the measure taken at present is
This class formation is carried out first to simplify processing, each attachment is regarded as a particle and is analyzed, and the selection of particle position,
Randomness is stronger, and human error is larger.Although the quality and volume of most attachmentes are all smaller, since engine includes tens of
A attachment, by accessory tapes Lai influence of the cumulative errors to engine entirety it is very important, still lack a kind of accurately hair at present
Motivation barycenter calculation method of parameters.
Invention content
The purpose of the present invention is to propose to a kind of aero-engine centroid computing method, this method has computational accuracy high, general
The advantages that adaptive is strong, convenient and efficient.
In order to realize the purpose of foregoing invention, the technical scheme is that：
A kind of aero-engine centroid computing method, is calculated based on homogeneous coordinate transformation method, includes mainly following
Step：
B. transformation matrix of the component local coordinate system relative to relative coordinate system is established
A11. start owner's installation section to set, establish engine master coordinate system；
A12. according to part quality characteristic file, component local coordinate system is determined；
A13. local coordinate system origin is crossed to establish and the equidirectional relative coordinate system of each axis of master coordinate system；
A14. according to local coordinate system and relative coordinate system, change of the component local coordinate system relative to relative coordinate system is established
Change matrix.
B. transformation matrix of the component local coordinate system relative to master coordinate system is established
B11. coordinate of the relative coordinate system origin in master coordinate system is sought；
B12. transformation matrix of the component relative coordinate system relative to master coordinate system is established；
B13. transformation matrix of the component local coordinate system relative to master coordinate system is established.
C. Motor Mass Centre is sought
C11. coordinate of the component barycenter in local coordinate system is sought；
C12. the transformation matrix according to component local coordinate system relative to master coordinate system seeks component barycenter in master coordinate system
In coordinate；
C13. according to part quality and resultant force theorem of moments, Motor Mass Centre is sought.
It is an advantage of the invention that：
1, aero-engine centroid computing method of the invention can accurately calculate the barycenter parameter of engine complete machine, side
Just lifting and the work such as the design of transport frock and the assembly of complete machine.
2, aero-engine centroid computing method of the invention is applicable not only to attachment, is also applied for host part, has very
Strong universality can calculate the barycenter parameter of any one component.
3, aero-engine centroid computing method of the invention is applicable not only to aero-engine field, for other rotations
The same meaning of class machinery.
Description of the drawings
Fig. 1 is the aero-engine centroid computing method schematic diagram of the present invention.
Fig. 2 is the aero-engine centroid computing method implementing procedure figure of the present invention.
Fig. 3 is the parts coordinate transform geometrical model of the aero-engine centroid computing method of the present invention.
Specific implementation mode
Illustrate present embodiment, its theoretical base of the aero-engine centroid computing method of present embodiment in conjunction with attached drawing 1-3
Plinth is homogeneous coordinate transformation method and resultant force theorem of moments, is calculated according to the following steps：
A. component local coordinate system σ is established2Relative to relative coordinate system σ3Transformation matrix
A11. start owner's installation section to set, establish engine master coordinate system σ1=[O1；x1,y1,z1]；
A12. according to part quality characteristic file, component local coordinate system σ is determined2=[O2；x2,y2,z2]；
A13. local coordinate system σ is crossed2Origin O2It establishes and master coordinate system σ1Each equidirectional relative coordinate system σ of axis3=[O3；
x3,y3,z3], coordinate system σ2With σ3The angle of corresponding each axis is respectively α, β, γ；
A14. according to local coordinate system σ2With relative coordinate system σ3, establish component local coordinate system σ2Relative to relative coordinate
It is σ3Transformation matrixWherein
B. component local coordinate system σ is established2Relative to master coordinate system σ1Transformation matrix
B11. relative coordinate system σ is sought3Origin is in master coordinate system σ1In coordinate
B12. component relative coordinate system σ is established3Relative to master coordinate system σ1Transformation matrix
B13. component local coordinate system σ is established2Relative to master coordinate system σ1Transformation matrix
C. Motor Mass Centre (X, Y, Z) is sought
C11. coordinate P of the component barycenter in local coordinate system is soughti=[x 'i y′i z′i 1]T, wherein i=1,2 ...,
n；
C12. according to component local coordinate system σ2Relative to master coordinate system σ1Transformation matrixComponent barycenter is sought in master
Coordinate in coordinate system(α, β, γ) in formula,(x 'i y′i
z′i) three groups of parameters can easily be obtained by mass property file and three-dimensional software；
C13. last, according to part quality miWith resultant force theorem of moments, Motor Mass Centre (X, Y, Z) is sought.
Claims (4)
1. a kind of aero-engine centroid computing method, is calculated based on homogeneous coordinate transformation method, which is characterized in that
It mainly includes the following steps that：
A. transformation matrix of the component local coordinate system relative to relative coordinate system is established；
A11. start owner's installation section to set, establish engine master coordinate system；
A12. according to part quality characteristic file, component local coordinate system is determined；
A13. it is established and the equidirectional relative coordinate system of each axis of master coordinate system by component local coordinate system origin；
A14. according to component local coordinate system and relative coordinate system, change of the component local coordinate system relative to relative coordinate system is established
Change matrix；
B. transformation matrix of the component local coordinate system relative to master coordinate system is established；
B11. coordinate of the relative coordinate system origin in master coordinate system is sought；
B12. transformation matrix of the component relative coordinate system relative to master coordinate system is established；
B13. transformation matrix of the component local coordinate system relative to master coordinate system is established；
C. Motor Mass Centre is sought；
C11. coordinate of the component barycenter in component local coordinate system is sought；
C12. the transformation matrix according to component local coordinate system relative to master coordinate system seeks component barycenter in master coordinate system
Coordinate；
C13. according to part quality and resultant force theorem of moments, Motor Mass Centre is sought.
2. a kind of aero-engine centroid computing method according to claim 1, it is characterised in that：
A. component local coordinate system σ is established2Relative to relative coordinate system σ3Transformation matrix
A11. start owner's installation section to set, establish engine master coordinate system σ1=[O1；x1,y1,z1]；
A12. according to part quality characteristic file, component local coordinate system σ is determined2=[O2；x2,y2,z2]；
A13. pass through component local coordinate system σ2Origin O2It establishes and master coordinate system σ1Each equidirectional relative coordinate system σ of axis3=
[O3；x3,y3,z3], coordinate system σ2With σ3The angle of corresponding each axis is respectively α, β, γ；
A14. according to component local coordinate system σ2With relative coordinate system σ3, establish component local coordinate system σ2Relative to relative coordinate
It is σ3Transformation matrixWherein
3. a kind of aero-engine centroid computing method according to claim 1, it is characterised in that：
B. component local coordinate system σ is established2Relative to master coordinate system σ1Transformation matrix
B11. relative coordinate system σ is sought3Origin is in master coordinate system σ1In coordinate
B12. relative coordinate system σ is established3Relative to master coordinate system σ1Transformation matrix；
B13. component local coordinate system σ is established2Relative to master coordinate system σ1Transformation matrix
4. a kind of aero-engine centroid computing method according to claim 1, it is characterised in that：
C. Motor Mass Centre (X, Y, Z) is sought；
C11. coordinate P of the component barycenter in component local coordinate system is soughti=[x 'i y′i z′i 1]T, wherein i=1,2 ...,
n；
C12. according to component local coordinate system σ2Relative to master coordinate system σ1Transformation matrixComponent barycenter is sought in principal coordinate
Coordinate in system(α, β, γ) in formula,(x 'i y′i z′i )
Three groups of parameters can easily be obtained by part quality characteristic file and three-dimensional software；
C13. last, according to part quality mi and resultant force theorem of moments,Seek Motor Mass Centre (X, Y,
Z)。
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| CN106979843B (en) * | 2016-01-15 | 2019-08-27 | 中国航发常州兰翔机械有限责任公司 | A kind of aero-engine center of gravity detection method |
| CN107238468B (en) * | 2017-08-01 | 2019-06-18 | 中科新松有限公司 | Discrimination method, device, equipment and the storage medium of mechanical arm tail end tool mass center |
| CN108267266B (en) * | 2017-12-21 | 2019-11-22 | 北汽福田汽车股份有限公司 | The measurement method and device of vehicle centroid |
| CN111307370A (en) * | 2020-03-19 | 2020-06-19 | 青岛航空技术研究院(中国科学院工程热物理研究所青岛研究中心) | Method for measuring rotational inertia of unmanned aerial vehicle |
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