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CN106353033B - A kind of aero-engine centroid computing method - Google Patents

A kind of aero-engine centroid computing method Download PDF

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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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金路
雷雨恒
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Beijing Kangda Huichuang Technology Co ltd
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Shenyang Jianzhu University
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    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract

本发明公开一种航空发动机质心计算方法；该方法具有计算精度高、普适性强、方便快捷等优点；本发明的技术方案是：一种航空发动机质心计算方法，主要包括以下步骤：a.建立部件局部坐标系相对于相对坐标系的变换矩阵；b.建立部件局部坐标系相对于主坐标系的变换矩阵；c.求取发动机质心；本发明用途：一、本发明够准确的计算发动机整机的质心参数，方便吊装和运输工装的设计及整机的装配等工作；二、本发明具有很强的普适性，可以计算任意一个部件的质心参数；三、本发明对于其它旋转类机械同样具有参考和借鉴意义。

The invention discloses a method for calculating the center of mass of an aero-engine; the method has the advantages of high calculation accuracy, strong universality, convenience and quickness; the technical solution of the invention is: a method for calculating the center of mass of an aero-engine, which mainly includes the following steps: a. Set up the transformation matrix of the component local coordinate system with respect to the relative coordinate system; b. set up the transformation matrix of the component local coordinate system with respect to the main coordinate system; The centroid parameter of the whole machine is convenient for the design of hoisting and transportation tooling and the assembly of the whole machine; two, the present invention has strong universality, and can calculate the centroid parameter of any part; three, the present invention is applicable to other rotating Machinery also has reference and reference significance.

Description

一种航空发动机质心计算方法A method for calculating the center of mass of an aeroengine

技术领域technical field

本发明涉及航空发动机领域，尤其涉及一种航空发动机质心的计算方法。The invention relates to the field of aero-engines, in particular to a method for calculating the centroid of an aero-engine.

背景技术Background technique

航空发动机质心是发动机的一个重要特征参数，是影响发动机吊装和运输设备设计等工作的一项重要技术指标。目前发动机质心的计算通常根据零部件的结构特点及安装的角向位置进行分类：将风扇、中介机匣、压气机、燃烧室、涡轮等具有轴对称特征且回转轴与发动机轴线重合的主机部件归为一类；将滑油箱、燃滑油散热器、转接齿轮箱等具有非轴对称特征且角向位置不固定的附件归为另一类。对于主机部件，可以借助Pro/E、UG等三维建模软件直接读出其质量特性数据，计算精度较高；但对于附件，则难度较大，由于附件数量多、结构复杂，附件的承制单位一般只提供一个简化的附件模型和一个包含局部坐标系的质量特性文件，因此单纯依靠三维软件是无法读取的。对于此类问题，目前采取的措施是首先将此类结构进行简化处理，将每个附件都视作一个质点进行分析，而质点位置的选取，随机性较强，人为误差较大。尽管多数附件的质量和体积都比较小，但由于发动机包含数十个附件，由附件带来的累计误差对发动机整体的影响不可忽视，目前尚缺少一种准确的发动机质心参数计算方法。The center of mass of an aero-engine is an important characteristic parameter of the engine, and an important technical index that affects the design of engine hoisting and transportation equipment. At present, the calculation of the center of mass of the engine is usually classified according to the structural characteristics of the parts and the angular position of the installation: the fan, the intermediate casing, the compressor, the combustion chamber, the turbine and other main components with axisymmetric characteristics and the axis of rotation coincide with the axis of the engine Classify them into one category; classify oil tanks, fuel oil radiators, transfer gearboxes and other accessories with non-axisymmetric features and angular positions that are not fixed into another category. For the host components, its mass characteristic data can be read directly with the help of 3D modeling software such as Pro/E and UG, and the calculation accuracy is high; but for the accessories, it is more difficult. Due to the large number and complex structure of the accessories, the manufacturing of the accessories The unit generally only provides a simplified accessory model and a mass characteristic file including the local coordinate system, so it cannot be read by relying solely on 3D software. For this kind of problem, the measures taken at present are to simplify the structure first, and analyze each attachment as a mass point, and the selection of the position of the mass point is relatively random and has a large human error. Although the mass and volume of most accessories are relatively small, since the engine contains dozens of accessories, the cumulative error brought by the accessories has a non-negligible impact on the overall engine. At present, there is still a lack of an accurate calculation method for the center of mass parameters of the engine.

发明内容Contents of the invention

本发明的目的是提出一种航空发动机质心计算方法，该方法具有计算精度高、普适性强、方便快捷等优点。The object of the present invention is to propose a method for calculating the center of mass of an aero-engine, which has the advantages of high calculation accuracy, strong universality, convenience and quickness, and the like.

为了实现上述发明的目的，本发明的技术方案是：In order to realize the purpose of the foregoing invention, the technical solution of the present invention is:

一种航空发动机质心计算方法，基于齐次坐标变换方法进行计算，主要包括以下步骤：A method for calculating the center of mass of an aeroengine is calculated based on a homogeneous coordinate transformation method, and mainly includes the following steps:

b.建立部件局部坐标系相对于相对坐标系的变换矩阵b. Establish the transformation matrix of the component local coordinate system relative to the relative coordinate system

a11.在发动机主安装节位置，建立发动机主坐标系；a11. Establish the main engine coordinate system at the position of the main engine installation section;

a12.根据部件质量特性文件，确定部件局部坐标系；a12. Determine the local coordinate system of the part according to the quality characteristic file of the part;

a13.过局部坐标系原点建立与主坐标系各轴同方向的相对坐标系；a13. Establish a relative coordinate system in the same direction as each axis of the main coordinate system through the origin of the local coordinate system;

a14.根据局部坐标系和相对坐标系，建立部件局部坐标系相对于相对坐标系的变换矩阵。a14. According to the local coordinate system and the relative coordinate system, establish the transformation matrix of the component local coordinate system relative to the relative coordinate system.

b.建立部件局部坐标系相对于主坐标系的变换矩阵b. Establish the transformation matrix of the component local coordinate system relative to the main coordinate system

b11.求取相对坐标系原点在主坐标系中的坐标；b11. Obtain the coordinates of the origin of the relative coordinate system in the main coordinate system;

b12.建立部件相对坐标系相对于主坐标系的变换矩阵；b12. Establish the transformation matrix of the component relative coordinate system relative to the main coordinate system;

b13.建立部件局部坐标系相对于主坐标系的变换矩阵。b13. Establish the transformation matrix of the component local coordinate system relative to the main coordinate system.

c.求取发动机质心c. Find the center of mass of the engine

c11.求取部件质心在局部坐标系中的坐标；c11. Obtain the coordinates of the centroid of the component in the local coordinate system;

c12.根据部件局部坐标系相对于主坐标系的变换矩阵，求取部件质心在主坐标系中的坐标；c12. Calculate the coordinates of the centroid of the component in the main coordinate system according to the transformation matrix of the component local coordinate system relative to the main coordinate system;

c13.根据部件质量和合力矩定理，求取发动机质心。c13. Calculate the center of mass of the engine according to the component mass and resultant moment theorem.

本发明的优点是：The advantages of the present invention are:

1、本发明的航空发动机质心计算方法能够准确的计算发动机整机的质心参数，方便吊装和运输工装的设计及整机的装配等工作。1. The method for calculating the center of mass of the aero-engine of the present invention can accurately calculate the parameters of the center of mass of the complete engine, and facilitate the design of hoisting and transportation tooling and the assembly of the complete machine.

2、本发明的航空发动机质心计算方法不仅适用于附件，也适用于主机件，具有很强的普适性，可以计算任意一个部件的质心参数。2. The method for calculating the center of mass of an aero-engine of the present invention is not only applicable to accessories, but also to main parts, and has strong universality, and can calculate the center of mass parameter of any part.

3、本发明的航空发动机质心计算方法不仅适用于航空发动机领域，对于其它旋转类机械同样意义。3. The method for calculating the center of mass of an aero-engine of the present invention is not only applicable to the field of aero-engines, but also has the same meaning for other rotating machines.

附图说明Description of drawings

图1是本发明的航空发动机质心计算方法原理图。Fig. 1 is a schematic diagram of the method for calculating the center of mass of an aeroengine according to the present invention.

图2是本发明的航空发动机质心计算方法实施流程图。Fig. 2 is an implementation flowchart of the method for calculating the center of mass of an aero-engine according to the present invention.

图3是本发明的航空发动机质心计算方法的零部件坐标变换几何模型。Fig. 3 is a coordinate transformation geometric model of parts of the aeroengine centroid calculation method of the present invention.

具体实施方式Detailed ways

结合附图1-3说明本实施方式，本实施方式的航空发动机质心计算方法其理论基础为齐次坐标变换方法和合力矩定理，按以下步骤进行计算：Illustrate this embodiment in conjunction with accompanying drawing 1-3, its theoretical basis of the calculation method of center of mass of aeroengine of this embodiment is the homogeneous coordinate transformation method and resultant moment theorem, calculates according to the following steps:

a.建立部件局部坐标系σ2相对于相对坐标系σ3的变换矩阵 a. Establish the transformation matrix of the component local coordinate system σ 2 relative to the relative coordinate system σ 3

a11.在发动机主安装节位置，建立发动机主坐标系σ1＝[O1；x1,y1,z1]；a11. At the position of the main engine installation section, establish the engine main coordinate system σ 1 =[O 1 ; x 1 ,y 1 ,z 1 ];

a12.根据部件质量特性文件，确定部件局部坐标系σ2＝[O2；x2,y2,z2]；a12. Determine the part local coordinate system σ 2 =[O 2 ; x 2 , y 2 , z 2 ] according to the part quality characteristic file;

a13.过局部坐标系σ2原点O2建立与主坐标系σ1各轴同方向的相对坐标系σ3＝[O3；x3,y3,z3]，坐标系σ2与σ3对应各轴的夹角分别为α、β、γ；a13. Establish a relative coordinate system σ 3 =[O 3 ; x 3 , y 3 , z 3 ] with the same direction as each axis of the main coordinate system σ 1 through the origin O 2 of the local coordinate system σ 2 , the coordinate systems σ 2 and σ 3 The included angles corresponding to each axis are α, β, γ respectively;

a14.根据局部坐标系σ2和相对坐标系σ3，建立部件局部坐标系σ2相对于相对坐标系σ3的变换矩阵其中a14. According to the local coordinate system σ 2 and the relative coordinate system σ 3 , establish the transformation matrix of the component local coordinate system σ 2 relative to the relative coordinate system σ 3 in

b.建立部件局部坐标系σ2相对于主坐标系σ1的变换矩阵 b. Establish the transformation matrix of the component local coordinate system σ 2 relative to the main coordinate system σ 1

b11.求取相对坐标系σ3原点在主坐标系σ1中的坐标 b11. Find the coordinates of the origin of the relative coordinate system σ 3 in the main coordinate system σ 1

b12.建立部件相对坐标系σ3相对于主坐标系σ1的变换矩阵b12. Establish the transformation matrix of the component relative coordinate system σ 3 relative to the main coordinate system σ 1

b13.建立部件局部坐标系σ2相对于主坐标系σ1的变换矩阵 b13. Establish the transformation matrix of the component local coordinate system σ 2 relative to the main coordinate system σ 1

c.求取发动机质心(X、Y、Z)c. Find the center of mass of the engine (X, Y, Z)

c11.求取部件质心在局部坐标系中的坐标Pi＝[x′i y′i z′i 1]T，其中i＝1,2，…，n；c11. Obtain the coordinates P i =[x′ i y′ i z′ i 1] T of the component centroid in the local coordinate system, where i=1,2,…,n;

c12.根据部件局部坐标系σ2相对于主坐标系σ1的变换矩阵求取部件质心在主坐标系中的坐标式中的(α、β、γ)、和(x′i y′iz′i)三组参数可通过质量特性文件和三维软件方便的得到；c12. According to the transformation matrix of the component local coordinate system σ 2 relative to the main coordinate system σ 1 Find the coordinates of the centroid of the part in the main coordinate system (α, β, γ) in the formula, and (x′ i y′ i z′ i ) three groups of parameters can be easily obtained through mass characteristic files and 3D software;

c13.最后，根据部件质量mi和合力矩定理，求取发动机质心(X、Y、Z)。c13. Finally, calculate the center of mass (X, Y, Z) of the engine according to the component mass m i and the resultant moment theorem.

Claims (4)

1.一种航空发动机质心计算方法，基于齐次坐标变换方法进行计算，其特征在于，1. A method for calculating the center of mass of an aero-engine is calculated based on a homogeneous coordinate transformation method, characterized in that, 主要包括以下步骤：It mainly includes the following steps: a.建立部件局部坐标系相对于相对坐标系的变换矩阵；a. Establish the transformation matrix of the component local coordinate system relative to the relative coordinate system; a11.在发动机主安装节位置，建立发动机主坐标系；a11. Establish the main engine coordinate system at the position of the main engine installation section; a12.根据部件质量特性文件，确定部件局部坐标系；a12. Determine the component local coordinate system according to the component quality characteristic file; a13.通过部件局部坐标系原点建立与主坐标系各轴同方向的相对坐标系；a13. Establish a relative coordinate system in the same direction as each axis of the main coordinate system through the origin of the local coordinate system of the component; a14.根据部件局部坐标系和相对坐标系，建立部件局部坐标系相对于相对坐标系的变换矩阵；a14. According to the component local coordinate system and the relative coordinate system, establish the transformation matrix of the component local coordinate system relative to the relative coordinate system; b.建立部件局部坐标系相对于主坐标系的变换矩阵；b. Establish the transformation matrix of the component local coordinate system relative to the main coordinate system; b11.求取相对坐标系原点在主坐标系中的坐标；b11. Obtain the coordinates of the origin of the relative coordinate system in the main coordinate system; b12.建立部件相对坐标系相对于主坐标系的变换矩阵；b12. Establish the transformation matrix of the component relative coordinate system relative to the main coordinate system; b13.建立部件局部坐标系相对于主坐标系的变换矩阵；b13. Establish the transformation matrix of the component local coordinate system relative to the main coordinate system; c.求取发动机质心；c. Find the center of mass of the engine; c11.求取部件质心在部件局部坐标系中的坐标；c11. Obtain the coordinates of the centroid of the component in the local coordinate system of the component; c12.根据部件局部坐标系相对于主坐标系的变换矩阵，求取部件质心在主坐标系中的坐标；c12. Calculate the coordinates of the centroid of the component in the main coordinate system according to the transformation matrix of the component local coordinate system relative to the main coordinate system; c13.根据部件质量和合力矩定理，求取发动机质心。c13. Calculate the center of mass of the engine according to the component mass and resultant moment theorem. 2.根据权利要求1所述的一种航空发动机质心计算方法，其特征在于：2. a kind of aero-engine centroid calculation method according to claim 1, is characterized in that: a.建立部件局部坐标系σ2相对于相对坐标系σ3的变换矩阵 a. Establish the transformation matrix of the component local coordinate system σ 2 relative to the relative coordinate system σ 3 a11.在发动机主安装节位置，建立发动机主坐标系σ1＝[O1；x1,y1,z1]；a11. At the position of the main engine installation section, establish the engine main coordinate system σ 1 =[O 1 ; x 1 ,y 1 ,z 1 ]; a12.根据部件质量特性文件，确定部件局部坐标系σ2＝[O2；x2,y2,z2]；a12. Determine the part local coordinate system σ 2 =[O 2 ; x 2 , y 2 , z 2 ] according to the part quality characteristic file; a13.通过部件局部坐标系σ2原点O2建立与主坐标系σ1各轴同方向的相对坐标系σ3＝[O3；x3,y3,z3]，坐标系σ2与σ3对应各轴的夹角分别为α、β、γ；a13. Establish the relative coordinate system σ 3 = [O 3 ; x 3 , y 3 , z 3 ] in the same direction as each axis of the main coordinate system σ 1 through the origin O 2 of the component local coordinate system σ 2 , the coordinate system σ 2 and σ 3 The included angles corresponding to each axis are α, β, γ respectively; a14.根据部件局部坐标系σ2和相对坐标系σ3，建立部件局部坐标系σ2相对于相对坐标系σ3的变换矩阵其中a14. According to the component local coordinate system σ 2 and the relative coordinate system σ 3 , establish the transformation matrix of the component local coordinate system σ 2 relative to the relative coordinate system σ 3 in 3.根据权利要求1所述的一种航空发动机质心计算方法，其特征在于：3. a kind of aero-engine centroid calculation method according to claim 1, is characterized in that: b.建立部件局部坐标系σ2相对于主坐标系σ1的变换矩阵 b. Establish the transformation matrix of the component local coordinate system σ 2 relative to the main coordinate system σ 1 b11.求取相对坐标系σ3原点在主坐标系σ1中的坐标 b11. Find the coordinates of the origin of the relative coordinate system σ 3 in the main coordinate system σ 1 b12.建立相对坐标系σ3相对于主坐标系σ1的变换矩阵；b12. Establish the transformation matrix of the relative coordinate system σ 3 relative to the main coordinate system σ 1 ; b13.建立部件局部坐标系σ2相对于主坐标系σ1的变换矩阵 b13. Establish the transformation matrix of the component local coordinate system σ 2 relative to the main coordinate system σ 1 4.根据权利要求1所述的一种航空发动机质心计算方法，其特征在于：4. a kind of aeroengine centroid calculation method according to claim 1, is characterized in that: c.求取发动机质心(X、Y、Z)；c. Find the center of mass of the engine (X, Y, Z); c11.求取部件质心在部件局部坐标系中的坐标Pi＝[x′i y′i z′i 1]T，其中i＝1,2，…，n；c11. Calculate the coordinates P i =[x′ i y′ i z′ i 1] T of the component centroid in the component local coordinate system, where i=1,2,…,n; c12.根据部件局部坐标系σ2相对于主坐标系σ1的变换矩阵求取部件质心在主坐标系中的坐标式中的(α、β、γ)、和(x′i y′i z′i )三组参数能够通过部件质量特性文件和三维软件方便的得到；c12. According to the transformation matrix of the component local coordinate system σ 2 relative to the main coordinate system σ 1 Find the coordinates of the centroid of the part in the main coordinate system (α, β, γ) in the formula, and (x′ i y′ i z′ i ) three groups of parameters can be easily obtained through component quality characteristic files and 3D software; c13.最后，根据部件质量mi和合力矩定理，求取发动机质心(X、Y、Z)。c13. Finally, according to the component mass mi and resultant moment theorem, Find the center of mass (X, Y, Z) of the engine.
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