CN111797480A - Load distribution method for airplane bolt group - Google Patents

Load distribution method for airplane bolt group Download PDF

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CN111797480A
CN111797480A CN202010552987.3A CN202010552987A CN111797480A CN 111797480 A CN111797480 A CN 111797480A CN 202010552987 A CN202010552987 A CN 202010552987A CN 111797480 A CN111797480 A CN 111797480A
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bolt
load distribution
bolt group
shearing force
bolts
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CN111797480B (en
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张宪政
张里伟
朱亲强
黄晓霞
胡益富
侯方
梅李霞
万志强
李森
熊盼
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Jiangxi Hongdu Aviation Industry Group Co Ltd
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
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    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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Abstract

The invention provides a load distribution method for an airplane bolt group, which mainly comprises the following steps: establishing a three-dimensional rectangular coordinate system, determining the centroid position of a bolt group according to the diameter of the bolt and the coordinate value, and translating the load to the centroid position; secondly, solving the shearing force of the bolt according to the characteristics of the bolts at different positions; thirdly, solving the tension or pressure of the bolt according to the characteristics of the bolt at different positions; fourthly, arranging the shearing force, the pulling force or the pressure applied to the bolts at different positions, and combining the shearing force, the pulling force or the pressure applied to the bolts, namely the resultant force applied to the bolts after load sharing, so as to complete the load distribution of the bolt group. The proposed load distribution method for the airplane bolt group can simply, quickly and effectively complete the strength design of the bolt group.

Description

Load distribution method for airplane bolt group
Technical Field
The invention belongs to the technical field of mechanical structure strength design, and particularly relates to a load distribution method for an airplane bolt group.
Background
Most main load-bearing structures of the airplane are connected through bolts, a plurality of bolts are often needed to be connected at a large-load part, and how to accurately calculate the load of each bolt is indispensable to strength design. Generally, a finite element method or an analytic method is adopted for calculating the bolt load distribution, and a Chinese courtyard compiles a Chinese standard 'strength calculation method of bolts under static load', so that basic standard specifications are provided for the field.
However, the finite element method or the analytic method is adopted for calculation, and is suitable for the general engineering application field, but the calculation method is lack of pertinence, the calculation steps are complex, and the calculation amount is relatively large. If the relevant experience and test data can be summarized, a relatively conservative airplane bolt group load distribution method is obtained through analysis, and the strength design of the bolt group can be completed quickly and effectively.
Disclosure of Invention
In order to solve the defects in the prior art, the invention provides the load distribution method for the airplane bolt group, which is mainly used for rapidly and reliably completing the load distribution task of the airplane bolt group by summarizing relevant experience and test data and providing experience method steps and a calculation formula.
The invention relates to an airplane bolt group load distribution method, which mainly comprises the following steps:
establishing a three-dimensional rectangular coordinate system, determining the centroid position of a bolt group according to the diameter of the bolt and the coordinate value, solving the centroid position of the bolt group by using an analytic method or a graphical method, and translating the load to the centroid position;
secondly, solving the shearing force of the bolt according to the characteristics of the bolts at different positions;
thirdly, solving the tension or pressure of the bolt according to the characteristics of the bolt at different positions;
fourthly, arranging the shearing force, the pulling force or the pressure applied to the bolts at different positions, and combining the shearing force, the pulling force or the pressure applied to the bolts, namely the resultant force applied to the bolts after load sharing, so as to complete the load distribution of the bolt group.
Further, the above-mentioned method for obtaining the centroid position of the bolt group by using the analytical method, assuming that the centroid position of the bolt group is X, Y, Z, the calculation method is:
Figure BDA0002543184780000021
Figure BDA0002543184780000022
wherein A isiIs the cross-sectional area of the bolt.
Further, the method for solving the shearing force and the tensile force or the pressure of the bolt specifically comprises the following steps:
shear distribution
Figure BDA0002543184780000023
Shear force generated by torque
Figure BDA0002543184780000024
Wherein Ki＝min(Kjq,Kjy)、Kjq＝GπD2/4、Kjy＝EDtminG is the shear modulus of the bolt, E is the modulus of elasticity of the material of the joint area, D is the diameter of the bolt, tminIs the minimum thickness of the connecting region, MXFor X-axis bending moment after translation, riSynthesizing the obtained shearing force according to a parallelogram rule for the distance from the bolt to the centroid to obtain a bolt shearing force;
distribution of tension or pressure
Figure BDA0002543184780000025
Tensile or compressive forces resulting from bending moments
Figure BDA0002543184780000026
Wherein
Figure BDA0002543184780000027
riDistance of bolt to centroid, MX,ZIn order to translate the back bending moment, the final tension or pressure is directly algebraically superposed.
In the technical scheme, the provided method for distributing the load of the bolt group of the airplane can simply, quickly and effectively complete the strength design of the bolt group.
Drawings
Fig. 1 is a schematic diagram of a bolt group position and a load acting point according to the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to fig. 1, and it is obvious that the described embodiments are only a specific embodiment of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention discloses a load distribution method for a bolt group of an airplane, which is characterized in that the positions of the bolt group and the load action point are as shown in figure 1, and the load is acted in a plane vertical to the plane of the bolt group and is respectively PX、PY、PZ. And (4) solving the centroid position of the bolt group by an analytical method or a graphical method, and translating the load to the centroid position of the bolt group. The position coordinates of the centroid of the bolt group are obtained by an analytic method as follows:
Figure BDA0002543184780000031
wherein A isiIs the cross-sectional area of the bolt.
The load after translation was: pX、PY、PZ(2)
The translational back bending moment is:
Figure BDA0002543184780000032
and (3) respectively distributing the loads and the bending moments of the formulas (2) and (3) to different bolts, namely dividing the loads into shearing force, tensile force or pressure force of the bolts.
1. Shear force distribution:
Figure BDA0002543184780000041
shear force generated by torque:
Figure BDA0002543184780000042
wherein, Ki＝min(Kjq,Kjy)、Kjq＝GπD2/4、Kjy＝EDtminG is the shear modulus of the bolt, E is the modulus of elasticity of the material of the joint area, D is the diameter of the bolt, tminIs the minimum thickness of the connecting region, MXFor X-axis bending moment after translation, riThe distance from the bolt to the centroid.
And synthesizing the obtained shearing force according to a parallelogram rule to obtain the bolt shearing force.
2. Tension or pressure distribution:
Figure BDA0002543184780000043
tension or compression force generated by bending moment:
Figure BDA0002543184780000044
wherein the content of the first and second substances,
Figure BDA0002543184780000045
ridistance of bolt to centroid, MX,ZIs the translational back bending moment.
The final tension or pressure is directly algebraically superimposed.
The shearing force, the pulling force or the pressure borne by the comprehensive bolt is the resultant force borne by the bolt after load sharing.

Claims (3)

1. An aircraft bolt group load distribution method is characterized in that: the distribution method mainly comprises the following steps:
step1, establishing a three-dimensional rectangular coordinate system, determining the centroid position of the bolt group according to the diameter of the bolt and the coordinate value, solving the centroid position of the bolt group by using an analytic method or a graphical method, and translating the load to the centroid position;
step2, solving the shearing force of the bolt according to the characteristics of the bolt at different positions;
step3, solving the tension or pressure of the bolt according to the characteristics of the bolt at different positions;
step4, arranging the shearing force, the pulling force or the pressure applied to the bolts at different positions, and finishing the load distribution of the bolt group by synthesizing the shearing force, the pulling force or the pressure applied to the bolts, namely the resultant force applied to the bolts after load distribution.
2. The aircraft bolt cluster load distribution formula of claim 1, wherein: the centroid position of the bolt group is obtained by adopting an analytical method, and if the centroid position of the bolt group is X, Y, Z, the calculation method is as follows:
Figure FDA0002543184770000011
wherein A isiIs the cross-sectional area of the bolt.
3. The aircraft bolt cluster load distribution formula of claim 1, wherein: the method for solving the shearing force, the pulling force or the pressure of the bolt according to the characteristics of the bolt at different positions comprises the following specific steps:
shear distribution
Figure FDA0002543184770000012
Shear force generated by torque
Figure FDA0002543184770000013
Wherein Ki＝min(Kjq,Kjy)、Kjq＝GπD2/4、Kjy＝EDtminG is the shear modulus of the bolt and E is the elasticity of the material of the joint areaModulus, D is the bolt diameter, tminIs the minimum thickness of the connecting region, MXFor X-axis bending moment after translation, riSynthesizing the obtained shearing force according to a parallelogram rule for the distance from the bolt to the centroid to obtain a bolt shearing force;
distribution of tension or pressure
Figure FDA0002543184770000021
Tensile or compressive forces resulting from bending moments
Figure FDA0002543184770000022
Wherein
Figure FDA0002543184770000023
riDistance of bolt to centroid, MX,ZIn order to translate the back bending moment, the final tension or pressure is directly algebraically superposed.
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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2004212210A (en) * 2002-12-27 2004-07-29 National Aerospace Laboratory Of Japan Method for measuring shearing load of fastening implement
CN110020474A (en) * 2019-04-02 2019-07-16 西安交通大学 A kind of hard and soft contact large deflection disk-shaped structure Bolt load Accurate Prediction method
CN110457797A (en) * 2019-07-29 2019-11-15 中国航发沈阳发动机研究所 A kind of test moment of flexure bearing bolt screw-down torque distribution method
CN110619155A (en) * 2019-08-26 2019-12-27 浙江工业大学 Finite element method for determining stress of bolt group of strip-shaped base
CN110705140A (en) * 2019-08-28 2020-01-17 浙江工业大学 Method for determining stress distribution of bolt group of strip-shaped base under combined load effect

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2004212210A (en) * 2002-12-27 2004-07-29 National Aerospace Laboratory Of Japan Method for measuring shearing load of fastening implement
CN110020474A (en) * 2019-04-02 2019-07-16 西安交通大学 A kind of hard and soft contact large deflection disk-shaped structure Bolt load Accurate Prediction method
CN110457797A (en) * 2019-07-29 2019-11-15 中国航发沈阳发动机研究所 A kind of test moment of flexure bearing bolt screw-down torque distribution method
CN110619155A (en) * 2019-08-26 2019-12-27 浙江工业大学 Finite element method for determining stress of bolt group of strip-shaped base
CN110705140A (en) * 2019-08-28 2020-01-17 浙江工业大学 Method for determining stress distribution of bolt group of strip-shaped base under combined load effect

Non-Patent Citations (7)

* Cited by examiner, † Cited by third party
Title
MACHEL MORRISON 等: "Performance enhancement of eight bolt extended end-plate moment connections under simulated seismic loading", 《ENGINEERING STRUCTURES》 *
姜亚娟 等: "基于有限元的螺栓弯曲强度分析方法", 《教练机》 *
戴笠等: "浅析偏心受剪螺栓群受力", 《科技创新与应用》 *
林海彬 等: "吊挂横梁螺栓拉力计算结果差异性分析", 《兵器装备工程学报》 *
王恒等: "高强螺栓群纯弯作用下中和轴位置研究", 《武汉大学学报(工学版)》 *
网站小编: "典型螺栓组的受力分析及螺栓载荷计算", 《HTTPS://WWW.XD-SJ.COM/ARCHIVES/3108.HTML》 *
顾晓勤 等: "组合式登机桥高强度螺栓群的强度计算", 《机械工程与技术》 *

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