CN105716842B - A kind of long straight wing load processing method of two-beam type - Google Patents
A kind of long straight wing load processing method of two-beam type Download PDFInfo
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- CN105716842B CN105716842B CN201410738211.5A CN201410738211A CN105716842B CN 105716842 B CN105716842 B CN 105716842B CN 201410738211 A CN201410738211 A CN 201410738211A CN 105716842 B CN105716842 B CN 105716842B
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Abstract
The invention provides a kind of long straight wing load processing method of two-beam type, it is characterised in that comprises the following steps：According to the finite element node serial number of each rib of wing and position, in each rib front-axle beam and back rest property arrangement rubberized tape selected around, every piece of rubberized tape load value is the maximum load value that rubberized tape can be born, then front-axle beam is calculated according to each rib front-axle beam and back rest rubberized tape position and rubberized tape load value respectively, the load value that the lever ending coordinates and its lever system of the back rest can be born, the load value is the maximum bearing value of its lever system, each rib front-axle beam, the lever ending coordinates of the back rest are respectively the rib anterior resultant force point, Resultant force afterwards, before, the lever system of Resultant force is referred to as special lever afterwards.
Description
Technical field
This patent is related to a kind of long straight wing load processing method of two-beam type, and being applied to two-beam type especially with regard to one kind grows
The wing-box load processing of the complete aircraft structure static strength test of straight wing and loading method.
Background technology
Complete aircraft structure static strength test is that research aircraft and its component structural are quiet strong under dead weight
Characteristic is spent, can the purpose is to meet Structural Strength Design and static strength code requirement by verification experimental verification aircaft configuration.Wing
It is an important component of aircraft, needs to carry out wing-box loading simulation wing in finite element analysis in different flights
The carrying and deformation of state.Current FEM model that each airplane design is established to aircraft wing carries out numerical analysis, and experiment is appointed
The given wing loads of business book are also finite element panel load, are excessively divided for finite element analysis wing finite element panel load
Dissipate, it is easy to the problem of larger difference in size or even opposite sign occur, it is therefore desirable at its original finite element panel load
Reason applies in order to test.Current most of wing-box uses " rubberized tape-lever " loading system more, in the past in experiment, often
The wing-box load of individual operating mode is individually handled by one, is a very time-consuming workload, and artificial treatment is easy to
Error.Because the finite element panel load that test mission book gives is more scattered, if applied according to test mission book specified load
Adding will cause lever quantity and series more, experiment loading error increase.
The content of the invention
In order to solve two-beam type long straight wing box section load processing workload is big, more than lever-loading series and load processing
The problem of efficiency is low, this patent provide a kind of long straight wing load processing method of two-beam type, it is characterised in that including following step
Suddenly：
1) according to the finite element node serial number of each rib of wing and position, in each rib front-axle beam and back rest property cloth selected around
Rubberized tape is put, every piece of rubberized tape load value is the maximum load value that rubberized tape can be born, then according to each rib front-axle beam and the back rest
The load that rubberized tape position and rubberized tape load value calculate front-axle beam respectively, the lever ending coordinates of the back rest and its lever system can be born
Charge values, the load value are referred to as the maximum bearing value of its lever system, and each rib front-axle beam, the lever ending coordinates of the back rest are respectively to be somebody's turn to do
Rib anterior resultant force point, rear Resultant force, the lever system of forward and backward Resultant force are referred to as special lever；
2) it is true to be located approximately at the forward and backward Resultant force of the rib for the aerodynamic loading of each rib finite element node and the inertial load pressure heart
On this fixed straight line, according to the forward and backward Resultant force 1) determined, according to the principle of equal effects of power, by each rib of every kind of operating mode
Aerodynamic loading and the equivalent forward and backward Resultant force to the rib of inertial load, can obtain the forward and backward Resultant force of each rib of each operating mode
Load value；
3) checking procedure, statistics is carried out to the load value of the forward and backward Resultant force of each rib of all operating modes and can obtain each rib
The maximum load value of forward and backward Resultant force, examines whether the load value exceedes the maximum bearing value of lever system, if right more than if
The quantity of the rubberized tape of forward and backward Resultant force is increased, and recalculates according to step 1) and 2) forward and backward Resultant force and each operating mode
Each rib forward and backward Resultant force load value；
4) error calculation, according to the special lever of the forward and backward Resultant force of each rib in 1) step and each forward and backward conjunction of rib is formed
The position of the rubberized tape in force, quantity can calculate maximum carrying of each rubberized tape load value in the forward and backward Resultant force of each rib
The ratio of value, thus ratio can with the forward and backward Resultant force of each rib of each operating mode of Extrapolation every piece of rubberized tape load, so
According to the LOAD FOR load-transfer mechanism of rubberized tape position, rubberized tape, the aerodynamic loading of each rib and inertial load press the heart afterwards afterwards,
Aerodynamic loading and inertial load the pressure heart with each rib finite element node are contrasted respectively, and whether calculation error value, which meets, carries
Lotus equivalent process error.
Using this processing method can according to the load value of the forward and backward Resultant force of known each rib, by before each or
The different sections of the front-axle beam position of several adjacent ribs or back rest position are passed through section by Resultant force as a loading section afterwards
Between combining leverage form a load(ing) point, the special lever of each section keeps constant, changed the outfit the phase in different loads operating mode
Between need only to change combining leverage, be greatly saved section lever processing quantity and change the outfit the time.
The load treatment principle and method have advantages below：
1) accuracy of finite element analysis wing loads processing is improved；
2) finite element analysis wing loads treatment effeciency is improved；
3) effective rate of utilization of wing loading lever is improved；
4) processing quantity and the amount of changing the outfit of wing-box lever can be reduced during testing.
Brief description of the drawings
Fig. 1 is the long straight wing finite element schematic diagram of two-beam type
Fig. 2 is the long straight wing load process chart of two-beam type
Fig. 3 is anterior resultant force point special lever schematic diagram；
Fig. 4 is rear Resultant force special lever schematic diagram.
Embodiment
Realize that the flow chart that the long straight wing load of two-beam type is handled is as shown in Figure 2 with computer program.
Program is divided into two parts of data verification and data processing, and all calculation procedures are completed using VC++.
The invention provides a kind of long straight wing load processing method of two-beam type, it is characterised in that comprises the following steps：
1) according to the finite element node serial number of each rib of wing and position, in each rib front-axle beam and back rest property cloth selected around
Rubberized tape is put, as shown in figure 1, every piece of rubberized tape load value is the maximum load value that rubberized tape can be born, then according to each rib
Front-axle beam and back rest rubberized tape position and rubberized tape load value calculate the lever ending coordinates and its lever system of front-axle beam, the back rest respectively
The load value that can be born, the load value are referred to as the maximum bearing value of its lever system, and each rib front-axle beam, the lever end of the back rest are sat
Mark is respectively rib anterior resultant force point, the rear Resultant force, and the lever system of forward and backward Resultant force is referred to as special lever, such as Fig. 3, Fig. 4 points
Not Wei the forward and backward Resultant force of 4 ribs special lever, the P in figure represents the maximum bearing value of lever system；
2) it is true to be located approximately at the forward and backward Resultant force of the rib for the aerodynamic loading of each rib finite element node and the inertial load pressure heart
On this fixed straight line, according to the forward and backward Resultant force 1) determined, according to the principle of equal effects of power, by each rib of every kind of operating mode
Aerodynamic loading and the equivalent forward and backward Resultant force to the rib of inertial load, can obtain the forward and backward Resultant force of each rib of each operating mode
Load value；
3) checking procedure, statistics is carried out to the load value of the forward and backward Resultant force of each rib of all operating modes and can obtain each rib
The maximum load value of forward and backward Resultant force, examines whether the load value exceedes the maximum bearing value of lever system, if right more than if
The quantity of the rubberized tape of forward and backward Resultant force is increased, and recalculates according to step 1) and 2) forward and backward Resultant force and each operating mode
Each rib forward and backward Resultant force load value；
4) error calculation, according to the special lever of the forward and backward Resultant force of each rib in 1) step and each forward and backward conjunction of rib is formed
The position of the rubberized tape in force, quantity can calculate the maximum carrying of each rubberized tape load value and the forward and backward Resultant force of each rib
The ratio of value, thus ratio can with the forward and backward Resultant force of each rib of each operating mode of Extrapolation every piece of rubberized tape load, so
According to the LOAD FOR load-transfer mechanism of rubberized tape position, rubberized tape, the aerodynamic loading of each rib and inertial load press the heart afterwards afterwards,
Aerodynamic loading and inertial load the pressure heart with each rib finite element node are contrasted respectively, and whether calculation error value, which meets, carries
Lotus equivalent process error.
Data verification part includes file read-write, and logic judgment and basic mathematical calculate, and main completion work is will be limited
First coordinate file and finite element load file merge processing, calculate the load value and moment of flexure of each rib of each operating mode
Value, the full payload of each condition calculating and moment is contrasted with test mission book load, it is ensured that test load is errorless.
Data processing needs to call the full payload and moment of each rib above calculated, then utilizes the equivalent original of power
Its equivalent front and rear load(ing) point to the rib is managed, the load value of each piece of rubberized tape is calculated according to the lever ratio of front and rear load(ing) point, is counted
Calculate the error amount with raw payload after the completion of load is handled.
Claims (1)
1. a kind of long straight wing load processing method of two-beam type, it is characterised in that comprise the following steps：
Finite element node serial number and position of the step 1) according to each rib of wing, in each rib front-axle beam and back rest property cloth selected around
Rubberized tape is put, every piece of rubberized tape load value is the maximum load value that rubberized tape can be born, then according to each rib front-axle beam and the back rest
The load that rubberized tape position and rubberized tape load value calculate front-axle beam respectively, the lever ending coordinates of the back rest and its lever system can be born
Charge values, the load value are the maximum bearing value of its lever system, and each rib front-axle beam, the lever ending coordinates of the back rest are respectively the rib
Anterior resultant force point, rear Resultant force, the lever system of forward and backward Resultant force are referred to as special lever；
It is true that aerodynamic loading and inertial load the pressure heart of each rib finite element node of step 2) are located approximately at the forward and backward Resultant force of the rib
It is according to the principle of equal effects of power, every kind of operating mode is each according to the forward and backward Resultant force of step 1) determination on this fixed straight line
The equivalent forward and backward Resultant force to the rib of aerodynamic loading and inertial load of rib, each rib that can obtain each operating mode are forward and backward with joint efforts
The load value of point；
Step 3) checking procedure, screening is carried out to the load value of the forward and backward Resultant force of each rib of all operating modes and can obtain each rib
The maximum load value of forward and backward Resultant force, examines whether the load value exceedes the maximum bearing value of lever system, if right more than if
The quantity of the rubberized tape of forward and backward Resultant force is increased, and forward and backward Resultant force and each is recalculated according to step 1) and step 2)
The load value of the forward and backward Resultant force of each rib of operating mode；
Step 4) error calculation, according to the special lever of the forward and backward Resultant force of each rib in step 1) and form each forward and backward conjunction of rib
The position of the rubberized tape in force, quantity can calculate the maximum carrying of each rubberized tape load value and the forward and backward Resultant force of each rib
The ratio of value, thus the forward and backward Resultant force of each rib of each operating mode of ratio Extrapolation is in the load of every piece of rubberized tape, Ran Hougen
According to rubberized tape position, rubberized tape LOAD FOR load-transfer mechanism after each rib aerodynamic loading and the inertial load pressure heart, respectively
Contrasted with aerodynamic loading and inertial load the pressure heart of each rib finite element node, whether calculation error value meets load etc.
Effect processing error.
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| CN107038296B (en) * | 2017-04-06 | 2020-12-18 | 深圳数设科技有限公司 | Method and device for determining finite element point load distribution in airplane airfoil |
| CN109490114B (en) * | 2018-12-12 | 2021-05-07 | 中国航空工业集团公司西安飞机设计研究所 | Full-size fatigue test flap load loading method |
| CN109490116A (en) * | 2018-12-12 | 2019-03-19 | 中国航空工业集团公司西安飞机设计研究所 | A kind of wing Plumb load method of full scale fatigue test |
| CN111301713A (en) * | 2020-04-09 | 2020-06-19 | 中国飞机强度研究所 | Double-beam type wing adhesive tape load sharing method |
| CN112109919B (en) * | 2020-04-30 | 2024-04-19 | 中国飞机强度研究所 | Loading point layout method for strength test |
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| CN1273814C (en) * | 2002-12-31 | 2006-09-06 | 中国农业机械化科学研究院 | On-site calibrating test method and its device for landing gear load |
| CN201575950U (en) * | 2009-12-14 | 2010-09-08 | 中国飞机强度研究所 | Tension and compression pad-lever loading device |
| CN102680236B (en) * | 2012-05-11 | 2014-10-22 | 中国航空工业集团公司西安飞机设计研究所 | Structural strength test loading device for aircraft wing-mounted engine |
| CN103303493B (en) * | 2013-01-05 | 2015-12-02 | 中国航空工业集团公司西安飞机设计研究所 | A kind of large aircraft strength test wing loads bringing device |
| CN103678763A (en) * | 2013-10-14 | 2014-03-26 | 北京航空航天大学 | Method for aeroelastic tailoring of composite wing and genetic/sensitivity-based hybrid optimization method of composite wing |
| CN103577648B (en) * | 2013-11-13 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | The defining method of wing structural load when transport class aircraft cargo drops |
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