CN105716842A - Double-beam type long straight wing load processing method - Google Patents
Double-beam type long straight wing load processing method Download PDFInfo
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- CN105716842A CN105716842A CN201410738211.5A CN201410738211A CN105716842A CN 105716842 A CN105716842 A CN 105716842A CN 201410738211 A CN201410738211 A CN 201410738211A CN 105716842 A CN105716842 A CN 105716842A
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Abstract
The invention provides a double-beam type long straight wing load processing method. The double-beam type long straight wing load processing method comprises the following steps: according to a finite element node number and position of each rib of a wing, selectively distributing adhesive tapes around the front beam and the back beam of each rib, wherein the load value of each adhesive tape is the maximum load value that the adhesive tape can bear; and according to the positions of the adhesive tapes of the front beam and the back beam of each rib, respectively calculating the lever end coordinates of the front beam and the back beam, and a load value that the lever system can bear, wherein the load value is the maximum bearing value of the lever system; the lever end coordinates of the front beam and the back beam of each rib are respectively the front resultant force point and the back resultant force point; and the lever systems for the front resultant force point and the back resultant force point are uniformly named as a special lever.
Description
Technical field
This patent relates to a kind of long straight wing load processing method of two-beam type, and the wing-box load especially with regard to a kind of complete aircraft structure static strength test being applied to the long straight wing of two-beam type processes and loading method.
Background technology
Can complete aircraft structure static strength test be research aircraft and component structural static strength characteristic under dead weight thereof, its objective is be met Structural Strength Design and static strength code requirement by verification experimental verification aircaft configuration.Wing is a vitals of aircraft, needs wing-box is carried out loading simulation wing in the carrying of different flight state and deformation in finite element analysis.Aircraft wing is set up FEM (finite element) model and is carried out numerical analysis by current each airplane design, the wing loads that test mission book is given is also finite element panel load, finite element analysis wing finite element panel load is excessively disperseed, the problem being easy to the relatively big even opposite sign of difference in size occurs, it is therefore desirable to be processed for its original finite element panel load applying in test.The at present major part many uses of wing-box " rubberized tape lever " loading system, in the past in test, the wing-box load of each operating mode, by single individual processing, is a workload very consuming time, and artificial treatment is as easy as rolling off a log makes mistakes.The finite element panel load given due to test mission book is comparatively disperseed, if applying to cause that lever quantity and progression are more according to test mission book specified load, test loading error increases.
Summary of the invention
Processing, in order to solve two-beam type long straight wing box section load, the problem that workload is big, lever-loading progression is many and load treatment effeciency is low, this patent provides a kind of long straight wing load processing method of two-beam type, it is characterised in that comprise the following steps:
1) according to the finite element node serial number of each rib of wing and position, rubberized tape is arranged in each rib front-axle beam and back rest property selected around, every piece of rubberized tape load value is the maximum load value that rubberized tape can bear, then front-axle beam is calculated respectively according to each rib front-axle beam and back rest rubberized tape position and rubberized tape load value, the load value that the lever ending coordinates of the back rest and lever system thereof can bear, this load value is called the maximum bearing value of its lever system, each rib front-axle beam, the lever ending coordinates of the back rest is this rib anterior resultant force point respectively, rear Resultant force, before, the lever system of rear Resultant force is referred to as special lever；
2) aerodynamic loading of each rib finite element node and the inertial load pressure heart are located approximately on this straight line that the forward and backward Resultant force of this rib is determined, according to 1) the forward and backward Resultant force determined, the principle of equal effects according to power, by the aerodynamic loading of every kind of each rib of operating mode and inertial load equivalence to the forward and backward Resultant force of this rib, the load value of the forward and backward Resultant force of each rib of each operating mode can be obtained；
3) checking procedure, carry out adding up the maximum load value that can obtain the forward and backward Resultant force of each rib to the load value of the forward and backward Resultant force of each rib of all operating modes, check whether this load value exceedes the maximum bearing value of lever system, if exceeding, the quantity of the rubberized tape of forward and backward Resultant force is increased, according to step 1) and 2) recalculate the load value of the forward and backward Resultant force of each rib of forward and backward Resultant force and each operating mode；
4) Error Calculation, according to 1) in step before each rib, before the special lever of rear Resultant force and each rib of composition, the position of the rubberized tape of rear Resultant force, quantity can calculate each rubberized tape load value before each rib, the ratio of the maximum bearing value of rear Resultant force, thus ratio can before each rib of each operating mode of Extrapolation, rear Resultant force is in the load of every piece of rubberized tape, then according to rubberized tape position, the aerodynamic loading of each rib and the inertial load pressure heart after the LOAD FOR load-transfer mechanism of rubberized tape, the heart is pressed to contrast with the aerodynamic loading of each rib finite element node and inertial load respectively, calculate whether error amount meets load-transfer mechanism process error.
Adopt this processing method can according to the load value of the forward and backward Resultant force of known each rib, Resultant force before or after each is loaded tangent plane as one, by the different tangent planes of the front-axle beam position of several ribs adjacent or back rest position by combining leverage one load(ing) point of composition between tangent plane, the special lever of each tangent plane remains unchanged, need only to change combining leverage during different loads operating mode changes the outfit, be greatly saved the processing quantity of tangent plane lever and change the outfit the time.
This load treatment principle and method have the advantage that
1) improve the accuracy that finite element analysis wing loads processes；
2) finite element analysis wing loads treatment effeciency is improved；
3) improve wing and load the effective rate of utilization of lever；
4) process of the test can reduce processing quantity and the amount of changing the outfit of wing-box lever.
Accompanying drawing explanation
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.
Detailed description of the invention
Flow chart that the long straight wing load of two-beam type processes is realized as shown in Figure 2 with computer program.
Program is divided into data verification and data to process two parts, and all calculation procedures all use VC++ to complete.
The invention provides a kind of long straight wing load processing method of two-beam type, it is characterised in that comprise the following steps:
1) according to the finite element node serial number of each rib of wing and position, rubberized tape is arranged in each rib front-axle beam and back rest property selected around, as shown in Figure 1, every piece of rubberized tape load value is the maximum load value that rubberized tape can bear, then front-axle beam is calculated respectively according to each rib front-axle beam and back rest rubberized tape position and rubberized tape load value, the load value that the lever ending coordinates of the back rest and lever system thereof can bear, this load value is called the maximum bearing value of its lever system, each rib front-axle beam, the lever ending coordinates of the back rest is this rib anterior resultant force point respectively, rear Resultant force, before, the lever system of rear Resultant force is referred to as special lever, such as Fig. 3, before Fig. 4 respectively 4 ribs, the special lever of rear Resultant force, P in figure represents the maximum bearing value of lever system；
2) aerodynamic loading of each rib finite element node and the inertial load pressure heart are located approximately on this straight line that the forward and backward Resultant force of this rib is determined, according to 1) the forward and backward Resultant force determined, the principle of equal effects according to power, by the aerodynamic loading of every kind of each rib of operating mode and inertial load equivalence to the forward and backward Resultant force of this rib, the load value of the forward and backward Resultant force of each rib of each operating mode can be obtained；
3) checking procedure, carry out adding up the maximum load value that can obtain the forward and backward Resultant force of each rib to the load value of the forward and backward Resultant force of each rib of all operating modes, check whether this load value exceedes the maximum bearing value of lever system, if exceeding, the quantity of the rubberized tape of forward and backward Resultant force is increased, according to step 1) and 2) recalculate the load value of the forward and backward Resultant force of each rib of forward and backward Resultant force and each operating mode；
4) Error Calculation, according to 1) in step before each rib, before the special lever of rear Resultant force and each rib of composition, the position of the rubberized tape of rear Resultant force, before quantity can calculate each rubberized tape load value and each rib, the ratio of the maximum bearing value of rear Resultant force, thus ratio can before each rib of each operating mode of Extrapolation, rear Resultant force is in the load of every piece of rubberized tape, then according to rubberized tape position, the aerodynamic loading of each rib and the inertial load pressure heart after the LOAD FOR load-transfer mechanism of rubberized tape, the heart is pressed to contrast with the aerodynamic loading of each rib finite element node and inertial load respectively, calculate whether error amount meets load-transfer mechanism process error.
Data verification part includes file read-write, logical judgment and basic mathematical calculate, mainly completing work is that finite element coordinate file and finite element load file are merged process, calculate load value and the moment of each each rib of operating mode, the full payload of each condition calculating and moment and test mission book load are contrasted, it is ensured that test load is errorless.
Data process the full payload and the moment that need to call each rib above calculated, then its equivalence of the principle of equal effects front and back load(ing) point to this rib of power is utilized, lever ratio according to front and back load(ing) point calculates the load value of each piece of rubberized tape, and assumed (specified) load has processed rear and raw payload error amount.
Claims (1)
1. the long straight wing load processing method of two-beam type, it is characterised in that comprise the following steps:
1) according to the finite element node serial number of each rib of wing and position, rubberized tape is arranged in each rib front-axle beam and back rest property selected around, every piece of rubberized tape load value is the maximum load value that rubberized tape can bear, then front-axle beam is calculated respectively according to each rib front-axle beam and back rest rubberized tape position and rubberized tape load value, the load value that the lever ending coordinates of the back rest and lever system thereof can bear, this load value is the maximum bearing value of its lever system, each rib front-axle beam, the lever ending coordinates of the back rest is this rib anterior resultant force point respectively, rear Resultant force, before, the lever system of rear Resultant force is referred to as special lever；
2) aerodynamic loading of each rib finite element node and the inertial load pressure heart are located approximately on this straight line that the forward and backward Resultant force of this rib is determined, according to 1) the forward and backward Resultant force determined, the principle of equal effects according to power, by the aerodynamic loading of every kind of each rib of operating mode and inertial load equivalence to the forward and backward Resultant force of this rib, the load value of the forward and backward Resultant force of each rib of each operating mode can be obtained；
3) checking procedure, carry out screening the maximum load value that can obtain the forward and backward Resultant force of each rib to the load value of the forward and backward Resultant force of each rib of all operating modes, check whether this load value exceedes the maximum bearing value of lever system, if exceeding, the quantity of the rubberized tape of forward and backward Resultant force is increased, according to step 1) and 2) recalculate the load value of the forward and backward Resultant force of each rib of forward and backward Resultant force and each operating mode；
4) Error Calculation, according to 1) in step before each rib, before the special lever of rear Resultant force and each rib of composition, the position of the rubberized tape of rear Resultant force, before quantity can calculate each rubberized tape load value and each rib, the ratio of the maximum bearing value of rear Resultant force, thus before each rib of each operating mode of ratio Extrapolation, rear Resultant force is in the load of every piece of rubberized tape, then according to rubberized tape position, the aerodynamic loading of each rib and the inertial load pressure heart after the LOAD FOR load-transfer mechanism of rubberized tape, the heart is pressed to contrast with the aerodynamic loading of each rib finite element node and inertial load respectively, calculate whether error amount meets load-transfer mechanism process error.
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Cited By (5)
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| CN107038296A (en) * | 2017-04-06 | 2017-08-11 | 深圳数设科技有限公司 | The method and apparatus that finite element point load is distributed in a kind of determination plane airfoil |
| 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 |
| CN109490114A (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 full scale fatigue test wing flap load loading method |
| 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 |
| CN112109919A (en) * | 2020-04-30 | 2020-12-22 | 中国飞机强度研究所 | Strength test loading point layout method |
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| 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 |
| CN109490114A (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 full scale fatigue test wing flap load loading method |
| 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 |
| 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 |
| CN112109919A (en) * | 2020-04-30 | 2020-12-22 | 中国飞机强度研究所 | Strength test loading point layout 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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