CN109490116A - A kind of wing Plumb load method of full scale fatigue test - Google Patents
A kind of wing Plumb load method of full scale fatigue test Download PDFInfo
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- CN109490116A CN109490116A CN201811523819.0A CN201811523819A CN109490116A CN 109490116 A CN109490116 A CN 109490116A CN 201811523819 A CN201811523819 A CN 201811523819A CN 109490116 A CN109490116 A CN 109490116A
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- wing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
Abstract
The invention belongs to aviation fatigue test fields, and in particular to a kind of wing Plumb load method of full scale fatigue test, method of the invention pushes the heart by multiple-loading cases and is weighted processing according to damage weight, so that it is determined that load pressurized strut position；Full scale fatigue test wing Plumb load design method proposed by the invention, it is to be obtained under the premise of shearing, moment of flexure, torque and the design load situation error for meeting wing and respectively controlling section are met the requirements, can be widely applied to the design of various aircraft full scale fatigue test wing Plumb load points.
Description
Technical field
The invention belongs to aviation fatigue test field, especially relate to a kind of full scale fatigue test wing it is vertical plus
Support method.
Background technique
Aircraft full scale fatigue test is the key link that aircraft determines the longevity, be related to fatigue load operating condition is more, test duration week
Phase is long, often up to the several years even more than ten years.It is different from test of static strength, fatigue test is during development, in order to protect
Confirmatory test progress is generally tested only with a set of loading system and fixture, and will not be carried out according to different operating conditions in testing
It changes the outfit.Thus the problem of bringing is that a set of loading system is difficult to meet the loading accuracy requirement of most of load working conditions, caused by
Error is larger.And wing is the critical component of aircraft carrying, bears the aircraft vertical load of the overwhelming majority, such as it cannot be guaranteed that missing
Difference will bring the distortion of experiment examination result, determines the longevity to wing structure fatigue or even full machine fatigue determines the longevity and brings large error, pass through
Ji property is poor.Existing specification, document just do not provide effective design method and hang down for carrying out full scale fatigue test wing
To designing load.Meanwhile the cloth of loading system often empirically or with personal preference is carried out when carrying out test designing load
It sets, random larger, error is larger and uncontrollable.
Summary of the invention
The purpose of the present invention is: when in order to solve full scale fatigue test wing Plumb load, lack effective set
The technical issues of meter method, provide it is a kind of based on multiple load working conditions weight pressure the heart full scale fatigue test wing it is vertical plus
Support method.
To solve this technical problem, the technical scheme is that
A kind of wing Plumb load method of full scale fatigue test, it is characterised in that: the full scale fatigue test
Wing Plumb load method be given by multiple-loading cases push the heart according to damage weight be weighted processing, so that it is determined that plus
Carry the loading method of pressurized strut position.
The wing Plumb load method of the full scale fatigue test the following steps are included:
Step 1: being required according to experiment examination, wing is divided into several examination sections by rib, provides each examination section
Shearing, moment of flexure, torque error requirement；
Step 2: successively calculating and being designed between each control section from wing tip to wing root according to examination section dividing condition
Load presses heart coordinate and its shearing, moment of flexure, torque to control section；
Step 3: finding out weighting pressure heart position after determining according to damage weight relationship；
Step 4: pressing heart position by the weighting that previous step determines, according to load(ing) point arrangement principle, weighting pressure heart position is found out
Corresponding initial loading point position；
Step 5: calculating load point load to shearing, moment of flexure, the torque of control section, and carry with being distributed under design conditions
Lotus carries out error comparison to the shearing of control section, moment of flexure, torque arithmetic result；
Step 6: when shearing, moment of flexure, torque are unsatisfactory for control errors requirement, the load point of adjustment front-axle beam, the back rest
It sets, repeats step 5, iterative calculation is until all loading Positions meet control errors requirement.
In the step one divide examination section foundation for according to the quantity of rib divide examination section, 3-4 rib away from
As an examination section.Not only the continuity of load transmission had been guaranteed, but also has guaranteed that pressurized strut quantity will not be made excessively to increase cost
And test period.
The condition that error requirements meet in the step one are as follows: it is 0 that root rib, which requires shearing, moment of flexure, the error of torque,.This
The purpose of sample is the accuracy in order to guarantee wing loads transmitting.
The step three specifically: according to operating condition each in loading spectrum damage weight relationship, the ratio always damaged according to Zhan,
Different weight coefficients is arranged to the pressure heart of each load working condition, presses heart position so as to find out weighting.
Load(ing) point arrangement principle described in step 4 are as follows: loading Position is arranged in front-axle beam, the back rest and siding junction
Principle.The substantivity of Path of Force Transfer was not only guaranteed according to this principle, but also has guaranteed that structure will not be destroyed.
The beneficial effects of the present invention are:
The invention proposes a kind of wing Plumb load methods of full scale fatigue test.Method proposed by the invention,
It is to be obtained under the premise of shearing, moment of flexure, torque and the design load situation error for meeting wing and respectively controlling section are met the requirements
, not only while guarantee test load precision, but also the scale of effectively control pressurized strut, it can largely save experimentation cost and shorten examination
Test the period.Method proposed by the invention overcomes often empirically or with individual to be liked when carrying out test designing load at present
The problem that the error of the arrangement of progress loading system is uncontrollable well, randomness is larger, it is full-scale to can be widely applied to various aircrafts
The design of fatigue test wing Plumb load point.
Detailed description of the invention
Fig. 1 is the flow chart of the wing Plumb load design method of full scale fatigue test；
Fig. 2 is that wing respectively controls section and final loading Position distribution schematic diagram；
Fig. 3 is that each load working condition presses heart position, weighting pressure heart position and initial loading point；
Fig. 4 is the shearing contrast schematic diagram that 1g equals winged design conditions and test situation；
Fig. 5 is the moment of flexure contrast schematic diagram that 1g equals winged design conditions and test situation.
Specific embodiment
The present invention will be further described with reference to the accompanying drawings and examples:
As shown in Figure 1, the flow chart of the wing Plumb load design method for full scale fatigue test.Give embodiment
In the parameter used.Specific step is as follows:
Step 1: being required according to experiment examination, wing shown in Fig. 2 is divided into 5 examination sections by rib, respectively examines section
Respectively 3 ribs, 7 ribs, 10 ribs, 13 ribs and 16 ribs.Requirement shears at outer 3 rib of wing root rib, the error of moment of flexure is 0, to guarantee wing
The accuracy of load transmission；The shearing of remaining each examination section, moment of flexure error requirements are respectively to shear 3%, moment of flexure 2%.Examination
Section divides is generally 3-4 rib, and rib will lead to that loading error is big, and rib has lacked the more pressurized strut of needs, experimentation cost and
Period will lengthen.
Step 2: successively calculating and being designed between each control section from wing tip to wing root according to examination section dividing condition
Load presses heart coordinate and its shearing, moment of flexure, torque to control section.
According to examination section dividing condition, from wing tip to wing root, the pressure of design load between each control section is successively found out
The heart (total load, total square) coordinate, by taking the design load between 13-16 rib as an example, calculating provides pressure heart distribution and sees Fig. 2, and with 1g
For flat winged operating condition, provides design load and Fig. 3, Fig. 4 are shown in the shearing of control section, moment of flexure, specific to 1g operating condition to 13 ribs
Shear value is 153300N, and moment is -1.16051E+09N.mm, moment of flexure be negative be represented as it is curved on wing；
Step 3: finding out weighting pressure heart position after determining according to damage weight relationship.
According to the distribution situation of damage regime in loading spectrum, it is arranged not by the pressure heart of the relative damage size to each load working condition
Same weight coefficient, provides the biggish Part load of weight coefficient and corresponding weight coefficient is shown in Table 1, finds out weighting pressure heart position
It sets, sees Fig. 2.
The corresponding weighting coefficient of 1 Part load of table
| Operating condition number | Weighting coefficient | Operating condition number | Weighting coefficient | Operating condition number | Weighting coefficient |
| 1 | 3.0338E-02 | 11 | 2.2219E-02 | 21 | 1.8194E-02 |
| 2 | 2.7431E-02 | 12 | 2.0844E-02 | 22 | 1.8123E-02 |
| 3 | 2.7334E-02 | 13 | 2.0362E-02 | 23 | 1.7552E-02 |
| 4 | 2.5858E-02 | 14 | 1.9651E-02 | 24 | 1.7547E-02 |
| 5 | 2.5371E-02 | 15 | 1.9648E-02 | 25 | 1.6674E-02 |
| 6 | 2.3855E-02 | 16 | 1.9641E-02 | 26 | 1.6647E-02 |
| 7 | 2.3674E-02 | 17 | 1.8827E-02 | 27 | 1.6498E-02 |
| 8 | 2.3156E-02 | 18 | 1.8770E-02 | 28 | 1.6366E-02 |
| 9 | 2.3100E-02 | 19 | 1.8752E-02 | 29 | 1.6321E-02 |
| 10 | 2.2516E-02 | 20 | 1.8706E-02 | 30 | 1.6079E-02 |
Step 4: pressing heart position by the weighting that previous step determines, according to load(ing) point arrangement principle, weighting pressure heart position is found out
Fig. 2 is seen in corresponding initial loading point position；The substantivity of Path of Force Transfer was not only guaranteed according to this principle, but also has guaranteed that knot will not be destroyed
Structure.
Step 5: calculating load point load to shearing, moment of flexure, the torque of control section, and carry with being distributed under design conditions
Lotus carries out error comparison to the shearing of control section, moment of flexure, torque arithmetic result and sees Fig. 3, Fig. 4.
1g operating condition is 157778N to the shear value of 13 ribs under trystate, and moment is -1.17131E+09N.mm, moment of flexure
Being negative, it is curved on wing to be represented as.It is compared with design conditions, shearing error is 2.92%, moment of flexure error is 0.93%.Meet error
It is required that.
Step 6: iterative calculation meets control errors requirement up to all loading Positions, determine that final load(ing) point is shown in figure
2。
Claims (5)
1. a kind of wing Plumb load method of full scale fatigue test, it is characterised in that: the full scale fatigue test
Wing Plumb load method is given by the multiple-loading cases pushing heart and is weighted processing according to damage weight, so that it is determined that load
The loading method of pressurized strut position, comprising the following steps:
Step 1: being required according to experiment examination, wing is divided into several examination sections by rib, provides cutting for each examination section
Power, moment of flexure, torque error requirement；
Step 2: successively calculating design load between each control section from wing tip to wing root according to examination section dividing condition
Pressure heart coordinate and its to the control shearing of section, moment of flexure；
Step 3: finding out weighting pressure heart position after determining according to damage weight relationship；
Step 4: pressing heart position by the weighting that previous step determines, according to load(ing) point arrangement principle, it is corresponding to find out weighting pressure heart position
Initial loading point position；
Step 5: calculating the shearing loaded point load to control section, moment of flexure, and control is cut with distributed load under design conditions
The shearing in face, calculation of Bending Moment result carry out error comparison；
Step 6: when shearing, moment of flexure are unsatisfactory for control errors requirement, the loading Position of adjustment front-axle beam, the back rest repeats step
Five, iterative calculation is until all loading Positions meet control errors requirement.
2. the wing Plumb load method of full scale fatigue test according to claim 1, it is characterised in that: the step
The foundation of examination section is divided in rapid one to divide examination section according to the quantity of rib, 3-4 rib is away from as an examination section.
3. the wing Plumb load method of full scale fatigue test according to claim 1, it is characterised in that: the step
The condition that error requirements meet in rapid one are as follows: root rib requires shearing, the error of moment of flexure is 0.
4. the wing Plumb load method of full scale fatigue test according to claim 1, it is characterised in that: the step
Rapid three specifically:
Weight relationship is damaged according to operating condition each in loading spectrum, the pressure heart of each load working condition is arranged in the ratio always damaged according to Zhan
Different weight coefficients presses heart position so as to find out weighting.
5. the wing Plumb load method of full scale fatigue test according to claim 1, it is characterised in that: in step 4
The load(ing) point arrangement principle are as follows: loading Position is arranged in the principle of front-axle beam, the back rest and siding junction.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109977556A (en) * | 2019-03-28 | 2019-07-05 | 中国飞机强度研究所 | Load-optimised method based on least square method |
| CN111122346A (en) * | 2019-12-24 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Test load processing method for main structure of airfoil |
| CN111422375A (en) * | 2020-04-15 | 2020-07-17 | 中国飞机强度研究所 | Active control method and system for load of vertical constraint point of airplane |
| CN112158359A (en) * | 2020-10-12 | 2021-01-01 | 中国地质大学（北京） | Method for detecting fatigue fracture of wing |
| CN113378293A (en) * | 2021-05-19 | 2021-09-10 | 中航西安飞机工业集团股份有限公司 | Method for determining severe load design condition of wing box of airplane wing |
| CN113654916A (en) * | 2021-09-03 | 2021-11-16 | 哈尔滨工程大学 | Box beam ultimate strength test device and test method |
| CN113704876A (en) * | 2021-08-05 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | 3D combined screening method for airfoil surface load |
| CN113720707A (en) * | 2021-08-23 | 2021-11-30 | 中国飞机强度研究所 | Design method for large-deformation loading point of structural fatigue test |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109977556A (en) * | 2019-03-28 | 2019-07-05 | 中国飞机强度研究所 | Load-optimised method based on least square method |
| CN109977556B (en) * | 2019-03-28 | 2023-04-07 | 中国飞机强度研究所 | Load optimization method based on least square method |
| CN111122346B (en) * | 2019-12-24 | 2022-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Test load processing method for main structure of airfoil |
| CN111122346A (en) * | 2019-12-24 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Test load processing method for main structure of airfoil |
| CN111422375A (en) * | 2020-04-15 | 2020-07-17 | 中国飞机强度研究所 | Active control method and system for load of vertical constraint point of airplane |
| CN112158359A (en) * | 2020-10-12 | 2021-01-01 | 中国地质大学（北京） | Method for detecting fatigue fracture of wing |
| CN112158359B (en) * | 2020-10-12 | 2022-01-04 | 中国地质大学（北京） | Method for detecting fatigue fracture of wing |
| CN113378293A (en) * | 2021-05-19 | 2021-09-10 | 中航西安飞机工业集团股份有限公司 | Method for determining severe load design condition of wing box of airplane wing |
| CN113378293B (en) * | 2021-05-19 | 2023-12-22 | 中航西安飞机工业集团股份有限公司 | Method for determining serious load design condition of wing box of airplane |
| CN113704876A (en) * | 2021-08-05 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | 3D combined screening method for airfoil surface load |
| CN113704876B (en) * | 2021-08-05 | 2023-06-02 | 中国航空工业集团公司沈阳飞机设计研究所 | 3D combined screening method for airfoil load |
| CN113720707A (en) * | 2021-08-23 | 2021-11-30 | 中国飞机强度研究所 | Design method for large-deformation loading point of structural fatigue test |
| CN113720707B (en) * | 2021-08-23 | 2023-09-05 | 中国飞机强度研究所 | Design method for large deformation loading point of structural fatigue test |
| CN113654916A (en) * | 2021-09-03 | 2021-11-16 | 哈尔滨工程大学 | Box beam ultimate strength test device and test method |
| CN113654916B (en) * | 2021-09-03 | 2023-09-12 | 哈尔滨工程大学 | Box girder ultimate strength test device and test method |
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Application publication date: 20190319 |