CN108108521A - A kind of method for obtaining the aircraft structure fatigue service life - Google Patents
A kind of method for obtaining the aircraft structure fatigue service life Download PDFInfo
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- CN108108521A CN108108521A CN201711229740.2A CN201711229740A CN108108521A CN 108108521 A CN108108521 A CN 108108521A CN 201711229740 A CN201711229740 A CN 201711229740A CN 108108521 A CN108108521 A CN 108108521A
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- 238000000034 method Methods 0.000 title claims abstract description 14
- 238000004458 analytical method Methods 0.000 abstract description 10
- 238000013461 design Methods 0.000 abstract description 6
- 238000013178 mathematical model Methods 0.000 abstract description 2
- 238000012795 verification Methods 0.000 abstract description 2
- 238000001228 spectrum Methods 0.000 description 6
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007619 statistical method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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- 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
- G06F2119/04—Ageing analysis or optimisation against ageing
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- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
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- Pure & Applied Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a kind of methods for obtaining the aircraft structure fatigue service life.The method for obtaining the aircraft structure fatigue service life includes the following steps：Step 1：Obtain fatigue quality index and SeqParameter；Step 2：The aircraft structure fatigue service life is obtained by formula.The method in the acquisition aircraft structure fatigue service life of the application, so as to quickly realize that airplane in transportation category structural fatigue is analyzed, obtains the aircraft structure fatigue service life by introducing fatigue quality index.By constructing new mathematical model, on the basis of similar model fatigue life verification experience, using a small amount of input condition, rapid fatigue analysis is completed in the Aircraft Conceptual Design stage for the aircraft structure fatigue analysis method of the application.
Description
Technical Field
The invention relates to the technical field of airplane structure fatigue, in particular to a method for obtaining the fatigue life of an airplane structure.
Background
The common metal structure fatigue life evaluation method is established on the basis of a complete and systematic S-N curve test, and the fatigue analysis flow is as follows: firstly, compiling a design load spectrum, then determining a typical fatigue load condition, establishing a finite element analysis model, determining the detail stress corresponding to the typical load condition according to the typical load condition characteristics of a key part, compiling a corresponding stress spectrum, then selecting a proper analysis method to carry out fatigue analysis, and verifying whether the structural design meets the design requirements. Based on the above, the structure is improved.
The conventional method has problems in that the analysis period is long and the required input conditions are sufficient.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present invention to provide a method of obtaining fatigue life for an aircraft structure that overcomes or at least mitigates at least one of the above-mentioned disadvantages of the prior art.
In order to achieve the above object, the present invention provides a method for obtaining the fatigue life of an aircraft structure, which comprises the following steps:
step 1: obtaining fatigue quality index and SeqA parameter;
step 2: by the formulaAnd obtaining the fatigue life of the airplane structure.
According to the method for obtaining the fatigue life of the airplane structure, the fatigue quality index is introduced, so that the fatigue analysis of the transportation airplane structure can be rapidly realized, and the fatigue life of the airplane structure is obtained. According to the airplane structure fatigue analysis method, a new mathematical model is constructed, and quick fatigue analysis is completed in the airplane scheme design stage by adopting a small number of input conditions on the basis of similar airplane type fatigue life verification experience.
Drawings
Fig. 1 is a schematic flow chart of a method for obtaining fatigue life of an aircraft structure according to an embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. 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. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
Fig. 1 is a schematic flow chart of a method for obtaining fatigue life of an aircraft structure according to an embodiment of the present application.
The method for obtaining the fatigue life of the aircraft structure as shown in fig. 1 comprises the following steps:
step 1: obtaining fatigue quality index and SeqA parameter;
step 2: by the formulaAnd obtaining the fatigue life of the airplane structure.
SeqComprises the following steps: for any given structural fatigue load spectrum, the damage equivalent of the fatigue load spectrum in the whole life can be converted into the stress ratio of 0.1 according to the equal damage conversion principle, and the maximum stress is Seq＝SmaxOne loading cycle of (D represents damage):
Seq＝(∑i(((1-Ri)/0.9)q·Smaxi)p)1/p(ii) a Wherein,
Ristress ratio for the ith load cycle in the fatigue load spectrum, SmaxiFor the maximum stress of the ith load cycle in the fatigue load spectrum, p and q are material constants, and for the aluminum alloy structure, p is 4.5, and q is 0.6.
IQF value definition: fatigue mass index, i.e. the stress ratio of the aircraft structure under cyclic loading of 0.1 constant amplitudeCan be up to 105And in the design stage of the airplane scheme, the fatigue quality index of the similar structure details can be obtained by carrying out statistical analysis on the structure detail conditions of the similar airplane models.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (1)
1. A method of deriving fatigue life for an aircraft structure, the method comprising the steps of:
step 1: obtaining fatigue quality index and SeqA parameter;
step 2: by the formulaAnd obtaining the fatigue life of the airplane structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711229740.2A CN108108521A (en) | 2017-11-29 | 2017-11-29 | A kind of method for obtaining the aircraft structure fatigue service life |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711229740.2A CN108108521A (en) | 2017-11-29 | 2017-11-29 | A kind of method for obtaining the aircraft structure fatigue service life |
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| Publication Number | Publication Date |
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| CN108108521A true CN108108521A (en) | 2018-06-01 |
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| CN201711229740.2A Pending CN108108521A (en) | 2017-11-29 | 2017-11-29 | A kind of method for obtaining the aircraft structure fatigue service life |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109033709A (en) * | 2018-08-30 | 2018-12-18 | 电子科技大学 | Predict Fatigue Life of Components appraisal procedure based on nonlinear fatigue damage accumulation theory |
| CN112035960A (en) * | 2020-09-02 | 2020-12-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for verifying influence of assembly stress on fatigue life of structure |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102184326A (en) * | 2011-05-04 | 2011-09-14 | 中国航空工业集团公司西安飞机设计研究所 | Method for estimating calendar life of aircraft structure |
| CN103344515A (en) * | 2013-07-05 | 2013-10-09 | 北京航空航天大学 | Damage calculation method for low-cycle fatigue and high-strength impact coupling based on local stress strain method |
| CN103530486A (en) * | 2013-11-05 | 2014-01-22 | 中国航空工业集团公司西安飞机设计研究所 | Method for designing fatigue life of aircraft bolts |
-
2017
- 2017-11-29 CN CN201711229740.2A patent/CN108108521A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102184326A (en) * | 2011-05-04 | 2011-09-14 | 中国航空工业集团公司西安飞机设计研究所 | Method for estimating calendar life of aircraft structure |
| CN103344515A (en) * | 2013-07-05 | 2013-10-09 | 北京航空航天大学 | Damage calculation method for low-cycle fatigue and high-strength impact coupling based on local stress strain method |
| CN103530486A (en) * | 2013-11-05 | 2014-01-22 | 中国航空工业集团公司西安飞机设计研究所 | Method for designing fatigue life of aircraft bolts |
Non-Patent Citations (2)
| Title |
|---|
| 董彦民 等: "军用飞机结构耐久性设计的细节疲劳额定值方法", 《航空学报》 * |
| 董登科 等: "飞机结构疲劳载荷谱加重系数与寿命之间的关系研究", 《机械强度》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109033709A (en) * | 2018-08-30 | 2018-12-18 | 电子科技大学 | Predict Fatigue Life of Components appraisal procedure based on nonlinear fatigue damage accumulation theory |
| CN109033709B (en) * | 2018-08-30 | 2020-03-31 | 电子科技大学 | Component fatigue life evaluation method based on nonlinear fatigue damage accumulation theory |
| CN112035960A (en) * | 2020-09-02 | 2020-12-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for verifying influence of assembly stress on fatigue life of structure |
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