CN105109705A - Method for calculating rigidity of aircraft airfoil surface structure - Google Patents
Method for calculating rigidity of aircraft airfoil surface structure Download PDFInfo
- Publication number
- CN105109705A CN105109705A CN201510464833.8A CN201510464833A CN105109705A CN 105109705 A CN105109705 A CN 105109705A CN 201510464833 A CN201510464833 A CN 201510464833A CN 105109705 A CN105109705 A CN 105109705A
- Authority
- CN
- China
- Prior art keywords
- tangent plane
- rigidity
- finite element
- element analysis
- stiffness
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention discloses a method for calculating the rigidity of an aircraft airfoil surface structure. The method includes the steps that an airfoil-surface-structure finite element analysis model is built, wherein the airfoil-surface-structure finite element analysis model should be corrected through a static test and can really simulate the rigidity of the structure; sections of the root are restrained in the finite element analysis model, and then finite element analysis is carried out; the torsional rigidity of the structure is reversely derived through torsional deformation of the sections, and then the rigidity center positions of the sections are determined through a torsional rigidity calculation formula; and when the bending rigidity of the structure is calculated, small-deformation assumption is adopted, the finite element analysis is fitted to obtain displacement at the rigidity centers of the sections, a structure bending rigidity calculation formula is obtained accordingly, and the rigidity, the rigidity center positions and the bending rigidity of the aircraft airfoil surface structure are rapidly and accurately calculated through the structure bending rigidity calculation formula. In this way, the rigidity, the rigidity center positions and the bending rigidity of the aircraft airfoil surface structure are rapidly and accurately calculated; and in addition, experiments in aircrafts in multiple types verify that the algorithm is correct in principle, easy and convenient to implement and capable of meeting the aircraft designing requirement.
Description
Technical field
The present invention relates to aircraft stiffness structure technical field, particularly relate to a kind of plane airfoil Calculation of Structure Stiffness method.
Background technology
Aeroplane structure design not only will meet requirement of strength, and will consider rigidity requirement; And aeroperformance desired during in order to ensure that aircraft has a design, require that airfoil structure need have enough global stiffnesses, such as, apart from the section torsional deflection of wing root a distance, do not allow to exceed certain limited angular, aerofoil amount of deflection should not exceed permissible value.Meanwhile, also have same requirement, particularly high-speed aircraft for local stiffness, the deformation of unevenness of aerofoil surface will have a strong impact on aircraft aerodynamic characteristic.Propose rigidity requirement and do not mean that it is all under any circumstance that rigidity is the bigger the better, particularly local stiffness, sometimes just the opposite, needing to reduce the rigidity of structure.
Therefore when carrying out plane airfoil structure design, should using stiffness index as one of constraint condition, by multiple constraint method of designing project organization.But at present, plane airfoil Calculation of Structure Stiffness does not have the comparatively ripe and method of practicality, substantially all Engineering Algorithm is adopted, according to version and size, the torsional stiffness of computation structure, just heart position and bending stiffness, but due to the airfoil structure more complicated of present generation aircraft, closed chamber is more and irregular, employing Engineering Algorithm calculates, and not only work capacity is comparatively large, and designs simplification process easily produces larger error.
Summary of the invention
Technical matters solved by the invention is to provide a kind of plane airfoil Calculation of Structure Stiffness method, to solve the shortcoming in above-mentioned background technology.
Technical matters solved by the invention realizes by the following technical solutions:
A kind of plane airfoil Calculation of Structure Stiffness method, first airfoil structure finite element analysis model is set up, model should through static test correction and can the rigidity of real simulation structure, and in finite element analysis model, retrain root tangent plane, then carry out finite element analysis, utilize the torsional deflection of each tangent plane, the torsional stiffness of anti-pushing-out structure, then by the firm heart position of torsional stiffness computing formula determination tangent plane; When computation structure bending stiffness, adopt small deformation hypothesis, matching finite element analysis obtains the firm heart place displacement of each tangent plane, thus obtains structural bending stiffness calculation formula, quick and precisely calculates the plane airfoil rigidity of structure, just heart position and bending stiffness with this; Concrete steps are as follows:
1) torsional stiffness calculates
Wingtip tangent plane applies the concentrated force that a pair equal and opposite in direction, direction are contrary
, to obtain the moment of torsion of each tangent plane, then obtain structural distortion state by finite element analysis, then utilize the torsional deflection of each tangent plane, the torsional stiffness of anti-pushing-out structure;
1. segmentation calculates the torsional stiffness of each tangent plane, and the formula of torsional deflection is:
;
Can draw:
;
Wherein:
---tangent plane moment of torsion,
---the distance between two tangent planes,
---tangent plane torsional stiffness,
---tangent plane twist angle;
2. the twist angle of the n-th tangent plane in finite element analysis model:
Torsional stiffness then between two tangent planes is:
,
;
Wherein:
---the displacement of tangent plane I point,
---the displacement of tangent plane J point,
---the distance between I point and J point;
2) firm heart position calculation
The firm heart position of tangent plane is in the amount of deflection of structural profile
place, is calculated the displacement of trying to achieve each point on section, obtains the displacement of I, J 2 by torsional stiffness
with
, the distance between known I, J 2
, again because firm heart position O between I, J, must can be obtained at 2 thus in firm heart position;
3) bending stiffness calculates
At the wingtip tangent plane of finite element analysis model, firm heart place adds a concentrated force
, according to small deformation hypothesis, sag curve has relational expression below:
;
From Finite element analysis results, take out the displacement of each point on the firm heart line of structure, simulate three (or more than three times) deflection curve equations:
;
And it is right
twice differentiate:
;
Then structure tangent plane bending stiffness:
;
The plane airfoil rigidity of structure, just heart position and bending stiffness quick and precisely can be calculated according to above-mentioned steps.
Beneficial effect: the present invention, by setting up airfoil structure finite element analysis model and incorporation engineering algorithm, utilizes the torsional deflection of each tangent plane, the torsional stiffness of anti-pushing-out structure, then by the firm heart position of torsional stiffness computing formula determination tangent plane; Small deformation hypothesis is adopted when computation structure bending stiffness, matching finite element analysis obtains the firm heart place displacement of each tangent plane, thus obtain structural bending stiffness calculation formula, the plane airfoil rigidity of structure, just heart position and bending stiffness is quick and precisely calculated with this, and through many types of aircraft experimental verification, this algorithm principle is correct, be easy to implement, and can meet airplane design requirement.
Accompanying drawing explanation
Fig. 1 is aerofoil structure of finite element analysis model schematic diagram in preferred embodiment of the present invention.
Fig. 2 is that the torsional stiffness in preferred embodiment of the present invention calculates tangent plane schematic diagram.
Fig. 3 is the firm heart position view in preferred embodiment of the present invention.
Detailed description of the invention
The technological means realized to make the present invention, creation characteristic, reaching object and effect is easy to understand, below in conjunction with concrete diagram, setting forth the present invention further.
A kind of plane airfoil Calculation of Structure Stiffness method, first airfoil structure finite element analysis model is set up, model should through static test correction and can the rigidity of real simulation structure, finite element analysis model is shown in Figure 1, be provided with 7 rib tangent planes, root tangent plane is retrained in finite element analysis model, wherein front wall root constraint Y-direction displacement U2=0, girder root constraint X to, Y-direction, Z-direction displacement U1=U2=U3=0, back rest constraint Y-direction, Z-direction displacement U2=U3=0, carry out finite element analysis, utilize the torsional deflection of each tangent plane, the torsional stiffness of anti-pushing-out structure, again by the firm heart position of torsional stiffness computing formula determination tangent plane, and when computation structure bending stiffness, adopt small deformation hypothesis, matching finite element analysis obtains the firm heart place displacement of each tangent plane, thus obtains structural bending stiffness calculation formula, quick and precisely calculates the plane airfoil rigidity of structure, just heart position and bending stiffness with this, concrete steps are as follows:
1) torsional stiffness calculates
Wingtip tangent plane applies the concentrated force that a pair equal and opposite in direction, direction are contrary
=10000N, to obtain the moment of torsion of each tangent plane, then obtains structural distortion state by finite element analysis, then utilizes the torsional deflection of each tangent plane, the torsional stiffness of anti-pushing-out structure, and torsional stiffness calculates sectional drawing, shown in Figure 2;
1. segmentation calculates the torsional stiffness of each tangent plane, and the formula of torsional deflection is:
;
Can draw:
;
Wherein:
---tangent plane moment of torsion,
---the distance between two tangent planes,
---tangent plane torsional stiffness,
---tangent plane twist angle;
2. the twist angle of the n-th tangent plane in finite element analysis model:
Torsional stiffness then between two tangent planes is:
,
;
Wherein:
---the displacement of tangent plane I point,
---the displacement of tangent plane J point,
---tangent plane I point and J dot spacing from;
2) firm heart position calculation
The firm heart position of tangent plane is in the amount of deflection of structural profile
place, is calculated the displacement of trying to achieve each point on section, obtains the displacement of I, J 2 by torsional stiffness
with
, the distance between known I, J 2
, again because firm heart position O between I, J, must can be obtained at 2 thus in firm heart position, shown in Figure 3;
3) bending stiffness calculates
At the wingtip tangent plane of finite element analysis model, firm heart place adds a concentrated force
, according to small deformation hypothesis, sag curve has relational expression below:
;
From Finite element analysis results, take out the displacement of each point on the firm heart line of structure, simulate three (or more than three times) deflection curve equations:
;
And it is right
twice differentiate:
;
Then structure tangent plane bending stiffness:
;
Quick and precisely can calculate the plane airfoil rigidity of structure, just heart position and bending stiffness according to above-mentioned steps, and through many types of aircraft experimental verification, this algorithm principle is correct, be easy to implement, airplane design requirement can be met.
More than show and describe groundwork of the present invention and principal character and advantage of the present invention.The technical personnel of the industry should be understood; the present invention is not restricted to the described embodiments; what describe in above-described embodiment and specification sheets just illustrates principle of the present invention; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications, and these changes and improvements all fall in the claimed scope of the invention.Application claims protection domain defines > by appending claims and equivalent thereof.
Claims (2)
1. a plane airfoil Calculation of Structure Stiffness method, it is characterized in that, first airfoil structure finite element analysis model is set up, model should through static test correction and can the rigidity of real simulation structure, and in finite element analysis model, retrain root tangent plane, then carry out finite element analysis, utilize the torsional deflection of each tangent plane, the torsional stiffness of anti-pushing-out structure, then by the firm heart position of torsional stiffness computing formula determination tangent plane; When computation structure bending stiffness, adopt small deformation hypothesis, matching finite element analysis obtains the firm heart place displacement of each tangent plane, thus obtains structural bending stiffness calculation formula, quick and precisely calculates the plane airfoil rigidity of structure, just heart position and bending stiffness with this.
2. a kind of plane airfoil Calculation of Structure Stiffness method according to claim 1, is characterized in that,
Concrete steps are as follows:
1) torsional stiffness calculates
Wingtip tangent plane applies the concentrated force that a pair equal and opposite in direction, direction are contrary
, to obtain the moment of torsion of each tangent plane, then obtain structural distortion state by finite element analysis, then utilize the torsional deflection of each tangent plane, the torsional stiffness of anti-pushing-out structure;
1. segmentation calculates the torsional stiffness of each tangent plane, and the formula of torsional deflection is:
;
Can draw:
;
Wherein:
---tangent plane moment of torsion,
---the distance between two tangent planes,
---tangent plane torsional stiffness,
---tangent plane twist angle;
2. the twist angle of the n-th tangent plane in finite element analysis model:
Torsional stiffness then between two tangent planes is:
,
;
Wherein:
---the displacement of tangent plane I point,
---the displacement of tangent plane J point,
---the distance of tangent plane I point and J point;
2) firm heart position calculation
The firm heart position of tangent plane is in the amount of deflection of structural profile
place, is calculated the displacement of trying to achieve each point on section, obtains the displacement of I, J 2 by torsional stiffness
with
, the distance between known I, J 2
, again because firm heart position O between I, J, must can be obtained at 2 thus in firm heart position;
3) bending stiffness calculates
At the wingtip tangent plane of finite element analysis model, firm heart place adds a concentrated force
, according to small deformation hypothesis, sag curve has relational expression below:
;
From Finite element analysis results, take out the displacement of each point on the firm heart line of structure, simulate three (or more than three times) deflection curve equations:
;
And it is right
twice differentiate:
;
Then structure tangent plane bending stiffness:
.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510464833.8A CN105109705A (en) | 2015-08-03 | 2015-08-03 | Method for calculating rigidity of aircraft airfoil surface structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510464833.8A CN105109705A (en) | 2015-08-03 | 2015-08-03 | Method for calculating rigidity of aircraft airfoil surface structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105109705A true CN105109705A (en) | 2015-12-02 |
Family
ID=54657898
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510464833.8A Pending CN105109705A (en) | 2015-08-03 | 2015-08-03 | Method for calculating rigidity of aircraft airfoil surface structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105109705A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105823688A (en) * | 2016-05-16 | 2016-08-03 | 中国航空工业集团公司西安飞机设计研究所 | Airfoil leading edge curve surface structure bearing testing method |
| CN106021779A (en) * | 2016-05-31 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating bending rigidity of main box section of high-aspect-ratio wing |
| CN106697328A (en) * | 2016-12-15 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Same-material model experimental design method for load transfer characteristic of aircraft thin-wall structure |
| CN107356404A (en) * | 2017-07-13 | 2017-11-17 | 江西洪都航空工业集团有限责任公司 | A kind of plate member formula wing aerodynamic elasticity model in wind tunnel |
| CN107817081A (en) * | 2017-08-31 | 2018-03-20 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of canopy static testing pad Stiffness Distribution analogy method |
| CN108256214A (en) * | 2018-01-16 | 2018-07-06 | 滨州学院 | A kind of orthogonal stiffened panel calculating method of stiffness of aviation and device |
| CN108763739A (en) * | 2018-05-28 | 2018-11-06 | 四川腾盾科技有限公司 | A kind of computational methods of the rigid heart of Flight Vehicle Structure section |
| CN113051656A (en) * | 2019-12-26 | 2021-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Rigidity control method for high-lift device of airplane |
| CN113486552A (en) * | 2021-07-01 | 2021-10-08 | 江苏科技大学 | Unidirectional composite material bending stiffness prediction method |
-
2015
- 2015-08-03 CN CN201510464833.8A patent/CN105109705A/en active Pending
Non-Patent Citations (1)
| Title |
|---|
| 侯甲栋等: "大展弦比机翼剖面刚度分析", 《航空计算技术》 * |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105823688B (en) * | 2016-05-16 | 2019-01-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of bearing test method of aerofoil leading edge curved-surface structure |
| CN105823688A (en) * | 2016-05-16 | 2016-08-03 | 中国航空工业集团公司西安飞机设计研究所 | Airfoil leading edge curve surface structure bearing testing method |
| CN106021779A (en) * | 2016-05-31 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating bending rigidity of main box section of high-aspect-ratio wing |
| CN106021779B (en) * | 2016-05-31 | 2019-04-23 | 中国航空工业集团公司西安飞机设计研究所 | A kind of main box section bending stiffness calculation method of high aspect ratio wing |
| CN106697328A (en) * | 2016-12-15 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Same-material model experimental design method for load transfer characteristic of aircraft thin-wall structure |
| CN107356404A (en) * | 2017-07-13 | 2017-11-17 | 江西洪都航空工业集团有限责任公司 | A kind of plate member formula wing aerodynamic elasticity model in wind tunnel |
| CN107356404B (en) * | 2017-07-13 | 2019-11-12 | 江西洪都航空工业集团有限责任公司 | A kind of plate member formula wing aerodynamic elasticity model in wind tunnel |
| CN107817081A (en) * | 2017-08-31 | 2018-03-20 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of canopy static testing pad Stiffness Distribution analogy method |
| CN108256214A (en) * | 2018-01-16 | 2018-07-06 | 滨州学院 | A kind of orthogonal stiffened panel calculating method of stiffness of aviation and device |
| CN108256214B (en) * | 2018-01-16 | 2021-07-02 | 滨州学院 | Aviation orthogonal stiffened plate rigidity calculation method and device |
| CN108763739A (en) * | 2018-05-28 | 2018-11-06 | 四川腾盾科技有限公司 | A kind of computational methods of the rigid heart of Flight Vehicle Structure section |
| CN108763739B (en) * | 2018-05-28 | 2022-03-22 | 四川腾盾科技有限公司 | Method for calculating structural section rigid center of aircraft |
| CN113051656A (en) * | 2019-12-26 | 2021-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Rigidity control method for high-lift device of airplane |
| CN113051656B (en) * | 2019-12-26 | 2023-12-22 | 中国航空工业集团公司西安飞机设计研究所 | Rigidity control method for aircraft high lift device |
| CN113486552A (en) * | 2021-07-01 | 2021-10-08 | 江苏科技大学 | Unidirectional composite material bending stiffness prediction method |
| CN113486552B (en) * | 2021-07-01 | 2023-11-17 | 江苏科技大学 | Method for predicting bending stiffness of unidirectional composite material |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105109705A (en) | Method for calculating rigidity of aircraft airfoil surface structure | |
| CN104133926A (en) | Comprehensive analysis method of elastic aerodynamic force characteristic | |
| US11279469B2 (en) | Airplane wing | |
| CN105183996A (en) | Surface element correction and grid beforehand self-adaption calculation method | |
| Goates et al. | Practical implementation of a general numerical lifting-line method | |
| Ritter et al. | Static and dynamic aeroelastic validation of a flexible forward swept composite wing | |
| CN105046021A (en) | Non-linear optimization algorithm for rational approximation of unsteady aerodynamic minimum state | |
| Nishida | Fully simultaneous coupling of the full potential equation and the integral boundary layer equations in three dimensions | |
| Leifsson et al. | Aerodynamic design optimization: physics-based surrogate approaches for airfoil and wing design | |
| Boiko et al. | Numerical prediction of laminar-turbulent transition on an airfoil | |
| CN111551343B (en) | Design method for full-speed domain aerodynamic characteristic wind tunnel test of rocket with grid rudder | |
| Kier | An integrated flexible aircraft model for optimal control surface scheduling of manoeuvre load alleviation and wing shape control functions | |
| Kuzmina et al. | Analysis of static and dynamic aeroelastic characteristics of airplane in transonic flow | |
| Kier | An integrated loads analysis model for wake vortex encounters | |
| Moreno et al. | A modification to the enhanced correction factor technique to correlate with experimental data | |
| Wang et al. | Static aeroelastic analysis of flexible aircraft with large deformations | |
| Castrichini | Parametric Assessment of a Folding Wing-Tip Device for Aircraft Loads Alleviation | |
| Niksch et al. | Morphing Aircaft Dynamical Model: Longitudinal Shape Changes | |
| Rizzi | Euler solutions of transonic vortex flows around the Dillner wing | |
| Kier | Aerodynamic modelling for integrated loads analysis models | |
| Arizono et al. | Flutter simulations of a T‐tail configuration using non‐linear aerodynamics | |
| Ahmad et al. | Aeroelastic analysis of high aspect ratio wing in subsonic flow | |
| CN112464372B (en) | Design sensitivity engineering numerical method for control surface efficiency of aileron of elastic wing | |
| Guo et al. | Numerical Simulation Research on Static Aeroelastic Effect of the Transonic Aileron of a High Aspect Ratio Aircraft. | |
| Zhang et al. | Hybrid feedback design for subsonic and transonic airfoils and wings |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20151202 |
|
| RJ01 | Rejection of invention patent application after publication |