CN112711806B - Method for calculating buckling deformation of large-opening structure of rectangular thin-wall machine body - Google Patents
Method for calculating buckling deformation of large-opening structure of rectangular thin-wall machine body Download PDFInfo
- Publication number
- CN112711806B CN112711806B CN202011611928.5A CN202011611928A CN112711806B CN 112711806 B CN112711806 B CN 112711806B CN 202011611928 A CN202011611928 A CN 202011611928A CN 112711806 B CN112711806 B CN 112711806B
- Authority
- CN
- China
- Prior art keywords
- opening structure
- model
- buckling deformation
- point
- torsion
- 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.)
- Active
Links
Images
Classifications
-
- 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
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/28—Fuselage, exterior or interior
-
- 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
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computational Mathematics (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention discloses a method for calculating the buckling deformation of a large opening structure of a rectangular thin-wall machine body, which comprises the following steps: establishing a torsion model of the large opening of the machine body according to the shape and the size of the actual large opening structure of the machine body; calculating relevant parameters of the section characteristics of the torsion model of the large-opening structure of the fuselage, including the fanning area and the main fanning moment of inertia; under the action of torsional load, calculating torsional angles at different section positions; determining buckling deformation key points in the large-opening structure torsion model, then respectively calculating buckling deformation at each buckling deformation key point, and solving the buckling deformation of the whole large-opening structure. According to the invention, through deep research on a large opening structure at the lower part of a rectangular section fuselage of the airplane under a torsional load, an expression of the buckling deformation of the structure is obtained, key parameters influencing the buckling deformation are obtained, and theoretical support is provided for controlling the buckling deformation.
Description
Technical Field
The invention relates to the field of aviation structure design, and particularly provides a method for calculating the buckling deformation of a large-opening structure of a rectangular thin-wall fuselage, which can obtain sensitive parameters influencing the buckling deformation and provide support for controlling the buckling deformation.
Background
The large opening structure is generally a throwing opening at the lower part of the airplane body, a cargo compartment door mounting opening, a missile compartment door mounting opening and the like; the large opening structure cuts off the force transmission path of the airplane structure, which is a difficult point of airplane design. The conventional large opening of the circular fuselage is based on a small number of design references, while the rectangular opening is a special cabin opening, is a novel structural form, and lacks design experience in model design and introduction of the structure of the type in the design information of the airplane.
At present, parameters of structural arrangement are usually obtained through finite element calculation software optimization, but because the airplane body large opening is less in airplane design application at present, a method for calculating the buckling deformation of a rectangular thin-wall airplane body large opening structure is unavailable; for a large opening structure of the fuselage, if a traditional finite element calculation method is adopted, the type selection of model elements, the scale, boundary conditions and the like all influence the calculation result. The result of the finite element structure lacks theoretical support of analytic solution, key factors influencing the buckling deformation cannot be obtained, and powerful data support for controlling the buckling deformation is lacked.
Disclosure of Invention
The invention aims to provide a method for calculating the buckling deformation of a large-opening structure of a rectangular thin-wall fuselage, which is used for solving the problem of low efficiency of repeated iterative calculation of a model which needs to be reestablished when a size parameter is changed in the conventional finite element calculation method.
In order to realize the task, the invention adopts the following technical scheme:
a method for calculating the buckling deformation of a large-opening structure of a rectangular thin-wall machine body comprises the following steps:
according to the shape and the size of an actual large opening structure of the machine body, a structural model of the large opening of the machine body is established, and in the structural model, reinforcing frames at two ends of the actual large opening structure are simplified into a model structure connected with the large opening through one of the reinforcing frames; setting a constraint end face to simulate a reinforcing frame at the end part of a large-opening structure of an actual structure, wherein the end face of a large-opening structure model is superposed with the constraint end face, the end face is used as a fixed end, and the other end face is used as a loading end; determining an origin of a coordinate axis in the structural model, and then establishing a coordinate system; applying a torsional load around an x axis to the large-opening structure model at the loading end so as to establish a torsional model;
calculating relevant parameters of the section characteristics of the torsion model of the large-opening structure of the fuselage, including the fanning area and the main fanning moment of inertia;
under the action of torsional load, calculating torsional angles at different section positions;
determining buckling deformation key points in the large-opening structure torsion model, then respectively calculating buckling deformation at each buckling deformation key point, and solving the buckling deformation of the whole large-opening structure.
Further, determining an origin of a coordinate axis in the structural model, and then establishing a coordinate system, including:
taking a symmetrical surface of the large opening structure as a reference, wherein the symmetrical surface vertically divides the end surface of the large opening structure; taking the top z of the large-distance opening structure on the intersection line of the symmetrical surface and the end surface h Point (c) is taken as the O point, z h The calculation formula of (c) is:
wherein h represents the height of the large opening structure, and b represents the width of the large opening structure;
and based on the origin O, determining that the length direction of the large opening structure is an x axis, the height direction is a z axis and the direction is upward, and the y axis is determined according to a right-hand coordinate system rule.
Further, the calculation process of the fanning area is as follows:
torsional load M applied to large-opening structure model t Then torsional deformation occurs; determining a torsional center position P of torsion on a z-axis, taking the torsional center P as a main pole point, taking an intersection point K of the z-axis and the upper part of the large-opening structure model as a main zero point, taking a vertical distance from any point Q to P on a section as r, and defining the integral of the vertical distance r from the main zero point K to the point Q along the arc length of the profile of the section as a fanning area A w 。
Further, the calculation process of the main fanning moment of inertia is as follows:
based on the fanning area A w Calculating the main fan-shaped moment of inertia I of the section of the large-opening model w (ii) a Principal fan moment of inertia I w Is: - Ω A w 2 dA, wherein dA represents the integral infinitesimal area, and Ω represents the cross-sectional area of the large opening of the fuselage; a is to be w After substituting the preceding formula, the formula is as follows:
where t represents the wall thickness of the large opening twist model.
Further, the calculating the torsion angle at different section positions under the action of the torsion load comprises:
under torsional load M t Under the action, the control equation of the torsion angle at different calculated section positions is as follows:
in the above formula, x represents the distance between the position of the calculated profile and the constraint end face, and the calculated profile is a profile perpendicular to the x axis; l represents the length of the fuselage large opening model, and E is the modulus of elasticity of the structural material;
principal segmental moment of inertia I w Substituting the expressions, further obtaining the expression of the torsion angle as:
further, in the large-opening structure torsion model, determining a buckling deformation key point includes:
and taking four corner points of the section of the large-opening torsion model of the fuselage as buckling deformation key points.
Further, the calculating the warp deformation at each warp deformation key point respectively comprises:
establishing an expression of the buckling deformation u of the large-opening structure torsion model along the x axis:
substituting the fanning area values at the buckling deformation key points A and A 'into u respectively, the buckling deformation at A and A' can be expressed as:
substituting the fanning area values of the buckling deformation key points B and B 'into u respectively to obtain the buckling deformation at the positions B and B', wherein the expressions of the buckling deformation are as follows:
the large opening torsion model comprises a torsion model section, a large opening torsion model section and a large opening torsion model section, wherein the four angular points of the large opening torsion model section are A and A ', and the left lower angular point and the right lower angular point are A and A', respectively; the upper left corner point and the upper right corner point are B and B' respectively.
Further, the determining the warp deformation of the whole large opening structure includes:
and calculating the warp deformation of each warp deformation key point at x = L, so that the warp deformation of the key point of the calculation section with the maximum warp deformation is calculated, and the maximum warp deformation of the whole model is represented.
Compared with the prior art, the invention has the following technical characteristics:
1. according to the invention, through deep research on a large opening structure at the lower part of the rectangular section fuselage of the airplane under torsional load, an expression of the buckling deformation of the structure is obtained, key parameters influencing the buckling deformation are obtained, and theoretical support is provided for controlling the buckling deformation.
2. The key parameters of the buckling deformation are obtained through optimization of finite element calculation software, when the load, the overall dimension and the opening dimension are changed in the finite element calculation, a finite element model needs to be re-established, grids are re-divided, optimization calculation is loaded, the calculation iteration process is long, the workload is large, and the key parameters influencing the buckling deformation are not clear in a finite element method. By adopting the method for determining the parameters in the formula, the key parameters of the warping deformation can be quickly obtained no matter how the size parameters of the large opening change, and the working efficiency is greatly improved.
Drawings
FIGS. 1 (a), (b) and (c) are respectively a front view, a right view and a perspective view of a torsion model of a large opening structure of a rectangular section fuselage;
FIG. 2 is a schematic view of the fan area distribution;
FIG. 3 is a schematic flow chart of the method of the present invention.
Detailed Description
Referring to fig. 1 to 3, the invention discloses a method for calculating the buckling deformation of a large opening structure of a rectangular thin-wall fuselage, which comprises the following steps:
step 1, establishing a torsion model of a rectangular section fuselage large opening structure
According to the shape and the size of the actual large opening structure of the machine body, a structural model of the large opening structure of the machine body is established, as shown in figure 1; in the structural model, for the reinforcing frames at two ends of the actual large-opening structure, because the reinforcing frames at two ends have the same constraint on the large-opening structure when the large-opening structure is subjected to torsional load, the reinforcing frames are simplified into a model structure in which one reinforcing frame is connected with the large opening in the structural model; the other reinforcing frame is connected with the large opening and used for analyzing the model structure in the same process.
Setting a restraint end face to simulate a reinforcing frame at the end part of a large-opening structure of an actual structure, wherein the end face of the large-opening structure model is superposed with the restraint end face, the end face is used as a fixed end, and the other end face is used as a loading end.
Firstly, determining an origin O of a coordinate axis, wherein the method comprises the following steps:
taking a symmetrical surface of the large opening structure as a reference, wherein the symmetrical surface vertically divides the end surface of the large opening structure; taking the top z of the large-distance opening structure on the intersection line of the symmetrical surface and the end surface h Point (c) is regarded as point O, z h The calculation formula of (2) is as follows:
where h denotes the height of the large-opening structure and b denotes the width of the large-opening structure.
In the above formula, the distance from the top surface z of the large opening structure h When the large-opening structure is twisted, the inventor analyzes and calculates that the normal stress is 0 and the shear stress is maximum, and then the point on the intersection line corresponding to the position is determined as the positionPoint O of (2).
Based on the origin O, determining that the length direction of the large opening structure is an x axis, the height direction is a z axis and points upwards, and the y axis is determined according to a right-hand coordinate system rule; taking an actual airplane as a reference, the x axis is generally the reverse heading of the airplane, the y axis is the right side of the airplane body, and the z axis is the height direction of the airplane body.
For the large-opening structure model, applying a torsional load M around the x axis to the large-opening structure model at the loading end t Thereby establishing a torsion model.
Torsional load M applied to large-opening structure model t Then torsional deformation occurs; determining a torsional center position P of torsion on a z-axis, taking the torsional center P as a main pole point, taking an intersection point K of the z-axis and the upper part of the large-opening structure model as a main zero point, taking a vertical distance from any point Q to P on a section as r, and defining the integral of the vertical distance r from the main zero point K to the point Q along the arc length of the profile of the section as a fanning area A w 。
Wherein, the distance m =3h from the torsional center position P to the top of the large-opening structure model 2 /(b+6h)。
For example, for a point B 'on the cross section, the integration direction of the corresponding fan-shaped area during calculation is shown by an arrow in fig. 2, the integration starting point is the intersection point of the z-axis and the top of the large opening mold, and the integration ending point is the point B'.
Based on the fanning area A w Calculating the main fan-shaped moment of inertia I of the section of the large-opening model w (ii) a Principal fan moment of inertia I w Is: - Ω A w 2 dA, wherein dA represents an integral infinitesimal area, and Ω represents a cross-sectional area of a large opening of the fuselage; a is to be w After substituting the foregoing equation, the following equation is used:
where t represents the wall thickness of the large opening model.
Step 3, calculating the torsion angle of the large opening structure model
Under torsional load M t Under the action, the torsion angle control equation at different calculated section positions is as follows:
in the above formula, x represents the distance between the position of the calculated profile and the constraint end face, and the calculated profile is a profile perpendicular to the x axis; l represents the length of the fuselage large opening model and E is the modulus of elasticity of the structural material.
Principal segmental moment of inertia I w Substituting the expressions, further obtaining the expression of the torsion angle as:
step 4, calculating the warping deformation of the large-opening structure model
In the large-opening structure torsion model, the buckling deformation key point is determined, and the position of the point with the largest buckling deformation can be determined from fig. 2 of the fan-shaped area of the cross section, so for the present solution, the buckling deformation key point is: four angular points of the cross section of the large-opening torsion model of the fuselage, wherein the left lower angular point and the right lower angular point are A and A' respectively; the upper left corner point and the upper right corner point are B and B' respectively.
Establishing an expression of the buckling deformation u of the large-opening structure torsion model along the x axis:
will I w Substituting the expression into a u expression, wherein the expression of u is as follows:
substituting the fanning area values at the buckling deformation key points A and A 'into u respectively can obtain the buckling deformation expressions at A and A' as follows:
substituting the fanning area values of the buckling deformation key points B and B 'into u respectively to obtain the buckling deformation at the positions B and B', wherein the expressions of the buckling deformation are as follows:
in the above formula, when x is L, u is maximum; in actual calculation, the warp deformation of each warp deformation key point can be calculated at x = L, and thus the calculated warp deformation is the warp deformation of the key point of the calculated section with the largest warp deformation, namely the largest warp deformation of the whole model.
According to the method, the warp deformation expression of the large-opening structure model with any size under the action of torque can be determined, and the method can be used for controlling the warp deformation of the structure in the structure design process; for example, for a certain actual large-opening structure, the warp deformation of the corresponding warp deformation key point can be obtained only by bringing the relevant structure parameters into the expression of the warp deformation key point, and then whether the design requirement is met is evaluated; when the structural design guidance is not satisfied, the parameters can be quickly adjusted through a formula, and the structural design guidance is of great significance.
The embodiment is as follows:
the buckling deformation of the cabin structure of a certain machine body is solved, and 2A12-T4 is selected as the cabin material.
(1) Determining a torsion model
The torsion model shown in fig. 1 is simplified from the actual structure, and the respective dimensional parameters are determined.
Width b =2440mm, height h =2060mm, opening length L =5000mm, wall thickness of structure t =5.8mm, and torsional load M t ＝10 9 N·mm
The material is 2A12-T4, and the elastic modulus of the material is E =71000MPa.
The calculation method comprises the following steps:
(2) Calculating warp deformation
Calculating a section: loading end, i.e. x =5000mm
At points a and a' at the edge of the rectangular opening, the warp deformation is:
and solving the buckling deformation at the position of any section x, and substituting the section position coordinate x into a deformation expression.
The above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should 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; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present application, and are intended to be included within the scope of the present application.
Claims (3)
1. A method for calculating the buckling deformation of a large-opening structure of a rectangular thin-wall machine body is characterized by comprising the following steps of:
according to the shape and the size of an actual large opening structure of the machine body, a structural model of the large opening of the machine body is established, and in the structural model, reinforcing frames at two ends of the actual large opening structure are simplified into a model structure connected with the large opening through one of the reinforcing frames; setting a restraint end face to simulate a reinforcing frame at the end part of a large-opening structure of an actual structure, wherein the end face of a large-opening structure model is superposed with the restraint end face, the end face is used as a fixed end, and the other end face is used as a loading end; determining an origin of a coordinate axis in the structural model, and then establishing a coordinate system; applying a torsional load around an x axis to the large-opening structure model at the loading end so as to establish a torsional model;
calculating relevant parameters of section characteristics of a torsion model of a large opening structure of the machine body, including a fanning area and a main fanning moment of inertia;
under the action of torsional load, calculating torsional angles at different section positions;
determining buckling deformation key points in a large-opening structure torsion model, then respectively calculating buckling deformation at each buckling deformation key point, and solving the buckling deformation of the whole large-opening structure;
determining an origin of a coordinate axis in the structural model, and then establishing a coordinate system, wherein the method comprises the following steps:
taking a symmetrical surface of the large opening structure as a reference, wherein the symmetrical surface vertically divides the end surface of the large opening structure; taking the top z of the large-distance opening structure on the intersection line of the symmetrical surface and the end surface h Point (c) is regarded as point O, z h The calculation formula of (2) is as follows:
wherein h represents the height of the large opening structure, and b represents the width of the large opening structure;
based on the origin O, determining that the length direction of the large opening structure is an x axis, the height direction is a z axis and points upwards, and the y axis is determined according to a right-hand coordinate system rule;
the calculation process of the fanning area is as follows:
torsional load M applied to large-opening structure model t Then torsional deformation occurs; determining a torsional center position P of torsion on a z-axis, taking the torsional center P as a main pole point, taking an intersection point K of the z-axis and the upper part of the large-opening structure model as a main zero point, taking a vertical distance from any point Q to P on a section as r, and defining the integral of the vertical distance r from the main zero point K to the point Q along the arc length of the profile of the section as a fanning area A w ；
The calculation process of the main sectorial moment of inertia is as follows:
based on the fanning area A w Calculating the dominant fan inertia of the large opening model profileMoment of sex I w (ii) a Principal fanning moment of inertia I w Is: - Ω A w 2 dA, wherein dA represents the integral infinitesimal area, and Ω represents the cross-sectional area of the large opening of the fuselage; a is to be w After substituting the foregoing equation, the following equation is used:
wherein t represents the wall thickness of the large opening torsion model;
under the action of torsional load, calculating torsion angles at different section positions, including:
under torsional load M t Under the action, the control equation of the torsion angle at different calculated section positions is as follows:
in the above formula, x represents the distance between the position of the calculated profile, which is a profile perpendicular to the x axis, and the constraining end face; l represents the length of the fuselage large opening model, and E is the modulus of elasticity of the structural material;
principal segmental moment of inertia I w Substituting the expressions, further obtaining the expression of the torsion angle as:
the step of respectively calculating the warp deformation at each warp deformation key point comprises the following steps:
establishing an expression of the buckling deformation u of the large-opening structure torsion model along the x axis:
substituting the fanning area values at the buckling deformation key points A and A 'into u respectively can obtain the buckling deformation expressions at A and A' as follows:
substituting the fanning area values of the buckling deformation key points B and B 'into u respectively to obtain the buckling deformation at the positions B and B', wherein the expressions of the buckling deformation are as follows:
the large opening torsion model comprises a torsion model section, a large opening torsion model section and a large opening torsion model section, wherein the four angular points of the large opening torsion model section are A and A ', and the left lower angular point and the right lower angular point are A and A', respectively; the upper left corner point and the upper right corner point are B and B' respectively.
2. The method for calculating the buckling deformation of the large-opening structure of the rectangular thin-walled fuselage according to claim 1, wherein the determining the buckling deformation key points in the large-opening structure torsion model comprises the following steps:
and taking four corner points of the section of the large-opening torsion model of the fuselage as buckling deformation key points.
3. The method for calculating the buckling deformation of the large opening structure of the rectangular thin-walled fuselage according to claim 1, wherein the finding of the buckling deformation of the whole large opening structure comprises:
and calculating the warp deformation of each warp deformation key point at x = L, so that the warp deformation of the key point of the calculation section with the maximum warp deformation is calculated, and the maximum warp deformation of the whole model is represented.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011611928.5A CN112711806B (en) | 2020-12-29 | 2020-12-29 | Method for calculating buckling deformation of large-opening structure of rectangular thin-wall machine body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011611928.5A CN112711806B (en) | 2020-12-29 | 2020-12-29 | Method for calculating buckling deformation of large-opening structure of rectangular thin-wall machine body |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112711806A CN112711806A (en) | 2021-04-27 |
| CN112711806B true CN112711806B (en) | 2022-10-11 |
Family
ID=75547317
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011611928.5A Active CN112711806B (en) | 2020-12-29 | 2020-12-29 | Method for calculating buckling deformation of large-opening structure of rectangular thin-wall machine body |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112711806B (en) |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006278803A (en) * | 2005-03-30 | 2006-10-12 | Nec Corp | Method, system, and program for analyzing warpage of board |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8721282B2 (en) * | 2008-07-29 | 2014-05-13 | The United States Of America, As Represented By The Secretary Of The Navy | Active twist hollow beam system |
-
2020
- 2020-12-29 CN CN202011611928.5A patent/CN112711806B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006278803A (en) * | 2005-03-30 | 2006-10-12 | Nec Corp | Method, system, and program for analyzing warpage of board |
Non-Patent Citations (3)
| Title |
|---|
| 偏心轴向荷载作用下薄壁箱梁的约束扭转翘曲应力研究;张元海等;《工程力学》;20130325(第03期);全文 * |
| 基于协调翘曲场的开闭口混合薄壁截面杆件约束扭转一维有限元分析;文颖等;《工程力学》;20200925(第09期);全文 * |
| 大型集装箱船弯扭总纵强度分析方法研究;彭文科等;《中国造船》;20200930(第03期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112711806A (en) | 2021-04-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2583468C (en) | Method for designing a flight vehicle | |
| CN108052772A (en) | A kind of geometrical non-linearity static aeroelastic analysis method based on structure reduced-order model | |
| KR102021498B1 (en) | Design method of attitude control system for flight vehicle and computer program | |
| EP2003581A1 (en) | Structural analysis apparatus and structural analysis method | |
| CN112711806B (en) | Method for calculating buckling deformation of large-opening structure of rectangular thin-wall machine body | |
| CN113158337A (en) | Variable camber flexible trailing edge-based wing and gust response slowing method thereof | |
| CN110508852A (en) | A kind of processing of structural member, assembly and detection Trinity hole location determine method | |
| CN113392599B (en) | Method for determining dynamic response of elastic aircraft | |
| CN112711812B (en) | Method for calculating torsional deformation of large-opening structure of rectangular thin-wall machine body | |
| CN112711799B (en) | Method for calculating buckling deformation of large-opening structure of reinforced rectangular thin-wall machine body | |
| CN112699485B (en) | Method for calculating torsional deformation of large opening structure of reinforced rectangular thin-wall machine body | |
| CN112829963B (en) | Method for determining structural parameters of rectangular fuselage large-opening structure under torsional load | |
| CN112035959A (en) | Method for rapidly determining airfoil rigid shaft by using full-machine finite element analysis result | |
| CN112711801B (en) | Rectangular thin-wall machine body large-opening structure torsion load distribution calculation method | |
| CN112052524B (en) | Modeling method for hanging flexible fuselage of helicopter | |
| CN106681350B (en) | Aircraft system balancing method and device | |
| CN112699486B (en) | Reinforced rectangular fuselage large-opening structure torsion load distribution calculation method | |
| CN112711803B (en) | Method for determining torsional rigidity of large-opening structure of cabin body of rectangular fuselage | |
| CN106055860B (en) | It inside buries weapon-bay and folds hatch door aeroelasticity dynamic response numerical computation method | |
| US20240150037A1 (en) | Aeroelastic adjustment using flutter vector strain energy | |
| JPH0411440B2 (en) | ||
| CN115238378B (en) | Aerodynamic design method with large attack angle | |
| JP6971759B2 (en) | Wing and wing design method | |
| CN117094077B (en) | Airfoil optimization method based on transonic aeroelastic analysis | |
| CN117932777A (en) | Accurate calculation method for torsional deformation of rectangular opening structure of reinforced fuselage |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |