CN109543345A - A kind of aircraft big opening construction torsion stiffness design method - Google Patents
A kind of aircraft big opening construction torsion stiffness design method Download PDFInfo
- Publication number
- CN109543345A CN109543345A CN201811540786.0A CN201811540786A CN109543345A CN 109543345 A CN109543345 A CN 109543345A CN 201811540786 A CN201811540786 A CN 201811540786A CN 109543345 A CN109543345 A CN 109543345A
- Authority
- CN
- China
- Prior art keywords
- big opening
- area
- rigidity
- stiffness ratio
- follows
- 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
- 238000000034 method Methods 0.000 title claims abstract description 14
- 238000010276 construction Methods 0.000 title claims abstract description 8
- 238000005452 bending Methods 0.000 claims abstract description 15
- 230000002787 reinforcement Effects 0.000 claims description 7
- 238000005094 computer simulation Methods 0.000 claims description 3
- 230000003068 static effect Effects 0.000 claims description 3
- 230000017260 vegetative to reproductive phase transition of meristem Effects 0.000 claims description 2
- 238000006243 chemical reaction Methods 0.000 claims 1
- 230000003014 reinforcing effect Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 2
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
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
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
Abstract
The invention belongs to aeronautic structure design fields, propose a kind of aircraft big opening construction torsion stiffness design method；This method is firstly introduced the concept of bending stiffness ratio, i.e. the bending stiffness ratio of big opening structure and complete airframe structure.Bending stiffness ratio is equal to 1 for design critical value, shows that the strengthened fuselage big opening rigidity of structure is consistent with complete airframe structure rigidity；Bending stiffness ratio is greater than 1 and shows that the strengthened rigidity of structure is greater than the rigidity of complete airframe structure；Bending stiffness ratio shows that the rigidity of complete airframe structure is not achieved in the strengthened rigidity of structure less than 1.The principle and method that fuselage torsional bending rigidity is reinforced can be determined by the expression formula of bending stiffness ratio, solve the predicament for designing for big opening fuselage and reinforcing gear shaper without theoretical foundation, filled up the domestic blank in the technical field.
Description
Technical field
The invention belongs to aeronautic structure design fields, how especially propose a kind of fuselage big opening construction torsion rigidity
The design method of reinforcement.
Background technique
Fuselage big opening region should bear the load of cargo door itself, still suffer from, transmit the load of empennage and rear body
Lotus.Due to fuselage big opening make structure rigidity occur change dramatically, lead to problems such as to deform it is discontinuous so that fuselage big opening
Reinforce the key points and difficulties for being designed to airplane in transportation category design.It is full in order to which the influence by big opening area to fuselage is minimized
Sufficient rigidity is continuous, compatibility of deformation requirement, must just reinforce open region.However, fuselage big opening reinforces the skill of design
Art data is seldom published, so that designing technique and experience relatively lack.
Summary of the invention
Goal of the invention: in order to which the influence by big opening area to fuselage is minimized, meet that rigidity is continuous, compatibility of deformation wants
It asks, proposes a kind of design method how fuselage big opening construction torsion rigidity is reinforced.
Technical solution: a kind of aircraft big opening construction torsion stiffness design method, method includes the following steps:
For aircraft big opening structure, usually reinforced in opening arrangement crossbeam；The area of stringer is rolled over when calculating
It calculates into skin thickness, simplified big opening structural computational model；
The sectorial area of any point K are as follows:
Fan property line static moment:
The axis moments of inertia are as follows:
Then coordinates of bending center are as follows:
Fan property the moment of inertia are as follows:
In formula:
For astomous airframe structure model, ψ=0, F are enabledb=0 substitutes into JωIn, obtain the fan of imperforation airframe structure
Property the moment of inertia are as follows:
Define the bending stiffness ratio of hatch frame and fuselage without big opening structure are as follows:
Wherein:
R --- fuselage radius；
Fch--- the cross-sectional area of stringer；
2 ψ --- big opening angle；
Fb--- the area of opening reinforcement trusses；
δmp--- skin thickness；
δx--- the converting thickness of covering,
sk--- the length of cross-sectional perimeter；
α --- the angle value at the K of arbitrary point, as angular integral；
ω --- main sectorial area is twice of the upper AKM area of figure, and has:
ω=zARsin(π-α)-R2(π-α)；
--- the sectorial area at arbitrary point K point is twice of KOM area,
zA--- coordinates of bending center value.
In structure design, it just be can determine that out according to bending stiffness ratio bending stiffness ratio and meet torsion stiffness requirement
Condition flowering structure this how to reinforce.
The side bar area that reinforcement mode is reinforced needed for being determined by theoretical formula, can also be according to torsion stiffness ratio
χ variation rule curve and torsion stiffness ratio χ withVariation rule curve checks in.
Advantageous effects: present invention research is firstly introduced the concept of rigidity ratio, i.e. big opening structure and complete fuselage knot
The rigidity ratio of structure.Rigidity ratio is equal to 1 for design critical value, shows the strengthened fuselage big opening rigidity of structure and complete fuselage knot
Structure rigidity is consistent；Large Rigidity contrast shows that the strengthened rigidity of structure is greater than the rigidity of complete airframe structure in 1；Rigidity ratio is less than 1
Show that the rigidity of complete airframe structure is not achieved in the strengthened rigidity of structure.Fuselage can be determined by the expression formula of rigidity ratio
The principle and method that torsional bending rigidity is reinforced solve the predicament for designing for big opening fuselage and reinforcing gear shaper without theoretical foundation, fill out
The domestic blank in the technical field is mended.
Detailed description of the invention
Fig. 1 is big opening structural computational model schematic diagram,
Fig. 2 is no big opening computation model figure,
Fig. 3 is fan property the moment of inertia reference section schematic diagram,
Fig. 4 is torsion stiffness ratio χ variation rule curve,
Fig. 5 be torsion stiffness ratio χ withVariation rule curve.
Specific embodiment
For aircraft big opening structure, usually reinforced in opening arrangement crossbeam, typical fuselage big opening structure
As shown in Fig. 1 (a)；The area of stringer is converted simplified computation model such as Fig. 1 (b) institute into skin thickness when calculating
Show.
In Fig. 1:
R --- fuselage radius；
Fch--- the cross-sectional area of stringer；
2 ψ --- big opening angle；
Fb--- the area of opening reinforcement trusses；
δmp--- skin thickness；
δx--- the converting thickness of covering,
sk--- the length of cross-sectional perimeter.
For aircraft big opening structure, usually reinforced in opening arrangement crossbeam, typical fuselage big opening structure
As shown in Fig. 2 (a)；The area of stringer is converted simplified computation model such as Fig. 2 (b) institute into skin thickness when calculating
Show.
For model shown in Fig. 3,
α --- the angle value at the K of arbitrary point, as angular integral；
ω --- main sectorial area is twice of the upper AKM area of figure, and has:
ω=zARsin(π-α)-R2(π-α)；
--- the sectorial area at arbitrary point K point is twice of KOM area,
zA--- coordinates of bending center value
The sectorial area of any point K are as follows:
Fan property line static moment:
The axis moments of inertia are as follows:
Then coordinates of bending center are as follows:
Fan property the moment of inertia are as follows:
In formula:
For astomous airframe structure model, ψ=0, F are enabledb=0 substitutes into JωIn, obtain the fan of imperforation airframe structure
Property the moment of inertia are as follows:
Define the bending stiffness ratio of hatch frame and fuselage without big opening structure are as follows:
The side bar area that reinforcement mode is reinforced needed for being determined by theoretical formula, can also be according to torsion stiffness ratio
χ variation rule curve (Fig. 4) and torsion stiffness ratio χ withVariation rule curve (Fig. 5) checks in.
Claims (2)
1. a kind of aircraft big opening construction torsion stiffness design method, which is characterized in that
For aircraft big opening structure, reinforced in opening arrangement crossbeam；The area conversion of stringer to covering when calculating
Big opening structural computational model in thickness, after being simplified；In the model,
The sectorial area of any point K are as follows:
Y=Rsin α
Fan property line static moment:
The axis moments of inertia are as follows:
Then coordinates of bending center are as follows:
Fan property the moment of inertia are as follows:
In formula:
For astomous airframe structure model, ψ=0, F are enabledb=0 substitutes into JωIn, obtain the fan inertia of imperforation airframe structure
Square are as follows:
Define the bending stiffness ratio of hatch frame and fuselage without big opening structure are as follows:
Wherein:
R --- fuselage radius；
Fch--- the cross-sectional area of stringer；
2 ψ --- big opening angle；
Fb--- the area of opening reinforcement trusses；
δmp--- skin thickness；
δx--- the converting thickness of covering,
sk--- the length of cross-sectional perimeter；
α --- the angle value at the K of arbitrary point, as angular integral；
ω --- main sectorial area is twice of the upper AKM area of figure, and has:
ω=zARsin(π-α)-R2(π-α)；
--- the sectorial area at arbitrary point K point is twice of KOM area,
zA--- coordinates of bending center value；
In structure design, the condition for meeting torsion stiffness requirement just can determine that out according to bending stiffness ratio bending stiffness ratio
Flowering structure this how to reinforce.
2. a kind of aircraft big opening construction torsion stiffness design method according to claim 1, which is characterized in that reinforcement side
The side bar area that formula is reinforced needed for being determined by theoretical formula, can also according to torsion stiffness ratio χ variation rule curve and
Torsion stiffness ratio χ withVariation rule curve checks in.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811540786.0A CN109543345A (en) | 2018-12-14 | 2018-12-14 | A kind of aircraft big opening construction torsion stiffness design method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811540786.0A CN109543345A (en) | 2018-12-14 | 2018-12-14 | A kind of aircraft big opening construction torsion stiffness design method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109543345A true CN109543345A (en) | 2019-03-29 |
Family
ID=65855212
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811540786.0A Pending CN109543345A (en) | 2018-12-14 | 2018-12-14 | A kind of aircraft big opening construction torsion stiffness design method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109543345A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112623255A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating torsional rigidity of section of door frame area of airplane body |
| CN112711803A (en) * | 2020-12-29 | 2021-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining torsional rigidity of large-opening structure of cabin body of rectangular fuselage |
| CN112763166A (en) * | 2020-12-29 | 2021-05-07 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining lateral rigidity of large-opening structure of cabin body of rectangular fuselage |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102446241A (en) * | 2011-10-27 | 2012-05-09 | 北京航空航天大学 | Wing surface structural rigidity simulation method |
| CN103552695A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Test method for verifying opening and closing functions of cargo door |
-
2018
- 2018-12-14 CN CN201811540786.0A patent/CN109543345A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102446241A (en) * | 2011-10-27 | 2012-05-09 | 北京航空航天大学 | Wing surface structural rigidity simulation method |
| CN103552695A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Test method for verifying opening and closing functions of cargo door |
Non-Patent Citations (1)
| Title |
|---|
| 苏雁飞: "《运输类飞机机身大开口结构加强方式理论研究》", 《力学与实践》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112623255A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating torsional rigidity of section of door frame area of airplane body |
| CN112711803A (en) * | 2020-12-29 | 2021-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining torsional rigidity of large-opening structure of cabin body of rectangular fuselage |
| CN112763166A (en) * | 2020-12-29 | 2021-05-07 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining lateral rigidity of large-opening structure of cabin body of rectangular fuselage |
| CN112711803B (en) * | 2020-12-29 | 2022-11-22 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining torsional rigidity of large-opening structure of cabin body of rectangular fuselage |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109543345A (en) | A kind of aircraft big opening construction torsion stiffness design method | |
| RU2500574C2 (en) | Reinforced wing multi-frame torsion box | |
| CN109573091A (en) | A kind of aircraft big opening structure vertical stiffness design method | |
| US8262024B2 (en) | Aircraft frames | |
| Wensheng et al. | Structural mass prediction in conceptual design of blended-wing-body aircraft | |
| CN109543344A (en) | A kind of calculation method of the vertical bending stiffness in aircraft doorframe area section | |
| CN104724279A (en) | Leading Edge For An Aircraft Lifting Surface | |
| Nguyen et al. | Flutter analysis of mission-adaptive wing with variable camber continuous trailing edge flap | |
| Cook et al. | Worst case gust prediction of highly flexible wings | |
| US9481444B2 (en) | Passive load alleviation for aerodynamic lift structures | |
| Schwinn et al. | Structural sizing of a rotorcraft fuselage using an integrated design approach | |
| Dababneh et al. | Design, analysis and optimization of thin walled semi-monocoque wing structures using different structural idealization in the preliminary design phase | |
| CN109711015A (en) | A kind of lateral stiffness design method of aircraft big opening structure | |
| Kaur et al. | Spars and stringers-function and designing | |
| Brooks et al. | Aerostructural design optimization of the D8 aircraft using active aeroelastic tailoring | |
| US20080203228A1 (en) | Double-Shell Design Center Box | |
| Nguyen et al. | Inertial force coupling to nonlinear aeroelasticity of flexible wing aircraft | |
| CN112711803B (en) | Method for determining torsional rigidity of large-opening structure of cabin body of rectangular fuselage | |
| CN113051660B (en) | Method for calculating lateral bending stiffness of cross section of airplane fuselage doorframe area | |
| Brooks et al. | UCRM: an aerostructural model for the study of flexible transonic aircraft wings | |
| CN112623255A (en) | Method for calculating torsional rigidity of section of door frame area of airplane body | |
| Rais-Rohani et al. | Integrated aerodynamic-structural-control wing design | |
| RU2696138C1 (en) | Controlled swivel wing | |
| Taylor et al. | Numerical method for rapid aerostructural design and optimization | |
| Garcia et al. | Mass prediction models for air cargo challenge aircraft |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190329 |
|
| RJ01 | Rejection of invention patent application after publication |