CN107918698A - A kind of amphibious aircraft fuselage skin Mass Distribution computational methods - Google Patents
A kind of amphibious aircraft fuselage skin Mass Distribution computational methods Download PDFInfo
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- CN107918698A CN107918698A CN201711032143.0A CN201711032143A CN107918698A CN 107918698 A CN107918698 A CN 107918698A CN 201711032143 A CN201711032143 A CN 201711032143A CN 107918698 A CN107918698 A CN 107918698A
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- fuselage
- hull bottom
- amphibious aircraft
- mass distribution
- camber line
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- 238000000205 computational method Methods 0.000 title claims abstract description 21
- 206010067868 Skin mass Diseases 0.000 title claims abstract description 18
- 230000011218 segmentation Effects 0.000 claims abstract description 10
- 238000000034 method Methods 0.000 claims abstract description 9
- 238000004364 calculation method Methods 0.000 claims abstract description 6
- 239000004744 fabric Substances 0.000 claims description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004590 computer program Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 230000010354 integration Effects 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
Abstract
The present invention relates to a kind of amphibious aircraft fuselage skin Mass Distribution computational methods, step 1, introduce typical amphibious aircraft fuselage cross-section parameter：Fuselage half-breadth D, fuselage upper half camber line height N, fuselage lower semisection radius of curvature R, fuselage hull bottom half-breadth B；Step 2, fuselage upper half camber line is described by introducing conic section, introduces camber line equation to describe fuselage lower semisection camber line, hull bottom camber line；Step 3, fuselage skin is reduced to quality infinitesimal along short transverse, fuselage longitudinal direction, calculates the mass property of each quality infinitesimal；Step 4, the covering Mass Distribution of whole fuselage is obtained by the covering mass property of each grid of integral and calculating or segmentation；Step 5, above computational methods are written as calculation procedure, input data file covering density, cross section parameter can high-speed computer body covering Mass Distribution.The present invention solves the problems, such as that aircraft layout stage amphibious aircraft fuselage Mass Distribution difficulty in computation is big, parameter selection is difficult.
Description
Technical field
The present invention relates to a kind of amphibious aircraft fuselage skin Mass Distribution computational methods, by the way that this method extraction is cut
Face parameter, programs, input data file, it is possible to rapidly and accurately carries out the quality point of amphibious aircraft fuselage skin
Cloth calculates.
Background technology
The fuselage skin interface of land airplane similar circular or ellipse mostly, fuselage skin are longitudinally tubular, shape
More regular, Mass Distribution computation modeling is relatively easy, and cross section parameter is chosen also relatively easy.Amphibious aircraft fuselage skin
Top half is analogous to the class half-cylinder structure of land airplane, may be referred to the modeling method meter of land airplane fuselage skin
Calculate；Lower half is Ship Structure, complex-shaped, it is difficult to reference to the Modeling Calculation mode of land airplane.
The content of the invention
The present invention provides a kind of new amphibious aircraft fuselage skin Mass Distribution computational methods, overcomes amphibious
Aircraft fuselage skin is complex-shaped, and Mass Distribution calculates the difficulty such as cumbersome.It introduces curvilinear equation by extracting cross section parameter,
Write computer program, input data file, it is possible to rapidly and accurately carry out the matter of amphibious aircraft fuselage skin hull
Amount distribution calculates.
In order to solve the above technical problems, the technical solution adopted in the present invention is：A kind of amphibious aircraft fuselage skin
Mass Distribution computational methods.This method comprises the following steps：
First, as shown in drawings, present invention introduces typical amphibious aircraft fuselage cross-section parameter：Fuselage half-breadth D, machine
Half camber line height N, fuselage lower semisection radius of curvature R, fuselage hull bottom half-breadth B, fuselage lower semisection camber line longitudinal projection height with it
H, fuselage lower semisection height h, fuselage hull bottom radius of curvature R1, fuselage hull bottom leaning angle βIt is interior, fuselage hull bottom camber angle βOutside。
Second, fuselage upper half camber line is described by introducing conic section, introduces camber line equation to describe fuselage lower semisection
Camber line, hull bottom camber line, introduce linear equation and describe fuselage hull bottom oblique line.
3rd, fuselage skin is reduced to the quality infinitesimal along short transverse, fuselage longitudinal direction, calculates each quality infinitesimal
Mass property.
4th, the covering quality of whole fuselage is obtained by the covering mass property of each grid of integral and calculating or segmentation
Distribution.
5th, above computational methods are written as calculation procedure, input data file covering density, cross section parameter can
The Mass Distribution of high-speed computer body covering.
Comprise the following steps that：
A kind of amphibious aircraft fuselage skin Mass Distribution computational methods, comprise the following steps that：
Step 1, typical amphibious aircraft fuselage cross-section parameter is introduced：Fuselage half-breadth D, fuselage upper half camber line height N,
Fuselage lower semisection radius of curvature R, fuselage hull bottom half-breadth B, fuselage lower semisection camber line longitudinal projection height H, fuselage lower semisection height
H, fuselage hull bottom radius of curvature R1, fuselage hull bottom leaning angle βIt is interior, fuselage hull bottom camber angle βOutside；
Step 2, fuselage upper half camber line is described by introducing conic section, introduces camber line equation to describe fuselage lower semisection
Camber line, hull bottom camber line, introduce linear equation and describe fuselage hull bottom oblique line；
Step 3, fuselage skin is reduced to quality infinitesimal along short transverse, fuselage longitudinal direction, calculates each quality infinitesimal
Mass property；
Step 4, the covering matter of whole fuselage is obtained by the covering mass property of each grid of integral and calculating or segmentation
Amount distribution；
Step 5, above computational methods are written as calculation procedure, input data file covering density, cross section parameter can
With the Mass Distribution of high-speed computer body covering.
Quadratic curve equation, fuselage half-breadth D, fuselage upper half camber line height N are introduced in step 2, to amphibious aircraft
The upper half segmental arc of fuselage cross-section is calculated.
In step 2, an arc equation, fuselage half-breadth D, fuselage lower semisection radius of curvature R, fuselage hull bottom half-breadth B, fuselage are introduced
Lower semisection camber line longitudinal projection height H, calculates amphibious aircraft fuselage cross-section lower half segmental arc.
In step 2, an arc equation, fuselage hull bottom radius of curvature R1, fuselage hull bottom half-breadth B, fuselage lower semisection camber line are introduced
Longitudinal projection height H, fuselage hull bottom camber angle βOutsideAmphibious aircraft fuselage hull bottom cross section segmental arc is calculated.
In step 2, linear equation, fuselage hull bottom leaning angle β are introducedIt is interior, fuselage lower semisection height h, to amphibious aircraft
The oblique line section of fuselage hull bottom cross section is calculated.
In step 3, by cross section parameter introduced above, curvilinear equation, in fuselage longitudinal direction, short transverse by fuselage skin
The quality infinitesimal of very little is reduced to, calculates the mass property of each quality infinitesimal respectively.
In step 4, the covering mass property that above-mentioned quality infinitesimal is carried out to each grid of integral and calculating or segmentation obtains
The covering Mass Distribution of whole fuselage.
Fuselage skin Mass Distribution computational methods of the present invention：Compared with the prior art, the beneficial effects of the present invention are：
By the way that fuselage skin part model is simplified, each section of characteristic cross-section of fuselage skin is extracted, according to cross section parameter, takes segmentation
Curve modeling pair cross-section carries out Mass Distribution calculating.Mass Distribution calculating is carried out using finite element, integration between each section of section.Calculate
Precision is high, it is only necessary to the formal parameter of fuselage, covering density, it is not necessary to establish careful threedimensional model, solve airplane design
The problem of conceptual level amphibious aircraft fuselage Mass Distribution difficulty in computation is big.
Brief description of the drawings
Fig. 1 is that a kind of new amphibious aircraft fuselage skin Mass Distribution computational methods of present invention offer are introduced
The typical cross section parameters schematic diagram of amphibious aircraft fuselage.
D is fuselage half-breadth in figure, N is fuselage upper half camber line height, R is fuselage lower semisection radius of curvature, B is fuselage hull bottom
Half-breadth, H are fuselage lower semisection camber line longitudinal projection height, h is fuselage lower semisection height, R1For fuselage hull bottom radius of curvature, βIt is interior
For fuselage hull bottom leaning angle, βOutsideFor fuselage hull bottom camber angle.
Embodiment
The tool of amphibious aircraft fuselage skin Mass Distribution computational methods of the present invention is further illustrated with reference to Fig. 1
Body embodiment is as follows.
First, introduce fuselage cross-section parameter：Fuselage half-breadth D, fuselage upper half camber line height N, fuselage lower semisection radius of curvature
R, fuselage hull bottom half-breadth B, fuselage lower semisection camber line longitudinal projection height H, fuselage lower semisection height h, fuselage hull bottom radius of curvature
R1, fuselage hull bottom leaning angle βIt is interior, fuselage hull bottom camber angle βOutside；
Second, segmentation introduces curvilinear equation to describe fuselage skin section feature.Pass through quadratic curve equation curvilinear equationFuselage upper semisection camber line is described.Pass through round equation (x-a)2+(y-b)2=R2Fuselage lower semisection camber line is described, its
Middle a, b are central coordinate of circle, can be by substituting into H, B, D gain of parameter.Pass through round equation (x-a1)2+(y-b1)2=R1 2To describe
Hull bottom cross-sectional curve, wherein a1, b1Can be β by substituting into B, H and inclination angle for central coordinate of circleIt is interiorLinear equation try to achieve.Hull bottom
Section oblique line can pass through linear equation y=xtan βIt is interior- h is described.The other half curve of fuselage cross-section can pass through above-mentioned segmentation
Curvilinear equation is obtained using symmetry.
3rd, infinitesimal, by the way that covering to be reduced to the mass-element of very little, the quality for calculating each quality infinitesimal respectively is special
Property.Infinitesimal is carried out along short transverse and fuselage length direction to fuselage skin, infinitesimal obtains the length of side and is
Wherein K1, K2For integer so that dy, dy's is respectively less than 0.005m.Closed according to the density of covering and infinitesimal point in the position at interface
System, calculates the mass property of infinitesimal.
4th, the masked Mass Distribution of integral and calculating, by the principle of stacking of mass property, according to grid or quality point
The requirement of cloth divisional plane, carries out integral and calculating by the quality infinitesimal in grid or in segmentation, obtains the Mass Distribution data of covering.
5th, above calculating process is written as calculation procedure, input data file covering density, cross section parameter can
The Mass Distribution of high-speed computer body covering.
The above disclosed right model for being only the preferred embodiment of the present invention, the present invention cannot being limited with this certainly
Enclose, with the equivalent variations that this is done according to scope of the present invention patent, still fall within the scope that the present invention is covered.
Claims (7)
1. a kind of amphibious aircraft fuselage skin Mass Distribution computational methods, it is characterised in that comprise the following steps that：
Step 1, typical amphibious aircraft fuselage cross-section parameter is introduced：Fuselage half-breadth D, fuselage upper half camber line height N, fuselage
Lower semisection radius of curvature R, fuselage hull bottom half-breadth B, fuselage lower semisection camber line longitudinal projection height H, fuselage lower semisection height h, machine
Body hull bottom radius of curvature R1, fuselage hull bottom leaning angle βIt is interior, fuselage hull bottom camber angle βOutside；
Step 2, fuselage upper half camber line is described by introducing conic section, introduces camber line equation to describe fuselage lower semisection arc
Line, hull bottom camber line, introduce linear equation and describe fuselage hull bottom oblique line；
Step 3, fuselage skin is reduced to quality infinitesimal along short transverse, fuselage longitudinal direction, calculates the matter of each quality infinitesimal
Flow characteristic；
Step 4, the covering quality point of whole fuselage is obtained by the covering mass property of each grid of integral and calculating or segmentation
Cloth；
Step 5, above computational methods are written as calculation procedure, input data file covering density, cross section parameter can be fast
Speed calculates the Mass Distribution of fuselage skin.
2. amphibious aircraft fuselage skin Mass Distribution computational methods according to claim 1, it is characterised in that：Step
Quadratic curve equation, fuselage half-breadth D, fuselage upper half camber line height N are introduced in 2, to amphibious aircraft fuselage cross-section
Upper half segmental arc is calculated.
3. amphibious aircraft fuselage skin Mass Distribution computational methods according to claim 1, it is characterised in that：Step
In 2, introduce an arc equation, fuselage half-breadth D, fuselage lower semisection radius of curvature R, fuselage hull bottom half-breadth B, fuselage lower semisection camber line and indulge
To standoff height H, amphibious aircraft fuselage cross-section lower half segmental arc is calculated.
4. amphibious aircraft fuselage skin Mass Distribution computational methods according to claim 1, it is characterised in that：Step
In 2, an arc equation, fuselage hull bottom radius of curvature R1, fuselage hull bottom half-breadth B, fuselage lower semisection camber line longitudinal projection height are introduced
H, fuselage hull bottom camber angle βOutsideAmphibious aircraft fuselage hull bottom cross section segmental arc is calculated.
5. amphibious aircraft fuselage skin Mass Distribution computational methods according to claim 1, it is characterised in that：Step
In 2, linear equation, fuselage hull bottom leaning angle β are introducedIt is interior, fuselage lower semisection height h, it is transversal to amphibious aircraft fuselage hull bottom
The oblique line section in face is calculated.
6. amphibious aircraft fuselage skin Mass Distribution computational methods according to claim 1, it is characterised in that：Step
In 3, by cross section parameter introduced above, curvilinear equation, fuselage skin is reduced to very little in fuselage longitudinal direction, short transverse
Quality infinitesimal, calculates the mass property of each quality infinitesimal respectively.
7. amphibious aircraft fuselage skin Mass Distribution computational methods according to claim 1, it is characterised in that：Step
In 4, the covering mass property that above-mentioned quality infinitesimal is carried out to each grid of integral and calculating or segmentation obtains the illiteracy of whole fuselage
Skin Mass Distribution.
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| CN201711032143.0A CN107918698A (en) | 2017-10-27 | 2017-10-27 | A kind of amphibious aircraft fuselage skin Mass Distribution computational methods |
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| CN203528820U (en) * | 2012-12-14 | 2014-04-09 | 中航通飞研究院有限公司 | Large-scale fire extinguishing amphibious airplane |
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Effective date of registration: 20221024 Address after: 519040 building 201, 999 Jinhai Middle Road, Jinwan District, Zhuhai City, Guangdong Province Applicant after: SOUTH CHINA AIRCRAFT INDUSTRY CO., LTD. OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. Address before: 519040 AVIC Tongfei industrial base, aviation industrial park, Jinwan District, Zhuhai City, Guangdong Province Applicant before: R&D INSTITUTE OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. |