CN113032894B - Double-cone fairing shape line optimization design method based on Feng Ka door-shaped line - Google Patents
Double-cone fairing shape line optimization design method based on Feng Ka door-shaped line Download PDFInfo
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- CN113032894B CN113032894B CN202110206013.4A CN202110206013A CN113032894B CN 113032894 B CN113032894 B CN 113032894B CN 202110206013 A CN202110206013 A CN 202110206013A CN 113032894 B CN113032894 B CN 113032894B
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Abstract
The invention discloses a double-cone fairing contour line optimization design method based on a Von Karman contour line, which comprises the steps of constructing a fairing contour line segmentation equation based on predefined characteristic parameters of a double-cone fairing; determining a deviation value between two molded lines based on the fairing molded line section equation and a Von Karman molded line equation established according to known structural parameters of the double-cone fairing; calculating the parameter value of the molded line of the biconical fairing by using the minimized molded line deviation as an optimization target; and drawing the double-cone fairing profile based on the parameter values. The double-cone molded line optimized by the appearance design scheme of the double-cone fairing is most attached to the Von Karman molded line, so that the cost is reduced, and the advantages of simple processing technology and superior pneumatic characteristic are achieved.
Description
Technical Field
The invention relates to an optimal design method, in particular to a double-cone fairing shape line optimal design method based on a Von Karman shape line.
Background
The existing nose line of the fairing of the carrier rocket mainly comprises a cone, an arc, a parabolic shape, an exponential shape, a Feng Ka door shape and a biconical shape.
The von Karman type wire has the advantages of excellent pneumatic characteristics, large space size and low internal noise, but is complex in structure, poor in manufacturability and high in cost.
The machining process of the double-cone molded line is simple, but the aerodynamic characteristics are slightly inferior, and the determination of a specific double-cone profile parameter with relatively better aerodynamic characteristics is dependent on experience and a large amount of fluid simulation calculation.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a double-cone fairing shape line optimization design method based on Feng Ka door-shaped lines, which is used for appearance design of a double-cone fairing.
The purpose of the invention is realized by adopting the following technical scheme:
a method for optimally designing a biconical fairing-shaped wire based on a Feng Ka door-shaped wire comprises the following steps:
constructing a fairing profile line section equation based on predefined characteristic parameters of the double-cone fairing;
determining a deviation value between two molded lines based on the fairing molded line section equation and a Von Karman molded line equation established according to known structural parameters of the double-cone fairing;
calculating the parameter value of the molded line of the biconical fairing by using the molded line deviation minimization as an optimization target;
and drawing the double-cone fairing profile based on the parameter values.
Preferably, the double-cone fairing comprises a cone top and a double-cone section;
the characteristic parameters of the double-cone fairing comprise: the position (x 1, y 1) of the tangent point of the cone vertex arc and the first cone segment, and the position coordinates (x 2, y 2) of the junction point of the double cone segments.
Preferably, the profile segment equation for the fairing is determined by:
y s ＝f(x s )
in the formula, x s As an axial coordinate, y s Is the radial coordinate of the fairing, f being the expression y s And x s A double-cone fairing profile equation of the functional relationship of (a).
Preferably, the known structural parameters of the double-cone fairing comprise a fairing length L, a fairing rear end diameter Rd and a tip end rounding radius rk;
the von Karman type line equation established according to the known structure parameters of the double-cone fairing is as follows:
y k ＝g(x k )；
in the formula, x k As an axial coordinate, y k Is the radial coordinate of the fairing, g being y k And x k Functional relationship of von karman type line equation.
Preferably, the determining the deviation value between the two profiles based on the fairing profile segment equation and the von karman profile equation established according to the known structural parameters of the double-cone fairing comprises:
calculating the molded line absolute difference value of a molded line section equation of the fairing and a Von Karman molded line equation to serve as a deviation value h (x) = | f (x) -g (x) | of the two molded lines at the position of x;
and (5) integrating h (x) along the length direction of the fairing to obtain the accumulation of the deviation value of the two molded lines.
Preferably, the calculating the parameter value for obtaining the double-cone fairing profile with the profile deviation minimization as the optimization target includes:
and (3) optimizing the accumulated deviation values of the two molded lines by taking the characteristic parameters of the double-cone fairing as variables, and obtaining the parameter values of the molded lines of the double-cone fairing when the accumulated sum of the deviation values of the two molded lines is minimized.
Further, the optimization method for the cumulative deviation value of the two profiles comprises a Lagrange multiplier method and a genetic algorithm.
The invention has the beneficial effects that:
the invention provides a double-cone fairing contour line optimization design method based on a Von Karman contour line, which is characterized in that a fairing contour line section equation is constructed based on predefined characteristic parameters of a double-cone fairing; determining a deviation value between two molded lines based on a fairing molded line section equation and a Von Karman molded line equation established according to known structural parameters of the double-cone fairing; calculating the parameter value of the molded line of the double-cone fairing by taking the molded line deviation minimization as an optimization target; and finally, drawing a double-cone fairing molded line based on the parameter values, wherein the double-cone fairing molded line obtained by the scheme is most approximate to a Von Karman curve, can be obtained without depending on experience and a large amount of fluid simulation calculation, can take two factors of pneumatic characteristics and processing cost into consideration, overcomes the defect of poor pneumatic characteristics of the conventional double-cone molded line, and has the advantages of simple processing technology and superior pneumatic characteristics.
Drawings
In order to more clearly illustrate the detailed description of the invention or the technical solutions in the prior art, the drawings that are needed in the detailed description of the invention or the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
FIG. 1 is a flow chart of a method for optimally designing a double cone fairing shape wire based on a Von Karman shape wire according to an embodiment of the invention;
FIG. 2 is a schematic view of a mold line coordinate system for a fairing in accordance with an embodiment of the present invention;
FIG. 3 is a schematic view of a Von Karman profile system according to an embodiment of the present invention;
fig. 4 is a schematic diagram of coordinates of deviation values of two types of lines in a fairing profile segment equation and a von karman profile equation provided in an embodiment of the present invention.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only used as examples, and the protection scope of the present invention is not limited thereby.
It is to be noted that, unless otherwise specified, technical or scientific terms used herein shall have the ordinary meaning as understood by those skilled in the art to which the present invention belongs.
Example 1:
as shown in fig. 1, embodiment 1 provides a method for optimally designing a biconical fairing shape line based on Feng Ka portal shape line, and the specific method steps are as follows:
s1, constructing a fairing profile line section equation based on predefined double-cone fairing characteristic parameters;
s2, determining a deviation value between two molded lines based on the fairing molded line section equation and a Von Karman molded line equation established according to known structural parameters of the double-cone fairing;
s3, calculating a parameter value of the molded line of the double-cone fairing by taking the molded line deviation minimization as an optimization target;
and S4, drawing the molded line of the double-cone fairing based on the parameter values.
The double-cone fairing in the step S1 consists of a cone top and a double-cone section;
the characteristic parameters of the double-cone fairing include: the position (x 1, y 1) of the tangent point of the cone vertex arc and the first cone segment, and the position coordinates (x 2, y 2) of the junction point of the double cone segments, as shown in fig. 2;
the profile segment equation for the fairing is determined by:
y s ＝f(x s )
in the formula, x s As an axial coordinate, y s Is the radial coordinate of the fairing, f being y s And x s A double-cone fairing profile equation of functional relationship.
In the step S2, the known structural parameters of the double-cone fairing comprise the length L of the fairing, the diameter Rd of the rear end of the fairing and the tip end rounding radius rk; as shown in FIG. 3, the Von Karman type line equation established according to the known structural parameters of the double-cone fairing is as follows:
y k ＝g(x k )；
in the formula, x k As an axial coordinate, y k Is the radial coordinate of the fairing, g being y k And x k Functional relationship of von karman type line equation.
As shown in FIG. 4, determining a deviation value between two profiles based on a cowl profile segment equation and a Von Karman profile equation established from known structural parameters of a bi-cone cowl includes:
calculating the molded line absolute difference value of a molded line section equation of the fairing and a Von Karman molded line equation to serve as a deviation value h (x) = | f (x) -g (x) | of the two molded lines at the position of x;
and (5) integrating h (x) along the length direction of the fairing to obtain the accumulation of the deviation value of the two molded lines.
In step S3, calculating and obtaining parameter values of the molded lines of the biconical fairing by using the molded line deviation minimization as an optimization target includes:
and (3) optimizing the accumulated deviation values of the two molded lines by taking the characteristic parameters of the double-cone fairing as variables, and obtaining the parameter values of the molded lines of the double-cone fairing when the accumulated sum of the deviation values of the two molded lines is minimized. The optimization method for the accumulated deviation value of the two molded lines comprises a Lagrange multiplier method and a genetic algorithm.
Based on the same technical concept, the specific embodiment of the invention also provides a double-cone fairing line optimization design system based on Feng Ka door-shaped lines, which corresponds to embodiment 1, and the virtual system comprises:
the construction module is used for constructing a fairing profile line section equation based on the predefined characteristic parameters of the double-cone fairing;
the determining module is used for determining a deviation value between two molded lines based on the fairing molded line section equation and a Von Karman molded line equation established according to known structural parameters of the double-cone fairing;
the calculation module is used for calculating the parameter value of the molded line of the double-cone fairing by taking the molded line deviation minimization as an optimization target;
and the drawing module is used for drawing the double-cone fairing molded line based on the parameter value.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present application and not for limiting the protection scope thereof, and although the present application is described in detail with reference to the above embodiments, those of ordinary skill in the art should understand that: numerous variations, modifications, and equivalents will occur to those skilled in the art upon reading the present application and are within the scope of the claims appended hereto.
Claims (4)
1. A method for optimally designing a double-cone fairing profile based on a Von Karman profile, the method comprising:
constructing a fairing profile line section equation based on predefined characteristic parameters of the double-cone fairing;
determining a deviation value between two molded lines based on the fairing molded line section equation and a Von Karman molded line equation established according to known structural parameters of the double-cone fairing;
calculating characteristic parameter values of the molded line of the biconical fairing by using the minimized molded line deviation as an optimization target;
drawing a double-cone fairing profile based on the characteristic parameter values, wherein the double-cone fairing consists of a cone top and a double-cone section;
the characteristic parameters of the double-cone fairing comprise: the position coordinates (x 1, y 1) of the tangent point of the cone vertex arc and the first cone segment, and the position coordinates (x 2, y 2) of the junction point of the double cone segments,
the profile segment equation for the fairing is determined by:
y s ＝f(x s )
in the formula, x s As an axial coordinate, y s Is the radial coordinate of the fairing, f being the expression y s And x s The known structural parameters of the double-cone fairing comprise the length L of the fairing, the diameter Rd of the rear end of the fairing and the radius rk of a tip guide circle;
the von Karman type line equation established according to the known structure parameters of the double-cone fairing is as follows:
y k ＝g(x k )；
in the formula, x k As an axial coordinate, y k Is the radial coordinate of the fairing, g being y k And x k Functional relationship of von karman type line equation.
2. The method of claim 1, wherein determining the deviation value between the two profiles based on a cowl-type line segment equation and a von karman-type line equation established from known structural parameters of a bi-conical cowl comprises:
calculating the molded line absolute difference value of a molded line section equation of the fairing and a Von Karman molded line equation to serve as a deviation value h (x) = | f (x) -g (x) | of the two molded lines at the position of x;
and (5) integrating h (x) along the length direction of the fairing to obtain the accumulation of the deviation values of the two molded lines.
3. The method of claim 1, wherein calculating the characteristic parameter values for obtaining the bi-cone fairing profile with the profile deviation minimization as an optimization objective comprises:
and (3) optimizing the accumulated deviation values of the two molded lines by taking the characteristic parameters of the double-cone fairing as variables, and obtaining the characteristic parameter values of the molded lines of the double-cone fairing when the accumulated sum of the deviation values of the two molded lines is minimized.
4. The method of claim 3, wherein the optimization methods for the cumulative offset values for the two profiles include Lagrangian multiplier method and genetic algorithm.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8725470B1 (en) * | 2010-05-17 | 2014-05-13 | The United States of America as represented by the Administrator of the National Aeronautics & Space Administration (NASA) | Co-optimization of blunt body shapes for moving vehicles |
| CN105082556A (en) * | 2014-05-07 | 2015-11-25 | 上海航天设备制造总厂 | Von Karman shaped satellite fairing and moulding method thereof |
| CN108860571A (en) * | 2018-07-26 | 2018-11-23 | 成都飞机工业（集团）有限责任公司 | A kind of plane wing-body fairing and its construction method |
| CN208665528U (en) * | 2018-07-26 | 2019-03-29 | 成都飞机工业（集团）有限责任公司 | A kind of plane wing-body fairing |
| CN109606728A (en) * | 2019-01-24 | 2019-04-12 | 中国人民解放军国防科技大学 | Method and system for designing precursor of hypersonic aircraft |
| CN110188447A (en) * | 2019-05-24 | 2019-08-30 | 南昌航空大学 | The three-dimensional side of completely pneumatic transition turns oval Design of Inlet method |
| CN110589010A (en) * | 2019-09-09 | 2019-12-20 | 南京航空航天大学 | Hypersonic large-loading-space waverider design method |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2141617A1 (en) * | 2008-07-04 | 2010-01-06 | Dassault Systèmes S.A. | A computer-implemented method of design of surfaces defined by guiding curves. |
| CN104192302B (en) * | 2014-07-18 | 2015-08-12 | 中国人民解放军国防科学技术大学 | Based on the Waverider method of designing around tip Feng karman curve gyro-rotor benchmark flow field |
| CN109598081B (en) * | 2018-12-13 | 2020-11-10 | 西安交通大学 | Radial-flow turbine pneumatic optimization method based on data dimension reduction and multi-two-dimensional flow surface |
-
2021
- 2021-02-24 CN CN202110206013.4A patent/CN113032894B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8725470B1 (en) * | 2010-05-17 | 2014-05-13 | The United States of America as represented by the Administrator of the National Aeronautics & Space Administration (NASA) | Co-optimization of blunt body shapes for moving vehicles |
| CN105082556A (en) * | 2014-05-07 | 2015-11-25 | 上海航天设备制造总厂 | Von Karman shaped satellite fairing and moulding method thereof |
| CN108860571A (en) * | 2018-07-26 | 2018-11-23 | 成都飞机工业（集团）有限责任公司 | A kind of plane wing-body fairing and its construction method |
| CN208665528U (en) * | 2018-07-26 | 2019-03-29 | 成都飞机工业（集团）有限责任公司 | A kind of plane wing-body fairing |
| CN109606728A (en) * | 2019-01-24 | 2019-04-12 | 中国人民解放军国防科技大学 | Method and system for designing precursor of hypersonic aircraft |
| CN110188447A (en) * | 2019-05-24 | 2019-08-30 | 南昌航空大学 | The three-dimensional side of completely pneumatic transition turns oval Design of Inlet method |
| CN110589010A (en) * | 2019-09-09 | 2019-12-20 | 南京航空航天大学 | Hypersonic large-loading-space waverider design method |
Non-Patent Citations (5)
| Title |
|---|
| 基于NURBS方法的气动外形优化设计;侯粉等;《计算机工程与应用》;20081001;第44卷(第28期);第211-213、222页 * |
| 头罩前锥曲线对运载器性能的影响分析;马洋等;《固体火箭技术》;20130815;第36卷(第04期);第437-441页 * |
| 整流罩头部钝度比对运载火箭气动性能影响研究;闫指江等;《导弹与航天运载技术》;20200810(第04期);第39-42、48页 * |
| 旋成体导弹头部母线线型的选择问题研究;唐伟等;《空气动力学学报》;20100415;第28卷(第02期);第218-221页 * |
| 超音速光学导引头整流罩的形状优化;魏群等;《光学精密工程》;20100215;第18卷(第02期);第384-389页 * |
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