CN112199853B - Winged missile with steering engine bulge and bulge optimization design method thereof - Google Patents

Winged missile with steering engine bulge and bulge optimization design method thereof Download PDF

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Publication number
CN112199853B
CN112199853B CN202011137051.0A CN202011137051A CN112199853B CN 112199853 B CN112199853 B CN 112199853B CN 202011137051 A CN202011137051 A CN 202011137051A CN 112199853 B CN112199853 B CN 112199853B
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edge line
bulge
steering engine
curve
missile
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CN112199853A (en
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陈镜帆
范晓樯
陈俊杰
王翼
熊冰
刘俊兵
徐阳
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National University of Defense Technology
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National University of Defense Technology
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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
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06N—COMPUTING ARRANGEMENTS BASED ON SPECIFIC COMPUTATIONAL MODELS
    • G06N3/00—Computing arrangements based on biological models
    • G06N3/12—Computing arrangements based on biological models using genetic models
    • G06N3/126—Evolutionary algorithms, e.g. genetic algorithms or genetic programming
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2111/00—Details relating to CAD techniques
    • G06F2111/04—Constraint-based CAD
    • 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

Abstract

The invention discloses a winged missile with a steering engine bulge and an optimization design method of the bulge, wherein the method comprises the following steps: determining the size of the equal straight section based on the size of the empennage, and parameterizing a first edge line, a second edge line and a third edge line of the first side surface and the second side surface to obtain a parameterization curve of the first edge line, the second edge line and the third edge line of the first side surface and the second side surface; upgrading the three-dimensional configuration of the steering engine bulge based on the size of the equal straight section and the parameterized curves of the first edge line, the second edge line and the third edge line of the first side surface and the second side surface; and generating a grid based on three-dimensional formation of the steering engine bulge, performing simulation, and performing global iterative optimization by taking the pneumatic performance of the winged missile as a target. Provide the space for holding the steering wheel, avoid ground will "crowd" the inside valuable space of projectile body, avoid producing with the jet nozzle and interfere, improve the quantity of loading fuel, influence the range and other performances of guided missile.

Description

Winged missile with steering engine bulge and bulge optimization design method thereof
Technical Field
The invention relates to the technical field of design of winged missiles, in particular to a winged missile with a steering engine bulge and a bulge optimization design method thereof.
Background
The missile mainly depends on the aerodynamic force generated by the wing surface and the control surface to make maneuvering flight, and is called winged missile. Tactical cruise missiles and most tactical missiles, such as ground-air missiles, air-air missiles, ship-air missiles, shore-based missiles and the like, are winged missiles. It is characterized by good maneuverability, convenient control, capability of controlling both the active section and the passive section of the flight trajectory,
in order to control the deflection of the missile rudder surface or aileron, a device called a steering engine is needed. This device needs to be mounted inside the projectile body, which inevitably "crowds" valuable space inside the projectile body, especially for near-distance air-space missiles of inherently small size, which is a further problem, since the servo mechanism affects the mounting of other components within the missile, such as the nozzle or propellant, and affects the range and other properties of the missile.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides the winged missile with the steering engine bulge and the bulge optimization design method thereof, which provide space for accommodating the steering engine, avoid the steering engine from occupying valuable space in the missile body, avoid the interference between the steering engine and the tail nozzle, improve the quantity of loaded fuel, and further improve the range and other performances of the winged missile.
In order to achieve the purpose, the invention provides a winged missile with a steering engine bulge, which comprises a missile body and an empennage arranged at the tail part of the missile body, wherein the steering engine bulge is arranged at the tail part of the missile body, and the empennage is connected to the missile body through the steering engine bulge.
In one embodiment, the steering engine bulge comprises a bulge section and an equal straight section, the bulge section is of a cone-like structure, the equal straight section is of a cuboid-like structure, one end of the bulge section corresponding to a cone top is a head, and the other end of the bulge section is a tail; the head of the bulge section faces the head of the missile body, the tail of the bulge section is connected with the equal straight section, and the tail wing is arranged on the equal straight section.
In one embodiment, the drum packet section comprises a first top surface, a first side surface and a second side surface, wherein the first side surface and the second side surface are connected to the missile body and are symmetrical to each other; the equal straight section comprises a second top surface, a third side surface and a fourth side surface;
the first side surface is connected with the third side surface, and the second side surface is connected with the fourth side surface; part of the first side surface positioned in the head direction of the bulge section is fixedly connected with part of the second side surface, part of the first side surface positioned in the tail direction of the bulge section is connected with part of the second side surface through a first top surface, and the first top surface is connected with a second top surface; the empennage is vertically arranged on the second top surface.
In one embodiment, the first side surface and the second side surface are both arc surfaces, and the first top surface, the second top surface, the third side surface and the fourth side surface are all planes.
In one embodiment, the first side surface and the second side surface each include a first edge line, a second edge line, a third edge line and a fourth edge line, the first edge line of the first side surface and the first edge line of the second side surface are connected to the missile body, the second edge line of the first side surface is connected to the second edge line of the second side surface, the third edge line of the first side surface and the third edge line of the second side surface are connected to the first top surface, the fourth edge line of the first side surface is connected to the third side surface, and the fourth edge line of the second side surface is connected to the fourth side surface.
In one embodiment, the first edge line, the second edge line and the third edge line of the first side surface and the second side surface are spline curves or power curves or von karman curves.
In order to achieve the purpose, the invention also provides a bulge design method of the winged missile with the steering engine bulge, which comprises the following steps:
step 1, selecting a plurality of first control points, a plurality of second control points and a plurality of third control points based on the sizes of a steering engine and an empennage of a winged missile;
step 2, generating an initial curve of a first edge line by adopting a spline curve or power curve or von Karman curve generation method based on the first control point; generating an initial curve of a second edge line by adopting a spline curve or power curve or von Karman curve generation method based on the second control point; generating an initial curve of a third edge line by adopting a spline curve or power curve or von Karman curve generation method based on the third control point; the initial curve of the first edge line, the initial curve of the second edge line and the initial curve of the third edge line are sequentially connected end to end, and the head end of the initial curve of the first edge line is connected with the tail end of the initial curve of the third edge line to form the initial curve of the fourth edge line of the first side face;
step 3, obtaining an initial curved surface of the first side surface based on the initial curve of the first edge line, the initial curve of the second edge line, the initial curve of the third edge line and the initial curve of the fourth edge line, and intersecting the initial curved surface of the first side surface with the surface of the missile body based on the size of the steering engine to obtain a design curved surface of the first side surface;
step 4, obtaining a design curved surface of the second side surface based on the design curved surface of the first side surface, and obtaining a design curved surface of the first top surface based on the design curved surface of the first side surface and the design curved surface of the second side surface; combining the design curved surface of the first side surface, the design curved surface of the second side surface and the design curved surface of the first top surface with the size of the equal straight section determined by the size of the steering engine and the empennage of the winged missile to obtain the three-dimensional configuration of the steering engine bulge;
and 5, generating a grid based on the three-dimensional formation of the steering engine bulge, carrying out pneumatic performance simulation, and adjusting the coordinate values of the first control point, the second control point and the third control point by adopting an optimization algorithm until the simulated pneumatic performance is converged, thereby obtaining the optimal configuration of the steering engine bulge.
Compared with the prior art, the winged missile with the steering engine bulge and the bulge optimization design method thereof have the following beneficial effects:
1. the internal space of the beneficial missile is saved, the interference with the tail nozzle is avoided, the quantity of loaded fuel is increased, and the range and other performances of the missile are influenced.
2. The shape can be flexibly changed by using a bulge parameterization method, and the types of design space samples can be greatly enriched;
3. the other parts can be fully automatically finished only by inputting the incoming flow conditions and the basic size of the steering engine bulge, and finally the optimal configuration is obtained.
Drawings
In order to more clearly illustrate the embodiments or technical solutions of the present invention, the drawings used in the embodiments or technical solutions of the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a winged missile with a steering engine bulge in an embodiment of the invention;
FIG. 2 is a schematic flow chart of the method for designing the bulge of the winged missile with the steering engine bulge in the embodiment of the invention.
Reference numerals: the missile comprises a missile body 1, a tail wing 2, a steering engine bulge 3, a first top surface 4, a first side surface 5, a second side surface 6, a second top surface 7, a third side surface 8, a first edge line 9 of the first side surface, a second edge line 10 of the first side surface, a third edge line 11 of the first side surface and a fourth edge line 12 of the first side surface.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all directional indicators (such as up, down, left, right, front, and back \8230;) in the embodiments of the present invention are only used to explain the relative positional relationship between the components, the motion situation, etc. in a specific posture (as shown in the attached drawings), and if the specific posture is changed, the directional indicators are changed accordingly.
In addition, descriptions such as "first", "second", etc. in the present invention are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless explicitly specified otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
As shown in fig. 1, the winged missile with the steering engine bulge 3 disclosed in the embodiment comprises a missile body 1 and an empennage 2 arranged at the tail part of the missile body 1, wherein the steering engine bulge 3 is arranged at the tail part of the missile body 1, and the empennage 2 is connected to the missile body 1 through the steering engine bulge 3. Through the steering wheel bulge 3 of addding on guided missile main part 1, can provide the space for holding the steering wheel, not only avoided the steering wheel "crowded to account for" the inside valuable space of projectile body, still avoided steering wheel and tail nozzle to produce simultaneously and interfered, improve the quantity of loading fuel, and then promote the range and other performances of winged guided missile.
In the embodiment, in order to effectively maintain the pneumatic performance of the winged missile after the steering engine bulge 3 is additionally arranged, the steering engine bulge 3 is composed of a bulge section and an equal straight section. The bulge section is of a cone-like structure, the equal straight section is of a cuboid-like structure, one end, corresponding to a cone top, of the bulge section is a head, and the other end of the bulge section is a tail; the head of the bulge section faces the head of the missile body 1, the tail of the bulge section is connected with the equal straight section, and the tail wing 2 is arranged on the equal straight section.
Specifically, the bulge section comprises a first top surface 4, a first side surface 5 and a second side surface 6, wherein the first side surface 5 and the second side surface 6 are connected to the missile body 1 and are symmetrical to each other; the equal straight section comprises a second top surface 7, a third side surface 8 and a fourth side surface. The first side 5 is connected with the third side 8, and the second side 6 is connected with the fourth side; part of the first side surface 5 positioned in the head direction of the bulge section is fixedly connected with part of the second side surface 6, part of the first side surface 5 positioned in the tail direction of the bulge section is connected with part of the second side surface 6 through the first top surface 4, and the first top surface 4 is connected with the second top surface 7; the tail fin 2 is vertically arranged on the second top surface 7.
Preferably, the first side surface 5 and the second side surface 6 are both arc surfaces, and the first top surface 4, the second top surface 7, the third side surface 8 and the fourth side surface are all planes. The first side 5 and the second side 6 respectively comprise a first edge line, a second edge line, a third edge line and a fourth edge line, the first edge line 9 of the first side 5 and the first edge line of the second side 6 are connected with the missile main body 1, the second edge line 10 of the first side 5 is connected with the second edge line of the second side 6, the third edge line 11 of the first side 5 and the third edge line of the second side 6 are connected with the first top surface 4, the fourth edge line 12 of the first side 5 is connected with the third side 8, and the fourth edge line of the second side 6 is connected with the fourth side. The first edge line, the second edge line and the third edge line of the first side surface 5 and the second side surface 6 are spline curves, power curves or von karman curves. So that the first edge line, the second edge line and the third edge line of the first side surface 5 and the second side surface 6 can be subjected to parametric optimization design, and further, the winged missile with the steering engine bulge 3 is subjected to pneumatic optimization.
Referring to fig. 2, based on the winged missile with the steering engine bulge, the embodiment also discloses a bulge design method of the winged missile with the steering engine bulge, the bulge in the design method of the embodiment has two constraints, the first constraint is that a space between the bulge and the surface of the missile body can accommodate the steering engine, and the second constraint is that the equal straight section can be installed; according to the two constraints, the length, height and width of the drum packet section on the drum packet and the length, height and width of the equal straight section are directly obtained. For example, when the size of the tail wing is known, when the minimum distance between each contour line of the bottom of the tail wing and each contour line of the second top surface is 1cm when the tail wing is installed on the second top surface, the length and the width of the equal straight section can be determined due to the known size of the tail wing; and after the size of the steering engine is known, when the steering engine is installed in the bulge, the minimum distance between the steering engine and the bulge is limited to be 1cm, and the length, the width and the height of the bulge can be determined due to the fact that the size of the steering engine can be known, and then the length, the width and the height of the bulge section can be obtained through derivation. Wherein, the length direction is the axial direction of the winged missile, and the height direction is the radial direction of the winged missile.
After the length, the width and the height of the bulge section and the equal straight section are known, the bulge design method of the winged missile with the steering engine bulge in the embodiment specifically comprises the following steps:
step 1, selecting a plurality of first control points, a plurality of second control points and a plurality of third control points based on the sizes of a steering engine and an empennage of a winged missile, wherein the values of coordinate points of the first control points, the second control points and the third control points are all kept in a space constrained by the length, the width and the height of a bulge section;
step 2, carrying out parametric design on the first edge line, the second edge line and the third edge line, wherein the specific process is as follows: generating an initial curve of a first edge line by adopting a spline curve or power curve or von Karman curve generation method based on the first control point; generating an initial curve of a second edge line by adopting a spline curve or power curve or von Karman curve generation method based on the second control point; generating an initial curve of a third edge line by adopting a spline curve or power curve or von Karman curve generation method based on the third control point; the initial curve of the first edge line, the initial curve of the second edge line and the initial curve of the third edge line are sequentially connected end to end, and the head end of the initial curve of the first edge line is connected with the tail end of the initial curve of the third edge line to form the initial curve of the fourth edge line of the first side face; the generation method of the spline curve or the power curve or the von karman curve under the premise of knowing the coordinates of the control points is a conventional technical means of those skilled in the art, and therefore, the detailed description is omitted in this embodiment.
Step 3, obtaining an initial curved surface of the first side surface based on the initial curve of the first edge line, the initial curve of the second edge line, the initial curve of the third edge line and the initial curve of the fourth edge line, and intersecting the initial curved surface of the first side surface with the surface of the missile body based on the size of the steering engine to obtain a design curved surface of the first side surface;
step 4, obtaining a design curved surface of the second side surface based on the design curved surface of the first side surface, and obtaining a design curved surface of the first top surface based on the design curved surface of the first side surface and the design curved surface of the second side surface; combining the design curved surface of the first side surface, the design curved surface of the second side surface and the design curved surface of the first top surface with the size of an equal straight section determined by the size of a steering engine and a tail wing of a guided missile to obtain the three-dimensional configuration of a steering engine bulge;
and 5, generating a grid based on the three-dimensional formation of the steering engine bulge, carrying out pneumatic performance simulation, and adjusting the coordinate values of the first control point, the second control point and the third control point by adopting an optimization algorithm until the simulated pneumatic performance is converged, thereby obtaining the optimal configuration of the steering engine bulge. Wherein, the simulation software adopts Fluent. The optimization algorithm is a multi-island genetic algorithm, and has better global solving capability and calculation efficiency than the traditional genetic algorithm.
By designing the steering engine bulge by adopting the method in the embodiment, the resistance coefficient is reduced by about 5% under the condition of meeting the requirement of a precursor of a space for accommodating the steering engine, and the optimization effect is considerable for a hypersonic aircraft which must meet the demands of deci-centimetre.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.

Claims (1)

1. A bulge design method of a winged missile with a steering engine bulge is characterized in that the winged missile with the steering engine bulge comprises a missile body and an empennage arranged at the tail of the missile body, wherein the steering engine bulge is arranged at the tail of the missile body, and the empennage is connected to the missile body through the steering engine bulge;
the steering engine bulge comprises a bulge section and an equal straight section, the bulge section is of a cone-like structure, the equal straight section is of a cuboid-like structure, one end of the bulge section, corresponding to a cone top, is a head part, and the other end of the bulge section is a tail part; the head of the bulge section faces the head of the missile body, the tail of the bulge section is connected with the equal straight section, and the tail wing is arranged on the equal straight section;
the bulge section comprises a first top surface, a first side surface and a second side surface, and the first side surface and the second side surface are connected to the missile body and are symmetrical to each other; the equal straight section comprises a second top surface, a third side surface and a fourth side surface;
the first side surface is connected with the third side surface, and the second side surface is connected with the fourth side surface; part of the first side surface positioned in the head direction of the bulge section is fixedly connected with part of the second side surface, part of the first side surface positioned in the tail direction of the bulge section is connected with part of the second side surface through the first top surface, and the first top surface is connected with the second top surface; the tail wing is vertically arranged on the second top surface;
the first side surface and the second side surface are both cambered surfaces, and the first top surface, the second top surface, the third side surface and the fourth side surface are all planes;
the first edge line of the first side face and the first edge line of the second side face are connected with the missile body, the second edge line of the first side face is connected with the second edge line of the second side face, the third edge line of the first side face and the third edge line of the second side face are connected with the first top face, the fourth edge line of the first side face is connected with the third side face, and the fourth edge line of the second side face is connected with the fourth side face;
the bump design method comprises the following steps:
step 1, selecting a plurality of first control points, a plurality of second control points and a plurality of third control points based on the sizes of a steering engine and an empennage of a winged missile;
step 2, generating an initial curve of a first edge line by adopting a spline curve or power curve or von Karman curve generation method based on the first control point; generating an initial curve of a second edge line by adopting a spline curve or power curve or von Karman curve generation method based on the second control point; generating an initial curve of a third edge line by adopting a spline curve or power curve or von Karman curve generation method based on the third control point; the initial curve of the first edge line, the initial curve of the second edge line and the initial curve of the third edge line are sequentially connected end to end, and the head end of the initial curve of the first edge line is connected with the tail end of the initial curve of the third edge line to form the initial curve of the fourth edge line of the first side face;
step 3, obtaining an initial curved surface of the first side surface based on the initial curve of the first edge line, the initial curve of the second edge line, the initial curve of the third edge line and the initial curve of the fourth edge line, and intersecting the initial curved surface of the first side surface with the surface of the missile body based on the size of the steering engine to obtain a design curved surface of the first side surface;
step 4, obtaining a design curved surface of the second side surface based on the design curved surface of the first side surface, and obtaining a design curved surface of the first top surface based on the design curved surface of the first side surface and the design curved surface of the second side surface; combining the design curved surface of the first side surface, the design curved surface of the second side surface and the design curved surface of the first top surface with the size of an equal straight section determined by the size of a steering engine and a tail wing of a guided missile to obtain the three-dimensional configuration of a steering engine bulge;
and 5, generating a grid based on the three-dimensional formation of the steering engine bulge, carrying out pneumatic performance simulation, and adjusting the coordinate values of the first control point, the second control point and the third control point by adopting an optimization algorithm until the simulated pneumatic performance is converged, thereby obtaining the optimal configuration of the steering engine bulge.
CN202011137051.0A 2020-10-22 2020-10-22 Winged missile with steering engine bulge and bulge optimization design method thereof Active CN112199853B (en)

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CN113390302A (en) * 2021-06-16 2021-09-14 重庆航天工业有限公司 Combined navigation controller
CN113665837B (en) * 2021-09-23 2023-03-21 中国人民解放军国防科技大学 Method for designing pointed Von Karman curve steering engine bulge based on equal shock wave intensity of leading edge line
CN113665836B (en) * 2021-09-23 2023-03-21 中国人民解放军国防科技大学 Method for designing steering engine bulge based on sharp Von Karman curve of shock wave intensity of back edge line and the like
CN113665835B (en) * 2021-09-23 2023-03-21 中国人民解放军国防科技大学 Steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave
CN113682491B (en) * 2021-09-23 2023-03-21 中国人民解放军国防科技大学 Steering engine bulge design method based on back edge line equal shock wave intensity wedge guided wave

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