CN114528634A - Pneumatic stealth optimization design method for elastic wings of high-stealth high-maneuvering layout aircraft - Google Patents

Pneumatic stealth optimization design method for elastic wings of high-stealth high-maneuvering layout aircraft Download PDF

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CN114528634A
CN114528634A CN202111673163.2A CN202111673163A CN114528634A CN 114528634 A CN114528634 A CN 114528634A CN 202111673163 A CN202111673163 A CN 202111673163A CN 114528634 A CN114528634 A CN 114528634A
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左林玄
刘艳
王泽宇
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Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
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Abstract

The application belongs to the field of aircraft design, and particularly relates to an elastic wing pneumatic stealth optimization design method of a high-stealth and high-maneuvering layout aircraft. The method comprises the following steps: step one, determining an optimization objective function; step two, determining constraint conditions; determining a design variable of the elastic wing shape by adopting an FFD shape parameterization method, and giving a feasibility interval of the design variable; step four, constructing a pneumatic calculation model, calculating to obtain a resistance coefficient of the elastic wing under the fixed lift coefficient, and taking a logarithm taking 10 as a base for the resistance coefficient; constructing an electromagnetic calculation model, and calculating to obtain an RCS value of the radar scattering area within the range of-40 degrees; and step five, determining the optimization direction of the design variable according to a gradient fast solving method based on the adjoint equation, adjusting the design variable, returning to the step three for iteration until the convergence condition is met, obtaining the final design variable, and determining the optimized appearance of the elastic wing according to the final design variable.

Description

Pneumatic stealth optimization design method for elastic wings of high-stealth high-maneuvering layout aircraft
Technical Field
The application belongs to the field of aircraft design, and particularly relates to an elastic wing pneumatic stealth optimization design method of a high-stealth and high-maneuvering layout aircraft.
Background
From the current research situation, a plurality of scholars in China deeply research the pneumatic stealth optimization method of the aircraft from various aspects such as pneumatic algorithm, stealth algorithm, optimization algorithm, agent model, stealth material and the like, and obtain corresponding achievements. However, there still exist some disadvantages, which are mainly reflected in: 1. the solver of the adopted flow field and electromagnetic field has low precision; 2. the optimization algorithm is difficult to process the optimization problem of large-scale design variables. The main reason is that gradient-free optimization algorithms such as genetic algorithm and particle swarm optimization are mainly adopted in the current pneumatic stealth optimization research. The algorithm has the advantages that the gradient of the objective function to the independent variable is not required to be solved, the overall optimal solution can be converged theoretically, and the multidisciplinary multi-objective optimization is easy to realize. However, the calculation amount is often large, and more iteration steps are needed to converge to the optimal value. Even if the proxy model is adopted to improve the optimization efficiency, the prediction accuracy of the proxy model is influenced by the number of design variables and the scale of sample points. Especially when the number of design variables is large, the number of sample points required for constructing the proxy model can reach thousands, that is, thousands of flow field calculations and electromagnetic field calculations are required. If a pneumatic solver and a stealth solver with higher precision are adopted, the calculated amount is considerable compared with that of a computer. The method is limited by computer hardware resources, a surface element method and a solving rapid potential equation which are high in solving speed and low in precision are mainly adopted in a pneumatic solver in the current research, and a stealth solver mainly adopts a physical optical method. Although the scholars adopt the Reynolds average N-S equation and the moment method to carry out the pneumatic stealth optimization, the method is only limited to the optimization of two-dimensional airfoil profiles and cannot be applied to the three-dimensional situation.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide an optimal design method for aerodynamic stealth of an elastic wing of an aircraft with a high stealth and high maneuvering layout, so as to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
a pneumatic stealth optimization design method for elastic wings of an aircraft with high stealth and high maneuvering layout comprises the following steps:
step one, determining an optimization objective function, specifically comprising:
determining that the optimization target of aerodynamic characteristics is that the resistance coefficient of the fixed lift coefficient after the wing elastically deforms is minimum;
determining that the optimized target of the electromagnetic property is the minimum mean value of the radar scattering area RCS within the range of-40 degrees;
taking logarithm with the resistance coefficient being 10 as a base, and then carrying out distribution weight superposition on the logarithm with the radar scattering area RCS mean value to obtain an optimized objective function;
step two, determining constraint conditions;
determining a design variable of the elastic wing shape by adopting an FFD shape parameterization method, and giving a feasibility interval of the design variable;
step four, constructing a pneumatic calculation model, calculating to obtain a resistance coefficient of the elastic wing under the fixed lift coefficient, and taking a logarithm with the resistance coefficient being 10 as a base;
constructing an electromagnetic calculation model, and calculating to obtain an RCS value of the radar scattering area within the range of-40 degrees;
and step five, determining the optimization direction of the design variable according to a gradient fast solving method based on the adjoint equation, adjusting the design variable, returning to the step three for iteration until the convergence condition is met, obtaining the final design variable, and determining the optimized appearance of the elastic wing according to the final design variable.
In at least one embodiment of the present application, in step two, the constraint condition includes: the method is characterized by comprising the following steps of corresponding to lift coefficient in subsonic cruising and supersonic cruising states, longitudinal instability of wings and airfoil thickness constraint of different chord-direction occupation.
In at least one embodiment of the present application, in step three, the design variables include airfoil leading edge radius, airfoil camber, and airfoil trailing edge angle.
In at least one embodiment of the present application, in step four, the electromagnetic calculation model is constructed using the quadrilateral-structured surface mesh.
In at least one embodiment of the present application, in step four, a multi-block structured grid and structured finite element method is used to construct an aerodynamic computational grid model and a structural linear solution model, and a resistance coefficient of the elastic wing under a fixed lift coefficient is obtained through CFD/CSD analysis and iterative solution.
In at least one embodiment of the present application, in step five, the convergence condition is that the variation of the design variable values obtained by two adjacent iterations is less than 10-6And the variation of the optimization objective function value is less than 10-6。
The invention has at least the following beneficial technical effects:
the method for optimally designing the aerodynamic stealth of the elastic wings of the high-stealth and high-mobility layout aircraft can improve the comprehensive performance of wing profile aerodynamics and stealth of the high-stealth and high-mobility layout aircraft, and the problem of long optimization time of a traditional optimization algorithm can be solved by the gradient-based method for solving the aerodynamic stealth of the elastic wings.
Drawings
FIG. 1 is a resistance coefficient change history according to an embodiment of the present application;
FIG. 2 is a RCS mean change history according to an embodiment of the present application;
FIG. 3 is a schematic comparison of an optimized fore-aft configuration of an elastomeric airfoil according to an embodiment of the present application;
FIG. 4 is a graphical representation of RCS values for different azimuths prior to optimization according to one embodiment of the present application;
FIG. 5 is a graph illustrating the RCS values of different optimized azimuths according to one embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. 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 application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 5.
The application provides a pneumatic stealth optimization design method for elastic wings of a high stealth and high maneuvering layout aircraft, which comprises the following steps:
step one, determining an optimization objective function, specifically comprising:
determining that the optimization target of aerodynamic characteristics is that the resistance coefficient of the fixed lift coefficient after the wing elastically deforms is minimum;
determining that the optimized target of the electromagnetic property is the minimum mean value of the radar scattering area RCS within the range of-40 degrees;
taking a logarithm taking the resistance coefficient as a base 10, and then carrying out distribution weight superposition on the logarithm taking the resistance coefficient and the radar scattering area RCS mean value to obtain an optimized objective function;
step two, determining constraint conditions;
in a preferred embodiment of the present application, in step two, the constraint condition includes: the method is characterized by comprising the following steps of corresponding to lift coefficient in subsonic cruising and supersonic cruising states, longitudinal instability of wings and airfoil thickness constraint of different chord-direction occupation.
Determining a design variable of the elastic wing shape by adopting an FFD (free deformation) shape parameterization method, and giving a feasibility interval of the design variable;
in this embodiment, in step three, the design variables include the airfoil leading edge radius, the airfoil camber, and the airfoil trailing edge angle.
Step four, constructing a pneumatic calculation model, calculating to obtain a resistance coefficient of the elastic wing under the fixed lift coefficient, and taking a logarithm with the resistance coefficient being 10 as a base;
constructing an electromagnetic calculation model, and calculating to obtain an RCS value of the radar scattering area within the range of-40 degrees;
in this embodiment, in the fourth step, an electromagnetic calculation model is constructed by using a quadrilateral surface mesh. And constructing a pneumatic computing grid model and a structural linear solving model by adopting a plurality of structural (hexahedral structural) grids and a structural finite element method, and obtaining the resistance coefficient of the elastic wing under the fixed lift coefficient through CFD/CSD analysis and iterative solving.
And step five, determining the optimization direction of the design variable according to a gradient fast solving method based on the adjoint equation, adjusting the design variable, returning to the step three for iteration until the convergence condition is met, obtaining the final design variable, and determining the optimized appearance of the elastic wing according to the final design variable.
In this embodiment, in step five, the convergence condition is that the variation of the design variable value obtained by two adjacent iterations is less than 10-6And the variation of the optimization objective function value is less than 10-6And the optimized objective function value can represent the comprehensive characteristics of stealth and aerodynamics of the elastic wing.
According to the method for the aerodynamic stealth optimization design of the elastic wings of the high-stealth high-maneuvering-layout aircraft, in an optimization example, in order to examine the cruising aerodynamic characteristics of the elastic wings, the lift coefficient after the aerodynamic/structural coupling solution is restrained to be unchanged, and for the method for the aerodynamic stealth optimization design of the elastic wings of the high-stealth high-maneuvering-layout aircraft, the lift coefficient is subjected to the aerodynamic/structural coupling solutionAdding geometric constraint to the parameterized control profile airfoil, and adding the airfoil thickness as constraint to the optimization design. The pitching moment constraint acts to limit the nose moment of the aircraft. Coefficient of resistance C in the course of optimizationDThe iterative change history of the RCS mean is shown in fig. 1 to 2. As can be seen from the airfoil variation shown in FIG. 3, the drag coefficient after optimization is reduced by 11counts and the RCS mean value is reduced by 4.5db relative to the initial configuration. The optimized wing leading edge radius is reduced and becomes a sharp leading edge.
According to the method for the aerodynamic stealth optimization design of the flexible wings of the high-stealth high-mobility layout aircraft, the aerodynamic stealth optimization design of the flexible wings of the high-stealth high-mobility layout aircraft is carried out by adopting an optimization algorithm based on an adjoint equation, and the whole optimization process comprises the steps of determining a target function, a constraint condition and a design variable and carrying out optimization calculation. For the design of the elastic wing of the airplane, the overall arrangement space, the aerodynamic characteristics and the stealth characteristics need to be comprehensively weighed, in order to comprehensively consider the three aspects, the aerodynamic characteristics and the electromagnetic characteristics after elastic influence are determined to be used as optimization targets, and the overall arrangement is used as an optimization strategy of geometric constraint. The application can effectively solve the problems of overall, pneumatic and stealth high coupling design of the wing airfoil of the high stealth high maneuvering aircraft, and solves the problem of unequal target functions among different disciplines by carrying out mathematical processing on the pneumatic characteristic and the electromagnetic characteristic after the elastic influence.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (6)

1. The utility model provides a high stealth high maneuvering overall arrangement aircraft's pneumatic stealth optimal design method of elasticity wing, its characterized in that includes:
step one, determining an optimization objective function, specifically comprising:
determining that the optimization target of aerodynamic characteristics is that the resistance coefficient of the fixed lift coefficient after the wing elastically deforms is minimum;
determining that the optimized target of the electromagnetic property is the minimum mean value of the radar scattering area RCS within the range of-40 degrees;
taking logarithm with the resistance coefficient being 10 as a base, and then carrying out distribution weight superposition on the logarithm with the radar scattering area RCS mean value to obtain an optimized objective function;
step two, determining constraint conditions;
determining a design variable of the elastic wing shape by adopting an FFD shape parameterization method, and giving a feasibility interval of the design variable;
step four, constructing a pneumatic calculation model, calculating to obtain a resistance coefficient of the elastic wing under the fixed lift coefficient, and taking a logarithm with the resistance coefficient being 10 as a base;
constructing an electromagnetic calculation model, and calculating to obtain an RCS value of the radar scattering area within the range of-40 degrees;
and step five, determining the optimization direction of the design variable according to a gradient fast solving method based on the adjoint equation, adjusting the design variable, returning to the step three for iteration until the convergence condition is met, obtaining the final design variable, and determining the optimized appearance of the elastic wing according to the final design variable.
2. The aerodynamic stealth optimization design method for the flexible wings of the high-stealth high-mobility layout aircraft according to claim 1, wherein in the second step, the constraint conditions include: the method is characterized by comprising the following steps of corresponding to lift coefficients in subsonic cruise and supersonic cruise states, longitudinal instability of wings and airfoil thickness constraints occupied by different chord directions.
3. The aerodynamic stealth optimization design method for the flexible wings of the high-stealth high-maneuvering layout aircraft according to claim 2, characterized in that in the third step, the design variables comprise airfoil leading edge radius, airfoil camber and airfoil trailing edge included angle.
4. The aerodynamic stealth optimization design method for the flexible wings of the high-stealth high-maneuvering layout aircraft according to claim 3, characterized in that in the fourth step, an electromagnetic calculation model is constructed by using a quadrilateral-structured surface mesh.
5. The aerodynamic stealth optimization design method for the flexible wings of the high-stealth high-maneuvering layout aircraft according to claim 4, characterized in that in the fourth step, a plurality of structural grids and structural finite element methods are adopted to construct an aerodynamic computational grid model and a structural linear solution model, and a resistance coefficient of the flexible wings under a fixed lift coefficient is obtained through CFD/CSD analysis and iterative solution.
6. The aerodynamic stealth optimization design method for the flexible wings of the high-stealth high-maneuvering layout aircraft according to claim 5, wherein in the fifth step, the convergence condition is that the variation of the design variable value obtained by two adjacent iterations is less than 10-6And the variation of the optimization objective function value is less than 10-6。
CN202111673163.2A 2021-12-31 2021-12-31 Pneumatic stealth optimization design method for elastic wings of high-stealth high-maneuvering layout aircraft Pending CN114528634A (en)

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Cited By (7)

* Cited by examiner, † Cited by third party
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CN114996840A (en) * 2022-05-25 2022-09-02 中国航发沈阳发动机研究所 Parameter optimization method for double-ring control receiving and expanding spray pipe adjusting mechanism
CN115092414A (en) * 2022-07-05 2022-09-23 中国人民解放军国防科技大学 Ring control airfoil pneumatic and electromagnetic stealth combined optimization method
CN115859483A (en) * 2023-02-16 2023-03-28 中国空气动力研究与发展中心空天技术研究所 Material distribution position optimization design method based on Maxwell Wei Fangfa adjoint equation
CN116702310A (en) * 2023-04-23 2023-09-05 中国航空工业集团公司沈阳飞机设计研究所 Wing trailing edge design method and system based on Gaussian curve
CN117634334A (en) * 2023-10-27 2024-03-01 西北工业大学 Fighter aircraft wing profile optimization design method considering pneumatic/stealth and wide-speed-domain wing profile family
CN117910140A (en) * 2024-01-23 2024-04-19 西北工业大学 Aircraft pneumatic electromagnetic coupling optimization design method for generating countermeasure network based on mixed condition
CN117993105A (en) * 2024-02-26 2024-05-07 南京航空航天大学 Method for designing aerodynamic profile of flying wing layout aircraft based on sharp leading edge airfoil

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114996840A (en) * 2022-05-25 2022-09-02 中国航发沈阳发动机研究所 Parameter optimization method for double-ring control receiving and expanding spray pipe adjusting mechanism
CN115092414A (en) * 2022-07-05 2022-09-23 中国人民解放军国防科技大学 Ring control airfoil pneumatic and electromagnetic stealth combined optimization method
CN115092414B (en) * 2022-07-05 2024-02-02 中国人民解放军国防科技大学 Annular quantity control airfoil pneumatic and electromagnetic stealth combined optimization method
CN115859483A (en) * 2023-02-16 2023-03-28 中国空气动力研究与发展中心空天技术研究所 Material distribution position optimization design method based on Maxwell Wei Fangfa adjoint equation
CN116702310A (en) * 2023-04-23 2023-09-05 中国航空工业集团公司沈阳飞机设计研究所 Wing trailing edge design method and system based on Gaussian curve
CN116702310B (en) * 2023-04-23 2024-03-26 中国航空工业集团公司沈阳飞机设计研究所 Wing trailing edge design method and system based on Gaussian curve
CN117634334A (en) * 2023-10-27 2024-03-01 西北工业大学 Fighter aircraft wing profile optimization design method considering pneumatic/stealth and wide-speed-domain wing profile family
CN117910140A (en) * 2024-01-23 2024-04-19 西北工业大学 Aircraft pneumatic electromagnetic coupling optimization design method for generating countermeasure network based on mixed condition
CN117993105A (en) * 2024-02-26 2024-05-07 南京航空航天大学 Method for designing aerodynamic profile of flying wing layout aircraft based on sharp leading edge airfoil
CN117993105B (en) * 2024-02-26 2024-08-20 南京航空航天大学 Method for designing aerodynamic profile of flying wing layout aircraft based on sharp leading edge airfoil

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