直升机总体优化设计技术研究
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摘要
本文研究数据库技术和多目标、多学科优化技术在直升机总体设计中的应用。
随着航空技术的迅猛发展和系统的日趋复杂，现代飞行器的设计理念和设计模式都发生了重大变化，从追求飞行性能发展到追求系统综合使用效能，从串行迭代的设计模式发展到集成并行设计模式。同时，飞行器的初期设计阶段即概念设计和初步设计阶段变得越来越重要。直升机总体设计面临的是一个庞大又复杂的系统，总体设计对研制工作具有全局性的影响，是直升机研制工作最重要的一个阶段。本文针对直升机总体设计的特点和多学科本质，开展了直升机总体数据库和人工神经网络技术在直升机概念设计阶段的应用研究，并建立了多学科设计优化框架，集成了与直升机总体设计相关的多个学科分析模型，进行了多学科设计优化技术在直升机初步设计阶段的应用研究。本文主要研究内容如下：
构建了直升机总体参数数据库和部件重量数据库，完成了数据的筛选、录入和修正，并基于数据库提出了回归统计分析法和人工神经网络响应面法的直升机概念设计方法，通过对重量、旋翼、尾桨、机身以及功率等参数的分析，给出了一套用于确定直升机总体参数的简化计算方法及神经网络模型。
建立了适合直升机总体参数优化设计的飞行性能计算模型，分析了包括悬停性能、爬升性能和前飞性能在内的基本飞行性能；并在遗传算法中引入了序和密度的概念，以及实数编码、锦标赛选择、精英保留策略、自适应算子等求解策略，经过改进的多目标遗传算法在求解Pareto解集时表现出更好的贴近性、均匀性和完整性；采用改进的遗传算法对直升机飞行性能进行多目标优化，提高了优化效率和决策的准确性。
建立了适合桨叶外形优化设计的自由尾迹模型，该模型采用Weissinger-L升力面模型和PIPC求解方法，使得计算精度能满足总体设计阶段桨叶气动外形对性能影响的要求，又具有较少的计算耗时；以减少悬停和前飞状态下旋翼的需用功率为优化目标，采用改进的多目标遗传算法，同时在算法中加入并行运算技术和人工神经网络代理模型，进一步缩短了优化时间，提高了优化效率和优化质量。
在建立和验证直升机重量估算、飞行性能、桨叶气动外形、操纵稳定性和机动性学科分析模型的基础上，分析了各学科之间的数据传递和耦合关系，确定设计变量、设计约束和优化目标，建立了直升机总体多学科设计优化模型。
针对直升机总体多学科设计优化的特点和常规协同优化方法的收敛性差、计算时间长等缺陷，提出了基于代理模型的直升机总体参数多目标协同优化方法，并以UH-60A直升机为算例，与多学科可行法进行对比，验证了该优化方法的可行性和有效性。最后以AH-64武装直升机为背景样机，按照任务设计要求进行概念设计，给出武装直升机总体初步设计参数，并以此为基础，进行以“作战效能指标”为综合优化目标的总体多学科设计优化。优化结果验证了多目标协同优化方法应用于实际工程设计的可行性和有效性。本文建立的直升机总体多学科设计优化框架和优化策略可以应用于直升机总体参数综合优化设计，并有效提高了设计效率和设计质量。
The application of Database and Multi-Objective/Multidisciplinary Design Optimization tohelicopter conceptual/preliminary design is researched in this thesis.
As the rapid development of aviation technology and the growing complexity of aerial systems,the concept and patterns of modern aircraft design have a great change that from focusing on flightperformances to focusing on the aircraft system effectiveness, from serial/iterative design pattern toparallel/integrative design pattern. Meanwhile, the early stage of aircraft design such as conceptualdesign and preliminary design is getting more and more important. Helicopter is a large complexsystem and conceptual design is the most important stage in helicopter research as it has an overallinfluence. According to the features and Multidisciplinary connection of helicopter preliminary design,the application of Helicopter Preliminary Parameter Database and Artificial Neural Networks tohelicopter conceptual design stage is researched, and the Multidisciplinary Design OptimizationFramework integrating with several subsystem analytical models is established to explore the efficacyof Multidisciplinary Design Optimization to helicopter preliminary design stage. The main contents ofthe thesis are as followings.
The Helicopter Preliminary Parameter Database and Group Weight Database are built to collectmost helicopters in the world. After the selection, input and fixing data, a helicopter concept designmethod based on Regression Analysis and Artificial Neural Networks is established to analysis theparameters of group weights, main rotor, tail rotor, fuselage and power plant. A set of simplifiedalgorithms and neural networks are obtained to estimate helicopter overall parameters.
The model of flight performance suitable for helicopter preliminary parameter optimization is setup to analysis the helicopter basic flight performance including hover, climb and level flight. Animproved rank-density-based multi-objective genetic algorithm with solution strategies such asreal-coded, tournament selection, elitism preservation and adaptive operators is developed to find anear-optimal, near-complete, uniformly distributed Pareto front. Based on this genetic algorithm,helicopter model of flight performance is optimized with a set of optimal solutions to helpdecision-making efficiently and accurately.
A free wake model with Wessinger-L lifting surface and PIPC solution is set up with anappropriate precision in blade aerodynamic shape optimization and the less time consuming at thepreliminary design stage. As the optimization goal of minimizing the rotor required power in bothhover and level flight status, parallel computing technology and surrogate model of neural networks are applied to the improved multi-objective genetic algorithm to reduce time consuming and improvethe efficiency and quality.
Based on the establishment and validation of helicopter group weight, flight performance, rotoraerodynamic shape, stability and control and maneuverability, the data flow and connections areanalyzed and the helicopter conceptual/preliminary multidisciplinary design optimization model is setup.
As the characteristics of helicopter conceptual/preliminary multidisciplinary design optimizationmodel and the bad convergence and large computation of regular collaborative optimization method,the Multi-Objective Collaborative Optimization method with surrogate model is presented in thisthesis. UH-60A helicopter is taken as the example to show the feasibility and effectiveness comparingwith multidisciplinary feasible method. Finally, referring to AH-64attack helicopter, conceptualdesign of a new attack helicopter is undertaken according to the design requirements. Based on thisconceptual design, helicopter preliminary multidisciplinary design optimization with CombatEfficiency Index as the composite indicator is carried out. The results show that the helicopterconceptual/preliminary multidisciplinary design optimization framework can be effectively applied tooptimize helicopter design parameters, able to improve efficiency and quality.
随着航空技术的迅猛发展和系统的日趋复杂，现代飞行器的设计理念和设计模式都发生了重大变化，从追求飞行性能发展到追求系统综合使用效能，从串行迭代的设计模式发展到集成并行设计模式。同时，飞行器的初期设计阶段即概念设计和初步设计阶段变得越来越重要。直升机总体设计面临的是一个庞大又复杂的系统，总体设计对研制工作具有全局性的影响，是直升机研制工作最重要的一个阶段。本文针对直升机总体设计的特点和多学科本质，开展了直升机总体数据库和人工神经网络技术在直升机概念设计阶段的应用研究，并建立了多学科设计优化框架，集成了与直升机总体设计相关的多个学科分析模型，进行了多学科设计优化技术在直升机初步设计阶段的应用研究。本文主要研究内容如下：
构建了直升机总体参数数据库和部件重量数据库，完成了数据的筛选、录入和修正，并基于数据库提出了回归统计分析法和人工神经网络响应面法的直升机概念设计方法，通过对重量、旋翼、尾桨、机身以及功率等参数的分析，给出了一套用于确定直升机总体参数的简化计算方法及神经网络模型。
建立了适合直升机总体参数优化设计的飞行性能计算模型，分析了包括悬停性能、爬升性能和前飞性能在内的基本飞行性能；并在遗传算法中引入了序和密度的概念，以及实数编码、锦标赛选择、精英保留策略、自适应算子等求解策略，经过改进的多目标遗传算法在求解Pareto解集时表现出更好的贴近性、均匀性和完整性；采用改进的遗传算法对直升机飞行性能进行多目标优化，提高了优化效率和决策的准确性。
建立了适合桨叶外形优化设计的自由尾迹模型，该模型采用Weissinger-L升力面模型和PIPC求解方法，使得计算精度能满足总体设计阶段桨叶气动外形对性能影响的要求，又具有较少的计算耗时；以减少悬停和前飞状态下旋翼的需用功率为优化目标，采用改进的多目标遗传算法，同时在算法中加入并行运算技术和人工神经网络代理模型，进一步缩短了优化时间，提高了优化效率和优化质量。
在建立和验证直升机重量估算、飞行性能、桨叶气动外形、操纵稳定性和机动性学科分析模型的基础上，分析了各学科之间的数据传递和耦合关系，确定设计变量、设计约束和优化目标，建立了直升机总体多学科设计优化模型。
针对直升机总体多学科设计优化的特点和常规协同优化方法的收敛性差、计算时间长等缺陷，提出了基于代理模型的直升机总体参数多目标协同优化方法，并以UH-60A直升机为算例，与多学科可行法进行对比，验证了该优化方法的可行性和有效性。最后以AH-64武装直升机为背景样机，按照任务设计要求进行概念设计，给出武装直升机总体初步设计参数，并以此为基础，进行以“作战效能指标”为综合优化目标的总体多学科设计优化。优化结果验证了多目标协同优化方法应用于实际工程设计的可行性和有效性。本文建立的直升机总体多学科设计优化框架和优化策略可以应用于直升机总体参数综合优化设计，并有效提高了设计效率和设计质量。
The application of Database and Multi-Objective/Multidisciplinary Design Optimization tohelicopter conceptual/preliminary design is researched in this thesis.
As the rapid development of aviation technology and the growing complexity of aerial systems,the concept and patterns of modern aircraft design have a great change that from focusing on flightperformances to focusing on the aircraft system effectiveness, from serial/iterative design pattern toparallel/integrative design pattern. Meanwhile, the early stage of aircraft design such as conceptualdesign and preliminary design is getting more and more important. Helicopter is a large complexsystem and conceptual design is the most important stage in helicopter research as it has an overallinfluence. According to the features and Multidisciplinary connection of helicopter preliminary design,the application of Helicopter Preliminary Parameter Database and Artificial Neural Networks tohelicopter conceptual design stage is researched, and the Multidisciplinary Design OptimizationFramework integrating with several subsystem analytical models is established to explore the efficacyof Multidisciplinary Design Optimization to helicopter preliminary design stage. The main contents ofthe thesis are as followings.
The Helicopter Preliminary Parameter Database and Group Weight Database are built to collectmost helicopters in the world. After the selection, input and fixing data, a helicopter concept designmethod based on Regression Analysis and Artificial Neural Networks is established to analysis theparameters of group weights, main rotor, tail rotor, fuselage and power plant. A set of simplifiedalgorithms and neural networks are obtained to estimate helicopter overall parameters.
The model of flight performance suitable for helicopter preliminary parameter optimization is setup to analysis the helicopter basic flight performance including hover, climb and level flight. Animproved rank-density-based multi-objective genetic algorithm with solution strategies such asreal-coded, tournament selection, elitism preservation and adaptive operators is developed to find anear-optimal, near-complete, uniformly distributed Pareto front. Based on this genetic algorithm,helicopter model of flight performance is optimized with a set of optimal solutions to helpdecision-making efficiently and accurately.
A free wake model with Wessinger-L lifting surface and PIPC solution is set up with anappropriate precision in blade aerodynamic shape optimization and the less time consuming at thepreliminary design stage. As the optimization goal of minimizing the rotor required power in bothhover and level flight status, parallel computing technology and surrogate model of neural networks are applied to the improved multi-objective genetic algorithm to reduce time consuming and improvethe efficiency and quality.
Based on the establishment and validation of helicopter group weight, flight performance, rotoraerodynamic shape, stability and control and maneuverability, the data flow and connections areanalyzed and the helicopter conceptual/preliminary multidisciplinary design optimization model is setup.
As the characteristics of helicopter conceptual/preliminary multidisciplinary design optimizationmodel and the bad convergence and large computation of regular collaborative optimization method,the Multi-Objective Collaborative Optimization method with surrogate model is presented in thisthesis. UH-60A helicopter is taken as the example to show the feasibility and effectiveness comparingwith multidisciplinary feasible method. Finally, referring to AH-64attack helicopter, conceptualdesign of a new attack helicopter is undertaken according to the design requirements. Based on thisconceptual design, helicopter preliminary multidisciplinary design optimization with CombatEfficiency Index as the composite indicator is carried out. The results show that the helicopterconceptual/preliminary multidisciplinary design optimization framework can be effectively applied tooptimize helicopter design parameters, able to improve efficiency and quality.
引文
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