高超声速飞行器本体—控制一体化设计的优化方法研究

发布时间：2018-03-10 02:02

  本文选题：高超声速飞行器　切入点：本体-控制一体化　出处：《南京航空航天大学》2016年硕士论文　论文类型：学位论文

【摘要】：通常飞行器的设计方法,特别在概念设计设计阶段并没有对控制系统设计予以考虑。这种设计方法可能会导致飞行器闭环控制系统的设计规格无法得到满足,整个设计过程需要通过多次的迭代交替才能得到可行的飞行器本体和控制系统设计。高超声速飞行器的气动-推进-弹性耦合性使得其本体外形设计对其闭环控制系统设计有很大的影响。本文考虑了适用于高超声速飞行器本体外形设计和控制系统设计的一体化优化设计策略。通过在系统设计阶段纳入与控制相关的考虑因素,使用合理的策略减少本体系统-控制设计迭代次数。首先,本文描述了在本体-控制一体化设计中所需的优化指标和优化方法,这些是后续章节展开研究的基础。其次,建立了高超声速飞行器动力学模型。利用高超声速空气动力学和准一维瑞利流原理估算气动力和发动机推力,将高超声速飞行器等效成两端自由的Euler-Bernoulli梁进行气动弹性分析。进而分析了本体系统模型的非最小相位特性和不稳定特性对闭环控制系统设计产生的影响,讨论单个外形设计参数变化对本体设计指标和控制系统设计指标的影响。再次,针对本体-控制一体化设计建立了精确优化和近似优化问题,在这基础上提出了适合于概念设计的迭代优化框架。并进一步将迭代优化框架中近似优化问题转化为BMI问题,可以使用BMI求解器作为核心优化求解工具。但考虑到BMI问题求解的局限性,针对高超声速飞行器本体-控制一体化设计应用提出基于辅助变量的迭代算法和两步迭代LMI算法作为BMI问题求解的替代算法。最后,针对高超声速飞行器的一体化设计设计实例进行仿真分析,验证所提方法的有效性。
[Abstract]:In general, the design method of aircraft, especially in the conceptual design stage, does not consider the design of the control system. This design method may lead to the failure of the design specification of the closed-loop control system of the aircraft. The whole design process needs several iterations alternately to obtain the feasible design of the aircraft body and control system. The aerodynamic propulsion-elastic coupling of hypersonic vehicle makes its body shape design to control it in closed loop. The design of the system has a great influence. In this paper, an integrated optimization design strategy for the design of the body shape and the control system of hypersonic vehicle is considered. The factors related to the control are taken into account in the design phase of the system. Reasonable strategies are used to reduce the number of iterations in ontology system-control design. Firstly, this paper describes the optimization indexes and optimization methods needed in ontology-control integrated design, which are the basis of the following chapters. The hypersonic aerodynamics and quasi-one-dimensional Rayleigh flow principle are used to estimate aerodynamic force and engine thrust. The hypersonic vehicle is equivalent to a free-end Euler-Bernoulli beam for Aeroelastic analysis. Furthermore, the influence of the non-minimum phase and unstable characteristics of the bulk system model on the design of the closed-loop control system is analyzed. The influence of individual shape design parameters on ontology design index and control system design index is discussed. Thirdly, the precise optimization and approximate optimization problems are established for ontology-control integrated design. On this basis, an iterative optimization framework suitable for conceptual design is proposed, and the approximate optimization problem in the iterative optimization framework is further transformed into a BMI problem. BMI solver can be used as the core optimization tool, but considering the limitations of BMI problem solving, An iterative algorithm based on auxiliary variables and a two-step iterative LMI algorithm are proposed for the integrated design of supersonic aircraft ontology-control. Finally, the two-step iterative LMI algorithm is used as the alternative algorithm for solving the BMI problem. The simulation analysis of the integrated design of hypersonic vehicle is carried out to verify the effectiveness of the proposed method.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V249.1;V221
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本文编号：1591248