本文選題：高超聲速飛行器　切入點：本體-控制一體化　出處：《南京航空航天大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

【摘要】：通常飛行器的設(shè)計方法,特別在概念設(shè)計設(shè)計階段并沒有對控制系統(tǒng)設(shè)計予以考慮。這種設(shè)計方法可能會導(dǎo)致飛行器閉環(huán)控制系統(tǒng)的設(shè)計規(guī)格無法得到滿足,整個設(shè)計過程需要通過多次的迭代交替才能得到可行的飛行器本體和控制系統(tǒng)設(shè)計。高超聲速飛行器的氣動-推進-彈性耦合性使得其本體外形設(shè)計對其閉環(huán)控制系統(tǒng)設(shè)計有很大的影響。本文考慮了適用于高超聲速飛行器本體外形設(shè)計和控制系統(tǒng)設(shè)計的一體化優(yōu)化設(shè)計策略。通過在系統(tǒng)設(shè)計階段納入與控制相關(guān)的考慮因素,使用合理的策略減少本體系統(tǒng)-控制設(shè)計迭代次數(shù)。首先,本文描述了在本體-控制一體化設(shè)計中所需的優(yōu)化指標(biāo)和優(yōu)化方法,這些是后續(xù)章節(jié)展開研究的基礎(chǔ)。其次,建立了高超聲速飛行器動力學(xué)模型。利用高超聲速空氣動力學(xué)和準(zhǔn)一維瑞利流原理估算氣動力和發(fā)動機推力,將高超聲速飛行器等效成兩端自由的Euler-Bernoulli梁進行氣動彈性分析。進而分析了本體系統(tǒng)模型的非最小相位特性和不穩(wěn)定特性對閉環(huán)控制系統(tǒng)設(shè)計產(chǎn)生的影響,討論單個外形設(shè)計參數(shù)變化對本體設(shè)計指標(biāo)和控制系統(tǒng)設(shè)計指標(biāo)的影響。再次,針對本體-控制一體化設(shè)計建立了精確優(yōu)化和近似優(yōu)化問題,在這基礎(chǔ)上提出了適合于概念設(shè)計的迭代優(yōu)化框架。并進一步將迭代優(yōu)化框架中近似優(yōu)化問題轉(zhuǎn)化為BMI問題,可以使用BMI求解器作為核心優(yōu)化求解工具。但考慮到BMI問題求解的局限性,針對高超聲速飛行器本體-控制一體化設(shè)計應(yīng)用提出基于輔助變量的迭代算法和兩步迭代LMI算法作為BMI問題求解的替代算法。最后,針對高超聲速飛行器的一體化設(shè)計設(shè)計實例進行仿真分析,驗證所提方法的有效性。
[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.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V249.1;V221
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本文編號：1591248