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Control-relevant modeling and performance limitation analysis for flexible air-breathing hypersonic vehicles

机译：柔性呼吸超音速飞行器的与控制有关的建模和性能限制分析

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摘要

Overall design in many air-breathing hypersonic vehicles (AHSVs) uses the integrated airframe/scramjet configuration formed with elongated fuselage and light structure, resulting in intricate aerodynamic propulsive-elastic couplings. In this paper, a high-fidelity flexible AHSV dynamic modeling procedure is proposed at first, which consists of three main parts: i) panel method based aerodynamic modeling; ii) scramjet modeling; iii) finite-element-method (FEM) based aeroelastic modeling. Unsteady and viscous effects are estimated through linear piston theory and Eckert's reference temperature method, respectively. Additional models for shock interaction, ram-to-scram transition, and finite rate chemistry reaction are also included. To overcome the intractability of physics-based model, the Morris method is applied to identify the main influence factors during surrogate modeling. Then to investigate the flexible mode effect on the stability boundary, the principle of Null-controllability region (NCR) is employed, under control input saturation and bandwidth constraints.
机译：许多呼吸高超音速飞行器（AHSV）的总体设计使用一体式的机身/超燃冲压发动机构造，该构造具有细长的机身和轻巧的结构，从而形成了复杂的气动推进弹性耦合。本文首先提出了一种高保真，灵活的AHSV动态建模程序，该程序包括三个主要部分：i）基于面板方法的空气动力学建模； ii）超燃冲压模型； iii）基于有限元方法（FEM）的气动弹性建模。非稳态和粘性效应分别通过线性活塞理论和埃克特的参考温度方法估算。还包括其他模型，包括冲击相互作用，撞棒到撞棒过渡和有限速率化学反应。为了克服基于物理模型的难处理性，Morris方法用于识别代理建模过程中的主要影响因素。然后研究柔性模式对稳定边界的影响，在控制输入饱和和带宽约束条件下，采用零可控区域（NCR）的原理。

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