高超声速飞行器跨流域动态稳定性问题及其预测方法研究

There appears to be two new features about a main developing direction for new generation hypersonic vehicles. One is that in pursuit of high lift-to-drag ratio, the aerodynamic layouts are tending to be designed flatter and the control surfaces are reduced or removed, which leads to the decease of direction stability. The other is that to satisfy the requirements of both the heat-protection and the aerodynamic effectiveness, the trajectories are designed to be long-time flight or maneuvering in the trans-flow-regimes. In this case the dynamic stability problem becomes outstanding, mainly represented in the contradiction between the high lift-to-drag ratio aerodynamic layout and the stability and controllability in trans-regime flight conditions. This project is planned to aim at the fundamental aerodynamic problems and requirements of engineering application about the dynamic characteristics of hypersonic high lift-to-drag ratio configurations in trans-regime flight conditions, to develop prediction methods for dynamic derivatives based on dynamic slip boundary conditions and high efficiency harmonic balance algorithm, to conduct the investigation of simulation and identification methods of cross derivatives in trans-regime flight conditions based on complex coupling simulation motion types, and to explore the evolution law of characteristics with parameters, the judging criteria of stability and corresponding flow mechanism of hypersonic high lift-to-drag ratio vehicles undergoing pitch, roll, and pitch/roll coupling motions in trans-regime flows. This could provide with technical support for the design of new generation hypersonic vehicles of our country.

新一代高超声速飞行器一类主要的发展方向呈现两个新特征：一是为追求高升阻比，布局设计趋于扁平、减小或去除控制面，导致方向稳定性降低；二是为兼顾防热和气动效率，弹道设计在跨流域长时间滑翔飞行或机动飞行。此种情况下，跨流域动稳定性问题就变得极为突出，主要表现为跨流域高升阻比气动布局与稳定性和操纵性的矛盾难以协调。本项目拟针对高超声速高升阻比飞行器跨流域动态特性气动基础问题和工程应用需求，发展基于动态滑移边界条件和谐波平衡高效算法的跨流域动导数预测方法，研究基于复杂耦合模拟运动形式的跨流域交叉导数模拟辨识方法，提升现有飞行器动态特性预测软件对跨流域动稳定性问题研究的适用性，探索典型高超声速高升阻比飞行器跨流域俯仰、滚转及俯仰/滚转耦合运动的动态特性随参数演化规律、稳定性判据及相应的流动机理，为我国自主创新发展新一代高超声速飞行提供理论与技术支持。

新一代高超声速飞行器一类主要的发展方向呈现两个新特征：一是为追求高升阻比，布局设计趋于扁平、减小或去除控制面，导致方向稳定性降低；二是为兼顾防热和气动效率，弹道设计在跨流域长时间滑翔飞行或机动飞行。此种情况下，跨流域动稳定性问题就变得极为突出，主要表现为跨流域高升阻比气动布局与稳定性和操纵性的矛盾难以协调。本项目拟针对高超声速高升阻比飞行器跨流域动态特性气动基础问题和工程应用需求，完成了动态滑移边界条件处理技术研究，动态跨流域计算软件发展，与高超声速谐波平衡法及交叉导数计算辨识方法研究。在跨流域问题研究中针对性地增加探索了适用于跨流域计算的Boltzmann/N-S耦合数值模拟方法探索研究与算例考核。但在将谐波平衡法推广应用于两自由度运动的研究中，没能取得实质进展。发表相关学术论文11篇，其中EI引用5篇。可为我国自主创新发展新一代高超声速飞行提供理论与技术支持。