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根据吸气式高超声速目标的动力学特性,对传统动压加速度模型的局限性做了分析。在重力转弯模型框架中,基于超燃冲压发动机的推力产生机理以及高超声速流场的斜激波方程和普朗特梅叶方程,提出了描述目标切向加速度的推广模型和目标法向加速度的斜激波、非解析混合模型。随后,基于高超声速流场工程近似算法对吸气式高超声速目标的模式特征进行分析,并设计了均匀模型集。对攻角、滚转角以及发动机状态发生突变的高超声速机动目标跟踪问题进行了仿真研究。结果表明,新的模型集能够较好地适应目标突然加速和转弯机动,有效跟踪助推跳跃机动的吸气式高超声速目标。
According to the dynamic characteristics of the aspiration hypersonic target, the limitations of the traditional dynamic pressure acceleration model are analyzed. In the framework of gravity turning model, based on the thrust generation mechanism of scramjet and the diagonal shock wave equation and Planrat’s equation of hypersonic flow field, an extension model describing the target tangential acceleration and the target normal acceleration Oblique shock, non-analytic mixture model. Then, based on the hypersonic flow field approximation algorithm, the pattern characteristics of the aspirated hypersonic target were analyzed and the uniform model set was designed. The attack angle, roll angle and the state of the engine with mutation of the hypersonic maneuvering target tracking problem are simulated. The results show that the new model set can better adapt to the target sudden acceleration and turning maneuvers, and effectively track the aspirated hypersonic targets that assist the jump maneuvers.