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新一代先进型格斗空空导弹都广泛采用了推力矢量控制系统(TVC),扰流片式推力矢量控制装置是实现这一功能的重要技术之一。本文利用气动力计算理论,研究扰流片产生的侧向控制力以及轴向推力损失,同时研究了扰流片伸入高度、阻塞面积、喷管扩张半角等因素的影响,得到了一些重要结论。
A new generation of advanced combat air-to-air missiles are widely used thrust vector control system (TVC), spoiler slice thrust vector control device is one of the important technologies to achieve this function. In this paper, the aerodynamic calculation theory is used to study the lateral control force and axial thrust loss of the spoiler, and the effects of spoiler height, blocking area and nozzle expansion half angle are studied. Some important conclusions are obtained .