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基于反馈线性化理论和简化的BTT导弹控制设计模型,在一定的假设条件下,提出了一种不存在零动力学的BTT导弹自动驾驶仪基本设计方法。该方法基于导弹动力学系数的名义值,适合于控制导弹作全空域飞行。仿真研究结果进一步验证了本文方法的正确性与有效性。
Based on feedback linearization theory and simplified BTT missile control design model, under certain assumptions, a basic design method of autopilot for BTT missile without zero dynamics is proposed. The method is based on the nominal value of the missile kinetic coefficient and is suitable for controlling the missile for full airspace flight. Simulation results further verify the correctness and effectiveness of the proposed method.