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导弹的控制能力是限制其制导控制系统性能指标的主要因素,如果未能充分考虑该因素的影响,会导致独立设计的制导律与姿态控制律的不匹配性,从而降低导弹初期设计工作的实用价值。考虑到最大可用舵偏角是再入段弹道导弹控制能力的一种直观体现,通过数学推导方式获得其解析表达式,并设计了与之对应的算法。利用风洞吹风试验数据,该算法可解算出一定飞行状态(包括高度、马赫数、攻角和侧滑角)下导弹各个舵的最大可用偏角,用于定点的静态分析或弹道的动态分析。借助于Matlab/Simulink计算机仿真手段,分析了某弹道内各个舵可用舵偏边界的变化规律,并绘制出相应的数据曲线,该曲线为导弹设计初期姿态控制系统的设计提供了约束条件和控制裕度的参考依据。
The control ability of missiles is the main factor to limit the performance of the guidance and control system. Failure to consider the influence of this factor will result in the incompatibility between the independently designed guidance law and the attitude control law, so as to reduce the practicality of the initial missile design work value. Considering that the maximum available rudder angle is an intuitive embodiment of reentry ballistic missile control ability, its analytical expression is obtained through mathematical derivation and its corresponding algorithm is designed. Using the wind tunnel blowing test data, the algorithm can calculate the maximum available declination of each rudder under a certain flight condition (including altitude, Mach number, angle of attack and side slip angle), static analysis for pointing or trajectory dynamic analysis . With the aid of Matlab / Simulink computer simulation method, the change rule of the available helm boundary of each rudder in a ballistic trajectory is analyzed, and the corresponding data curve is drawn. This curve provides the constraints and control margins for the design of the attitude control system Degree of reference.