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在气动力控制的寻的制导系统初步设计时,首先要在保证弹上耦合回路稳定的条件下,对制导系统和导弹的重要参数进行折衷,接着把制导系统简化为一个五阶的线性时变系统来分析,其中随机量对系统的影响用伴随法进行分析、计算。最终要求出该系统在系统误差和随机误差作用下的脱靶距离和需用过载。采用这种设计方法、并辅之以计算机辅助设计,可以大大减少初步设计的时间。
In the preliminary design of the guidance system for aerodynamic control, firstly, the important parameters of the guidance system and the missile should be compromised under the condition of ensuring the stability of the coupled loop on the missile, and then the guidance system is simplified into a fifth-order linear time-varying System to analyze, in which the amount of random impact on the system with the accompanying method of analysis, calculation. Finally, it is required to find out the system’s off-target distance and overload required by system error and random error. Using this design approach, complemented by computer-aided design, can greatly reduce the initial design time.