【作者】 王娟利； 祁载康；

【Author】 WANG Juan-li, QI Zai-kang (Department of Flying Vehicle Engineering, Beijing Institute of Technology, Beijing 100081, China)

【机构】 北京理工大学机电工程学院；

【摘要】 在导弹控制系统设计过程中,考虑了自动驾驶仪的高频振荡问题,将其转化为系统的一个约束条件,同时把上升时间转化为目标函数,其他设计指标视为约束条件,采用有约束多目标优化的方法解决了系统鲁棒性设计问题。此方法解决了导弹控制系统设计过程中,由于气动参数拉偏导致控制器参数设计周期较长的问题,并且可以根据具体情况加入所需的约束,为工程设计提供了一种实用灵活有效的设计方法。更多还原

【Abstract】 To avoid high frequency oscillation in the course of autopilot design, damping coefficient value was treated as a constraint, the rise time was taken as objective, and the other performance criteria were taken as constraints, then the robustness design problem was solved by multi-objective optimization method. This design method offers a much better design than the traditional method, and it is of great usefulness and flexibleness in practical application.更多还原