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战术导弹的飞行动力学特性随导弹飞行高度不同而急剧变化,导弹飞行控制系统的各种参数在飞行过程中必须进行在线调整,以适应导弹动力学特性的变化。本文在对现有某型地空导弹飞行控制系统进行全面仿真的基础上,根据新的性能指标要求,应用模型参考自适应控制理论导出了自适应规律,完成了方案设计。全弹道飞行仿真表明,新的飞行控制系统比原系统有很大改进,可满足高、中、低不同高度飞行性能指标的要求,且具有较好的抗干扰能力,为新型导弹控制系统提供了依据。
Tactical missile flight dynamics with the rapid changes in missile altitude and the rapid changes in the various parameters of the missile flight control system must be online during the flight adjustment to meet the dynamic characteristics of the missile changes. Based on the full simulation of the existing flight control system of a certain SAM, according to the requirement of new performance index, the adaptive rule is derived by using the model reference adaptive control theory and the scheme design is completed. Full-ballistic flight simulation shows that the new flight control system has greatly improved than the original system to meet the high, medium and low altitude requirements of different flight performance indicators, and has good anti-jamming capability for the new missile control system provides in accordance with.