Design of Nonsaturating Guidance Systems
Design of Nonsaturating Guidance Systems
复制标题
非饱和制导系统的设计
DOI：
10.2514/2.4585
复制
发表时间：
2000
期刊：
影响因子：
--
通讯作者：
Moshe Guelman
中科院分区：
文献类型：
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作者：
P. Gurfil;M. Jodorkovsky;Moshe Guelman
考虑了非饱和制导系统的设计问题。在运动学线性化的前提下，建立了比例导引模型。所讨论的导弹制导回路包含诸如受限的导弹机动性、受限的加速指令和受限的测量视线角速率等非线性。一种基于输入-输出稳定性的新方法，给出了在给定导弹-目标机动比的情况下，确保在非饱和区运行的设计准则。这些指导方针产生了一种基于比例导航的制导律，确保了任何有界目标机动的零脱靶量。结果表明，如果将制导回路的总动态设计为正实数，并选择有效比例导航常数为操纵比的简单函数，则不会发生饱和。算例验证了分析的正确性，并表明即使设计准则有所松动，新的制导律仍具有足够的鲁棒性，可以保证性能有明显的改善。
Design of nonsaturating guidance systems is considered. Assuming linearized kinematics, a proportional navigation guidance model is introduced. The missile guidance loop discussed contains nonlinearities such as limited missile maneuverability, limited acceleration command, and constrained measured line-of-sight angular rate. A novel approach, based on input–output stability, renders design guidelines that assure operation in the nonsaturating region, given the missile–target maneuver ratio. These guidelines yield a proportional-navigation-based guidance law that assures zero miss distance for anybounded targetmaneuver. It is shown that if the total dynamics of the guidance loop is designed to be positive real, and the effective proportional navigationconstant is chosen to be a simple function of themaneuver ratio, no saturation shall occur. The illustrative examples validatethe analysis and show that the new guidance law is robust enough to guarantee a signi cant performance improvement even if the design guidelines are somewhat loosened.