Analysis of generalized guidance laws for homing missiles

Vathsal, S.; Rao, Meng

doi:10.1109/7.381902

Cited by 8 publications

(1 citation statement)

References 16 publications

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“…PN was considered to be a quasi-perfect guidance law in the early stage of many kinds of tactical missiles because its theoretical study was more mature and its engineering implementation was relatively simple [3]. If a combination of the state variables of the PN systems, e.g., line-of sight (LOS) rate, missile maneuver acceleration, and missile commanded acceleration are kept bounded until the end of interception, PN system can realize zero miss distance [4][5][6]. But during intercepting the fast targets [7][8], or maneuvering targets [9][10], the PN guidance precision becomes worse.…”

Section: Introductionmentioning

confidence: 99%

A Study on an Improved Guidance Law Which is Insensitive to the Time-to-Go Estimation Error

Han

2009

2009 Second International Symposium on Computational Intelligence and Design

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PN (proportional navigation) law is in wide use. In this paper, the traditional proportional navigation control system is analyzed, then we find that the traditional proportional navigation guidance law is sensitive to the timeto-go (i.e., time to interception) measurement, in other words, the time-to-go estimation error may cause significant degradation in the performance of the PN guidance law. In this paper, we design a new guidance law which is called reduced sensitivity guidance law (RSL) to solve the problem. At the end of the article, the simulation results show that the RSL method is insensitive to the time-to-go estimation error and the performance of the RSL guidance law system is improved.

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