Design of Three-Dimensional Missile Guidance Law via Sliding Mode with Saturation Constraint
نویسندگان
چکیده
Various guidance laws have been exploited with different design concepts over the years [2]. Currently, the most popular terminal guidance laws, as defined by Locke [1], involve Line-Of-Sight (LOS) guidance, LOS rate guidance and other advanced guidance such as proportional navigation guidance [1], Augmented Proportional Navigation Guidance (APNG) [3], optimal guidance law based on the linear quadratic regulator theory [4] and linear exponential Gaussian theory [5].
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