Abstract
State-dependent Riccati equation (SDRE) techniques are rapidly emerging as general design methods for nonlinear controllers. A nonlinear optimal guidance law with impact angle constraint is derived for planar engagements to attack stationary targets. The guidance problem is formulated as an infinite horizon nonlinear regulator problem whose equilibrium state is zero. It is solved by SDRE technique and the state weight matrix is chosen as a function of time-to-go. Performance of the guidance law is tested numerically with different initial firing conditions for a realistic GPS/INS guided artillery rocket model with low available lateral acceleration. A reasonable launch angle is helpful to reduce the control effort, and it is acquired by trajectory optimization using genetic algorithm. Results show negligible errors for miss-distance and the desired impact angle. The proposed guidance law is a choice for the guided artillery rocket.
Highlights
State-dependent Riccati equation (SDRE) approach is a promising technique for designing controllers for nonlinear systems
A good guidance law is especially crucial for guided artillery rockets with impact angle constraint because they can only provide low available lateral acceleration, and traditional guidance laws such as proportional navigation, prediction of impact point, are not adaptable
A nonlinear optimal guidance law is proposed for intercepting stationary targets with terminal impact angle constraint
Summary
State-dependent Riccati equation (SDRE) approach is a promising technique for designing controllers for nonlinear systems. SDRE-based design procedures have been used in advanced guidance law development, in output feedback autopilot designs (nonlinear H2 ), and in full information nonlinear H∞ autopilot designs. In many advanced guidance application, impact angle constraint is required to enhance the effect of the warhead and increase its kill probability. Deep penetration of ground based targets requires vertical impact. In this paper a nonlinear optimal guidance law with impact angle constraint is derived for planar engagements to attack stationary targets. The guidance law is applied to simulations of a GPS/INS guided artillery rocket with different initial firing conditions
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