Suboptimal Guidance and Control Design for a Missile with Onboard Strapdown Seeker

Abstract:

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Dynamic inversion control in conjunction with nonlinear suboptimal three dimensional (3-D) guidance law, in terminal phase, is implemented in both the pitch and yaw plane for a short range surface to surface missile with onboard active strapdown seeker. The implemented guidance and control laws intercept the target with a minimum miss distance in addition to meeting the various constraints such as line of sight, seeker field-of-view (FOV), and impact angle. This is achieved using approximate solution to Hamilton-Jacobi-Bellman (HJB) equation [1]. Dynamic inversion control is implemented in two time scales for the inner loop body rate and outer loop angles. Various nonlinearities including that due to the coupling effect between pitch and yaw channels are accounted for in the six-degree-of-freedom (6-DOF) formulation.

Info:

Periodical:

Edited by:

Wu Fan

Pages:

2513-2520

DOI:

10.4028/www.scientific.net/AMM.110-116.2513

Citation:

N. Singh and M. Sinha, "Suboptimal Guidance and Control Design for a Missile with Onboard Strapdown Seeker", Applied Mechanics and Materials, Vols. 110-116, pp. 2513-2520, 2012

Online since:

October 2011

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Price:

$35.00

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