Paper Title:
Suboptimal Guidance and Control Design for a Missile with Onboard Strapdown Seeker
  Abstract

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
Chapter
Chapter 14: Modeling, Analysis, and Simulation of Manufacturing Processes
Edited by
Wu Fan
Pages
2513-2520
DOI
10.4028/www.scientific.net/AMM.110-116.2513
Citation
N. Singh, 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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$32.00
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