Guidance Law Design for Missiles with Reduced Seeker Field-Of-View
In this paper, a missile guidance law is designed to address the reduced seeker field-of-view constraint that is required in the low cost weapon system. The guidance problem is formulated as a nonlinear optimal control problem in the polar coordinates such that the line-of-sight (LOS) can be explicitly controlled. A closed-form guidance law is obtained by employing the θ − D nonlinear control technique. By virtue of state dependent weighting functions, impact angle requirement for increasing weapon lethality can also be met while satisfying reduced seeker field-of-view constraint. A missile attacking a stationary target is considered in this study. The simulation demonstrated favorable results compared with the classical proportional navigation law in terms of satisfying both reduced seeker field-of-view constraint and the terminal impact angle requirement.
M. Xin et al., "Guidance Law Design for Missiles with Reduced Seeker Field-Of-View," Proceedings of the AIAA Guidance, Navigation, and Control Conference and Exhibit (2006, Keystone, CO), American Institute of Aeronautics and Astronautics (AIAA), Aug 2006.
AIAA Guidance, Navigation, and Control Conference and Exhibit 2006 (2006: Aug. 21-24, Keystone, CO)
Mechanical and Aerospace Engineering
Keywords and Phrases
Nonlinear Control Technique; Missile Guidance Law; Field-Of-View Constraint
Article - Conference proceedings
© 2006 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
24 Aug 2006