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.

Meeting Name

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

Document Type

Article - Conference proceedings

Document Version


File Type





© 2006 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.

Publication Date

24 Aug 2006

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