Abstract
An optimal midcourse guidance law with flight path angle and lead angle constraints to reach a circular target area is proposed here. In this paper, the circular target area is defined as a circle which center is a target to intercept and radius becomes a seeker's detection range. This guidance law is especially useful for a missile which has a strap-down type seeker with limited F.O.V. (Field Of View) because a missile's lock-on condition can be satisfied by imposing a final lead angle constraint with consideration of a seeker's F.O.V. limit. In addition, through a final flight path angle constraint, a missile can occupy an advantageous homing point. This guidance law is derived from an optimal control theory which minimizes a range weighted control energy and its characteristics are studied further. Finally, performance of this guidance law is verified by a numerical simulation.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
