Abstract
The three-loop autopilot is employed by spinning missiles as well as by many high-performance command or homing guidance missiles currently because it performs well in stabilizing airframe and implementing guidance commands. However, for spinning missiles, the closed-loop system may be dynamically unstable in the form of a divergent coning motion due to the existence of cross-coupling effects. And the stability criteria of the autopilot applicable to the nonspinning missile are no longer valid in the event of the spinning. To address this issue, the structure of a three-loop autopilot of spinning missiles is introduced in this study, for which the sufficient and necessary condition of coning motion stability is analytically derived from the equations in the form of complex summation. The stability criteria are further illustrated by numerical simulation. It is noticed that spinning shrinks the stable region of the design parameters significantly. And the higher the spinning rate, the smaller the stable region becomes.
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 callMore From: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
Disclaimer: 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.
