Abstract
For tactical missiles, sliding mode control and super-twisting algorithms have been widely studied in the area of guidance law design. However, these methods require the information of the target accelerations and the target acceleration derivatives, which is always unknown in practice. In addition, guidance laws utilizing these tools always have chattering phenomena and large acceleration commands. To solve these problems, this article introduces a barrier function based super twisting controller and expands the controller to a multivariable adaptive form. Consequently, a multivariable adaptive super-twisting guidance law based on barrier function is proposed. Moreover, the stability of the guidance law is analyzed, and the effectiveness and the robustness are demonstrated by three simulation examples. Compared with previous guidance laws using sliding mode control or super-twisting algorithm, the one proposed in this paper does not require the information of target accelerations, nor target acceleration derivatives; it has smaller super-twisting gains so that has smaller acceleration commands; it can increase and decrease the gains to follow the target accelerations and maintain the sliding mode, and it does not chatter.
Highlights
Inspired by the above works, this study presents a multivariable barrier functionbased super-twisting controller and applied the algorithm to guidance law design with impact angle consideration for a maneuvering target
The guidance law does not require the information of disturbance derivatives, nor utilize a filter to obtain the value of equivalent control; The super-twisting gains of the guidance law are small but sufficient to counteract the disturbances, and the output variable is small but adequate to achieve performance goals; The guidance law can converge to a predefined neighborhood of zero and maintain the sliding mode, whether the disturbances increase or decrease; The acceleration commands have no chatterings
The rest of the paper is organized as follows: Section 2 presents the kinematics of missile-target engagement and preliminaries; Section 3 designs a multivariable adaptive super-twisting guidance law based on barrier function and analyzes the stability, and Section 4 gives three simulation examples to demonstrate the effectiveness and robustness of the proposed guidance law
Summary
Publisher’s Note: MDPI stays neutral with regard to jurisdictional claims in published maps and institutional affiliations. The guidance law does not require the information of disturbance derivatives, nor utilize a filter to obtain the value of equivalent control; The super-twisting gains of the guidance law are small but sufficient to counteract the disturbances, and the output variable (acceleration command) is small but adequate to achieve performance goals; The guidance law can converge to a predefined neighborhood of zero and maintain the sliding mode, whether the disturbances increase or decrease; The acceleration commands have no chatterings. The rest of the paper is organized as follows: Section 2 presents the kinematics of missile-target engagement and preliminaries; Section 3 designs a multivariable adaptive super-twisting guidance law based on barrier function and analyzes the stability, and Section 4 gives three simulation examples to demonstrate the effectiveness and robustness of the proposed guidance law
Sign-in/Register to view highlights & summary 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.
