Abstract
This paper aims to establish an effective guidance law to accomplish the interception guidance mission for a missile intercepting a target with impact angle constraint and autopilot dynamics. To achieve this purpose, a fixed-time disturbance observer-based adaptive finite-time guidance law is presented. First, a fixed-time disturbance observer (FTDO) is designed to guarantee the fast estimation of the lumped disturbance caused by the target maneuver. Then, the FTDO-based adaptive integral sliding mode backstepping (AISMB) guidance law is constructed for the interception guidance problem. Besides, several adaptive laws are established to estimate the derivative of virtual control inputs, making the “differential explosion problem” of conventional backstepping get avoided. The finite-time convergence characteristic of the closed-loop system is analyzed by utilizing the Lyapunov stability theory. Finally, the simulation examples are conducted to demonstrate the effectiveness of the proposed composite guidance law.
Highlights
Academic Editor: Hamid Reza Karimi is paper aims to establish an effective guidance law to accomplish the interception guidance mission for a missile intercepting a target with impact angle constraint and autopilot dynamics
A fixed-time disturbance observer (FTDO) is designed to guarantee the fast estimation of the lumped disturbance caused by the target maneuver. en, the FTDO-based adaptive integral sliding mode backstepping (AISMB) guidance law is constructed for the interception guidance problem
When facing a highly maneuvering target, few of these mentioned methods can simultaneously guarantee the small miss distance and desired impact angle. is disadvantage encourages the researchers to further develop some advanced methods for the guidance law, i.e., optimal control [8], sliding mode control [9], and disturbance observerbased control [10, 11]
Summary
Yunjie Wu ,1,2,3 Fei Ma ,1,2,3 Xiaofei Yang ,1,2,3 Siqi Wang ,1,2,3 and Xiaodong Liu. Is paper aims to establish an effective guidance law to accomplish the interception guidance mission for a missile intercepting a target with impact angle constraint and autopilot dynamics To achieve this purpose, a fixed-time disturbance observer-based adaptive finite-time guidance law is presented. This study attempts to employ the fixed-time disturbance observer to construct the composite adaptive finite time guidance law for intercepting highly maneuvering targets considering impact angle constraint and autopilot dynamics. (2) Based on the FTDO, an adaptive integral sliding mode backstepping (AISMB) guidance law is proposed to accomplish the interception mission, and the closed-loop guidance system can converge a small neighborhood around the origin in a finite time. Calculating the time derivatives of (1) and (2) yields r€ rθ_ 2 + at sin θt − am sin θm,
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.
