Three-dimensional cooperative guidance law to control impact time and angle with fixed-time convergence

Abstract

This article proposes a new terminal cooperative guidance law to control both impact time and impact angle in three-dimensional engagement. The presented guidance law employs on and normal line-of-sight accelerations to control the impact time and angle together. Two parts are included in this guidance law, that is, the guidance laws with impact time constraint and impact angle constraint. The first is designed based on fixed-time consensus theory to fulfill the salvo attack of the target, and the second is developed based on fixed-time nonsingular fast terminal sliding mode control method to achieve the desired impact angles. The stability analysis of this guidance law based on Lyapunov theory is also presented in detail. Moreover, the maneuvering target can be intercepted successfully with the presented guidance law, and the fixed-time stability and less control energy are well ensured. Additionally, the effectiveness and applicability of the proposed guidance scheme are explicitly verified through simulation tests.

Adaptive Distributed Fixed-Time Cooperative Three-Dimensional Guidance Law for Multimissiles against Manoeuvring Target

“…Likewise, extended state observer and protocol are united to achieve fixed-time consensus [26], and adaptive fixed-time guidance laws are designed to guarantee that LOS angular rates are nullified in the elevation and azimuth LOS directions. Based on the SM observer of the low-pass filtering [30], fixed-time consensus and NTSM are adopted to realize salvo attack and impact angle constraints, respectively. In the process of coordinated attack, a group of missiles can be regarded as special multiagents, so most cooperative guidance laws are established from consensus protocols [29,31,32] and guidance laws of single missile [19,27].…”

Adaptive Super-Twisting Cooperative Guidance Law with Fixed-Time Convergence

“…The rapid convergence is an important requirement for missiles, quadrotors, and other flight vehicles, because the final guidance time is short and about a few seconds [20]. Therefore, variable high-performance control strategies, including funnel control [21,22], prescribed performance control [23,24], and finite/fixed-time sliding mode techniques [25][26][27][28][29][30][31], have been applied to flight control systems. Compared with the traditional asymptotic stability, finitetime control can obtain faster convergence rate [25,32].…”

“…A fixed-time cooperative guidance law for attacking stationary targets is carried out in [34], in which an adaptive law is designed for disposing of the uncertainty. In order to attack a maneuvering target, a fixed-time cooperative guidance law is presented with constraints including the impact time and the LOS angle [30]. The designed fixed-time cooperative guidance law in [31] can satisfy the impact angle constraints, which regards the interference in the direction of LOS as zero.…”

“…(1) Compared with Refs. [30,31,34], a new fixed-time consensus protocol based on the integral sliding mode and adaptive ST algorithm, i.e., the acceleration command on the LOS direction, is designed to guarantee that the time-to-go for each missile achieves consensus within fixed time. The stability of the system is demonstrated by Lyapunov stability theory, and the convergence time is independent of the initial conditions of the system (2) Different from Refs.…”

“…(3) Compared with Refs. [30,37], a novel fixed-time guidance law, i.e., the acceleration command on the normal direction of the LOS, is developed to ensure that the LOS angles of all missiles can converge to the expected LOS angles rapidly. It can guarantee the system stabilization is independent on initial conditions without singularity…”