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Cooperative guidance strategy for multiple hypersonic gliding vehicles system with flight constraints and cooperative constraints is investigated. This paper mainly cares about the coordination of the entry glide flight phase and driving-down phase. Different from the existing results, both the attack time and the attack angle constraints are considered simultaneously. Firstly, for the entry glide flight phase, a two-stage method is proposed to achieve the rapid cooperative trajectories planning, where the control signal corridors are designed based on the quasi-equilibrium gliding conditions. In the first stage, the bank angle curve is optimized to achieve the attack angle coordination. In the second stage, the angle of attack curve is optimized to achieve the attack time coordination. The optimized parameters can be obtained by the secant method. Secondly, for the driving-down phase, the cooperative terminal guidance law is designed where the terminal attack time and attack angle are considered. The guidance law is then transformed into the bank angle and angle of attack commands. The cooperative guidance strategy is summarized as an algorithm. Finally, a numerical simulation example with three hypersonic gliding vehicles is provided for revealing the effectiveness of the acquired strategy and algorithm. Keywords: Attack angle constraints, Attack time constraints, Cooperative guidance, Cooperative path planning, Entry guidance, Hypersonic vehicles

In order to reduce the computational cost for online calculation of the quantum filter, in this paper, a linear quantum projection filtering scheme is developed by projecting the time evolution trajectory of quantum system state onto a lower-dimensional linear submanifold spanned by a set of basis matrices. The lower-dimensional submanifold is obtained through an extended singular value decomposition algorithm. Compared with the existing works on quantum projection filtering, the proposed approach requires no prior knowledge on the structure of the submanifold, and thus can be used to deal with general open quantum systems. Simulation results demonstrate that the proposed linear projection filter is able to approximate the high-dimensional quantum filter within acceptable accuracy.

This paper investigates the problem of dynamic sliding-mode control through piecewise affine systems (PWAs). An uncertain piecewise affine system is utilized to equivalently represent a general nonlinear system on a compact region around the origin. A piecewise dynamic sliding-mode control law is then constructed for robustly stabilizing the uncertain piecewise affine system and, consequently, for asymptotic stabilization of the corresponding non-affine continuous-time nonlinear system. The constructed approach holds a favorable feature: it removes some assumptions on the system matrices, thus the developed scheme is more relaxed compared with the published approaches. The simplicity and advantages of the developed scheme is illustrated by a numerical simulation.

Distributed adaptive cooperative time-varying formation tracking guidance problems of multiple aerial vehicles system against a maneuvering target are investigated. Different from the former results, the proposed cooperative guidance strategies are based on distributed time-varying formation tracking theories. Firstly, the leader aerial vehicle is designed to achieve interception with desired terminal attack angle, which provides a reference trajectory. The uncertain dynamic items and target's uncertain maneuver have been compensated. For the follower aerial vehicles, the distributed cooperative time-varying formation tracking guidance laws are raised. Adaptive distributed extended state observers are introduced to estimate the leader vehicle's states and input information. Then, an algorithm is shown for determining guidance parameters of cooperative guidance laws. Thirdly, the properties and the stabilities of the algorithm are discussed in detail. Finally, a simulation experiment is performed for showing the feasibility and effectiveness of achieved results.