In this paper, we investigate the formation control of multiple unmanned aerial vehicles (UAVs), specifically aircraft, in an obstacle-laden environment. The main contribution paper is to integrate control, trajectory tracking, and obstacle/collision avoidance into one unified optimal framework. A nonquadratic cost innovatively constructed via inverse approach, which leads analytical, distributed, law. stability optimality closed-loop system are proven. addition, proposed law dependent only...

A new suboptimal control method is proposed in this study to effectively design an integrated guidance and system for missiles. Optimal formulations allow designers bring together concerns about law performance autopilot responses under one unified framework. They lead a natural integration of these different functions. By modifying the appropriate cost functions, responses, saturations (autopilot related), miss distance (guidance etc., which are primary concern missile designer, can be...

A novel sparse Gauss―Hermite quadrature filter is proposed using a sparse-grid method for multidimensional numerical integration in the Bayesian estimation framework. The conventional computationally expensive problems, because number of points increases exponentially with dimension. efficient filter, however, only polynomially In addition, it proven this paper that unscented Kalman suggested optimal parameter subset filter. Gauss-Hermite therefore more flexible to use than terms and...

In this paper, two kinds of sliding-mode guidance laws with impact time constraint are proposed for intercepting various target motions, including nonmaneuvering and maneuvering targets. To achieve the desired time, line-of-sight (LOS) dynamics is controlled to track a novel time-varying LOS profile created by rate-shaping approach. Unlike existing approaches that transform equations motion downrange variable as independent variable, no such manipulation necessary in technique virtue...

In this paper, a new guidance strategy is proposed for intercepting stationary and constant-velocity moving targets with desired impact time angle via virtual target approach, subject to nonlinear engagement kinematics lateral-acceleration limits. The procedure divided into two stages by introducing target. Specifically, the first stage, nonsingular terminal sliding-mode law employed intercept specified in finite time. Furthermore, achieve on real target, proportional navigation used second...

Highly efficient single-composition white-emitting phosphors based on NaSrBO₃:Ce³⁺,Sm³⁺,Tb³⁺have been developed for the fabrication of near-UV excited white LEDs with a high color rendering index.

This article proposes an integrated optimal control strategy for a servicing spacecraft in proximity operations on target space. The relative position vector between the and is required to direct towards docking port of while attitude two bodies must be synchronised without exciting large flexible vibrations. translational, rotational motions formulated one unified framework which tracking errors attitude, structure vibrations can minimised simultaneously using cost function. formulation...

A new method is proposed for robust control of spacecraft in proximity orbit servicing operations from an optimal formulation. It can be shown that the nonlinear uncertain system equivalent to controlled nominal with a modified cost functional including uncertainty bounds such both stabilization and performance achieved. The -D technique utilized design closed-form law, which facilitates onboard implementation. pursuer autonomously approach target at specified safe relative position align...

In this paper, a twisting control-based guidance law considering nonlinear/coupled dynamics and terminal angle constraints is proposed in three-dimensional (3-D) space. The refers to the impact for nonmaneuvering targets, approach maneuvering respectively. To meet 3-D space, coupled line-of-sight (LOS) error controlled track command LOS angles, which can be obtained from relation between desired angle. Then, barrier function-based adaptive multivariable controller designed obtain nullifying...

This paper proposes distributed cooperative guidance laws for multiple missiles with constant speeds to achieve impact-angle-constrained salvo attack against a stationary target in both two-dimensional (2D) and three-dimensional (3D) scenarios. First, the 2D law is derived based on an optimal impact angle control (IACG) law, which augmented by term ensure consensus of times-to-go fixed time before interception. To avoid singularity, auxiliary function three candidates introduced into term....

In this paper, a distributed three-dimensional (3D) nonsingular cooperative guidance law is designed for multiple missiles with different seeker’s field-of-view (FOV) constraints to achieve salvo attack against stationary target. The derived from an extended biased proportional navigation (PNG). PNG augmented by term ensure that times-to-go of the missile group reach consensus in fixed time before interception. Two auxiliary functions are included into guarantee nonsingularity and meet FOV...

In this paper, a cooperative guidance law is proposed for missiles with thrust control to realize impact angle constrained salvo attack, where missile speed limit also considered. Guidance of powered decoupled into independent flight direction normal acceleration as an input control/constrained (IACG) and engine attack. Firstly, IACG derived from geometrically modified proportional navigation guidance. The trajectory shape length under are proved be variation. Then (CMTC) designed consensus...

With the continuous development of information technology, new teaching resources “micro-video class” and model “flipped classroom” have gradually attracted attention teachers. Whether how they can be applied in pharmacology has already become focus medical education research recent years. This paper explores application evaluation flipped classroom based on micro-video class our college. Students Class 1 2 majoring clinical medicine 2018 Chengdu Medical College were randomly divided into...

This paper proposes a varying-gain proportional navigation guidance (PNG) law that can serve as the baseline for precise control of impact time. First, PNG is developed by an inverse design strategy from explicit time-to-go estimation conventional law, which leads to high efficiency and accurate prediction. Next, show its potential significance, augmented with biased feedback command obtain time (ITCG) law. As step forward in more practical applications considering missile speed variation...

In this article, an incremental guidancelaw with terminal angle constraint is proposed against maneuvering targets in the 3-D space. First, a sliding surface constructed such that its first-order dynamics excludes relative range and line-of-sight angles perturbation. This manipulation avoids unboundedperturbations induced by target maneuvers near collision. Then, benchmark guidance law derived via nonlinear dynamic inversion (NDI) based mode control (NDI-SMC). To further enhance system...

This paper investigates the three-dimensional (3D) spatial–temporal cooperative guidance problem for multiple missiles with time-varying speeds, which is addressed by a progressive design strategy. First, zero miss distance and desired impact directions are realized 3D vector angle control (IACG) law whose time-to-go predicted accurately efficiently numerical algorithm. Then, introducing an implicit trajectory-to-go function, mechanism clearly revealed under missile speed variation....

In this paper, a new non-linear control synthesis technique (θ–D approximation) is discussed. This approach achieves suboptimal solutions to class of optimal problems characterized by quadratic cost function and plant model that affine in control. An approximate solution the Hamilton–Jacobi–Bellman (HJB) equation sought adding perturbations function. By manipulating perturbation terms both semi-global asymptotic stability suboptimality properties are obtained. The overcomes...

In this paper, a new nonlinear control method is used to design full-envelope, hybrid bank-to-turn (BTT)/skidto-turn (STT) autopilot for an airbreathing air-to-air missile. Through approach, called the θ − D method, we find approximate solutions Hamilton‐Jacobi Bellman (HJB) equation. As result, resulting feedback law can be expressed in closed form. outer-loop and inner-loop controller structure design. A BTT/STT command logic convert commanded accelerations from guidance laws reference...