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In this paper, a novel cascade type design model is transformed from the simulation model, which has a broader scope of application, for integrated guidance and control (IGC). A novel non-singular terminal dynamic surface control based IGC method is proposed. It can guarantee the missile with multiple disturbances fast hits the target with high acc...
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... in Fig. 1 shows the inertial coordinate system. O-xyz is fixed to the missile centroid and parallel to A-XYZ. Firstly, rotate Oxyz counterclockwise by q 2 along O-y axis, and then rotate it counterclockwise by q 1 along O-z axis. One gets line-of-sight (LOS) coordinate system O-x 4 y 4 z 4 ...
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... guidance equations of the pursuit situation in the threedimensional space as shown in Fig. 1 can be described by the following nonlinear Eqs. (1) [10,11] ...
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... [5,5] SMC_DSC method. NT_DSC IGC law can guarantee the missile hits the target with higher accuracy while better satisfying the terminal impact angular constraint. Moreover, as Remark 1 in Section 2.3, θ and ψ V tend to the terminal impact angular constraints when LOS angles (x 0 ) tends to the constraints shown as Fig. 10. In addition, the states (x 2 and x 3 ) and commands (u) are reasonable and smooth without any chattering. Concrete accuracy statistics will be presented by Monte Carlo simulations as ...
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... order to investigate and research the 2 methods more generally, Monte-Carlo simulations in Case 2 continue. The miss distances and terminal impact angular constraints are concerned in the following simulations. 50 times simulations of the 2 IGC laws mentioned in Table 1 have been carried out in Case 2. The miss distances are shown as Fig. 10. And the terminal impact angular constraints are shown as Fig. ...
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... generally, Monte-Carlo simulations in Case 2 continue. The miss distances and terminal impact angular constraints are concerned in the following simulations. 50 times simulations of the 2 IGC laws mentioned in Table 1 have been carried out in Case 2. The miss distances are shown as Fig. 10. And the terminal impact angular constraints are shown as Fig. ...
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Citations
This paper proposes a novel finite-time integrated guidance and control (IGC) design for skid-to-turn (STT) missiles, taking full state constraints into account. Firstly, the actuator saturation is converted into a state constraint. Secondly, to handle full state constraints effectively, the “non-constrained” IGC (NCIGC) model is constructed by combing the IGC model with a permissible set of states and applying a nonlinear transformed function. Thirdly, a finite-time full state constraints IGC scheme based on the NCIGC model is presented. According to Lyapunov stability theory, the proposed IGC method is verified to ensure that all states of the IGC model converge to a small neighborhood near zero within a finite time while satisfying the predefined state constraints. Finally, numerical simulations are performed to demonstrate the effectiveness and robustness of the proposed IGC scheme.
This paper presents an adaptive nonsingular finite-time sliding mode control, for a class of second-order nonlinear systems in the presence of uncertainties and disturbances. The core idea involves employing an adaptive mechanism to estimate the unknown upper bounds associated with system uncertainty. These estimates are then utilized as controller parameters, effectively neutralizing the impact of uncertain dynamics and external disturbances. Importantly, this technique ensures finite-time convergence of errors without encountering singularities. Consequently, the control inputs remain smooth and bounded throughout the entire tracking process. Additionally, the proposed algorithm offers an appropriate coordinate transformation, enabling its adaptation for a broad spectrum of electromechanical systems, with particular emphasis on robotic manipulators. The closed-loop system's stability is substantiated through the Lyapunov stability theorem. Through simulation results, the paper substantiates the effectiveness of the approach by showcasing its capacity to achieve good tracking performance.
This article proposes a time‐varying nonsingular terminal sliding mode (TSM) control for a class of uncertain second‐order nonlinear system and its application to n‐links rigid robotic manipulators. First, a time‐varying nonsingular terminal sliding manifold is developed by incorporating a piecewise‐defined function of time into a nonsingular TSM manifold. As a result, the singularity problem is avoided and the reaching phase existing in conventional TSM control is totally suppressed which ensures the global robustness of the system against uncertainties and disturbances. Moreover, adaptive tuning laws are developed to omit the requirement of prior knowledge of the upper bound of the lumped uncertainty. In particular, an effective method is provided for the parameters selection to meet a prespecified convergence time. Hence, the convergence time to the origin of the tracking errors can be specified in advance according to the mission requirements. The formulation of the controllers and the stability analysis are verified by Lyapunov theory. Simulation results and comparative studies are presented to demonstrate the effectiveness and the superiority of the proposed algorithms.
