Three-dimensional Impact Angle Control Guidance Law for Missiles Using Dual Sliding Surfaces

Lee, Yongwoo; Kim, Youdan

doi:10.3182/20130902-5-de-2040.00075

Cited by 11 publications

(5 citation statements)

References 11 publications

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“…The impact angle guidance laws have also been derived using coupled engagement dynamics. [8][9][10][11] These guidance laws do not guarantee convergence of errors and their derivatives within a finite time. In fact, the papers [8][9] do not provide an analysis of the sliding mode dynamics for the chosen switching surface and it satisfies the objectives of the guidance law after occurrence of sliding mode.…”

Section: Introductionmentioning

confidence: 98%

“…[2][3][4] In the literature, there exist only a few papers that address the impact angle problem in a 3D engagement scenario using SMC. [5][6][7][8][9][10][11] In Sun and Zheng, 5 Hu et al, 6 and Feng and Song 7 the 3D engagement dynamics is first decoupled into two mutually orthogonal 2D planes and then the guidance laws are designed independently for both the planes. In both Sun and Zheng 5 and Hu et al, 6 the optimal control theory is used to derive the reference model and optimal guidance law, respectively, using linearized 2D engagement dynamics.…”

Section: Introductionmentioning

confidence: 99%

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Three-dimensional impact angle guidance with coupled engagement dynamics

Kumar

Ghose

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper proposes three-dimensional impact angle control guidance laws based on a sliding mode control technique. Unlike the usual approach of decoupling the engagement dynamics into two mutually orthogonal two-dimensional planes, the guidance laws are derived using coupled engagement dynamics. By using this approach, the control effort required to achieve the objective reduces and the performance of the guidance law is improved. The derivations of guidance laws are done using both conventional as well as nonsingular terminal sliding mode control, which guarantees asymptotic and finite time convergence, respectively, to the desired impact angle. In order to derive the guidance laws, multi-dimensional switching surfaces are used. The stability of the system, with selected switching surfaces, is demonstrated using Lyapunov stability theory. Numerical simulation results are presented to validate the proposed guidance laws for constant speed, as well as a realistic interceptor model with given aerodynamic properties. The simulations show the advantage of using coupled dynamics. The robustness of the proposed guidance laws, with respect to the interceptor's system lag, is also investigated.

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Section: Introductionmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

Three-dimensional impact angle guidance with coupled engagement dynamics

Kumar

Ghose

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…14,15 Wang et al 16 investigated a partial integrated guidance and control design for an interception with terminal impact angle constraints in three-dimensional space by using the sliding mode control. Lee et al 17 gave a three-dimensional guidance law for missiles with terminal impact angle constraints by using the sliding mode control scheme with dual sliding surfaces. Biswas et al 18 designed a three-dimensional guidance law with terminal impact angle constraints for manoeuvering targets by using dynamic inversion and sliding mode control techniques.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional impact angles constrained integral sliding mode guidance law for missiles with input saturation

Qian

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper proposes the three-dimensional impact angles constrained integral sliding mode guidance laws for the missile with the constraint of the input saturation. To solve the problem of the input constraint, an integral sliding mode surface is given for the first time by using the saturation function. The first three-dimensional integral sliding mode guidance law can solve the impact angle constraint and the target accelerations with known upper bound, while the second one can solve the impact angle constraint, input saturation, and the target accelerations with unknown upper bound simultaneously. Finally, numerical simulations are used to verify the effectiveness of the guidance laws.

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“…Note that these terminal angle constrained guidance laws are developed in a planar case, which assumes decoupled three-dimensional (3D) engagement dynamics. However, a real 3D interception is more practical for guidance law design, which attracts the recent study on the design of 3D guidance laws [20][21][22][23][24][25][26][27][28][29][30]. Thus, it is of practical significance to investigate the terminal angle constrained guidance law in the 3D space.…”

Section: Introductionmentioning

confidence: 99%

“…Then, adaptive multivariable twisting and super-twisting controls were employed to handle the impact angle constrained 3D guidance problems in [24,25]. In [26,27], the 3D guidance law was derived via the Lyapunov-based approach and SMC with dual sliding surfaces. Using the rotation angle and Euler axis of quaternion, the impact angle constraint was achieved in a 3D space in [28].…”

Section: Introductionmentioning

confidence: 99%

Sensor-Based Robust Incremental Three-Dimensional Guidance Law with Terminal Angle Constraint

Han¹,

Hu²,

Shin³

et al. 2021

Journal of Guidance, Control, and Dynamics

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In this work, a robust incremental three-dimensional (3D) guidance law is proposed considering terminal angle constraint against maneuvering targets. As a stepping stone, the line-of-sight (LOS) tracking error dynamics is employed for the 3D guidance law design. A sliding variable is constructed such that its first-order derivative excludes the relative range in the perturbation, which avoids the unboundedness of system perturbation induced by target maneuvers near collision. A time-varying version of the sliding variable is designed to accelerate convergence of the LOS tracking errors and avoid large initial sliding variables. Then, two guidance laws are derived as a benchmark via the nonlinear dynamic inversion (NDI)-based sliding mode control (NDI-SMC) and NDI-based time-varying sliding mode control (NDI-TVSMC), respectively. To further improve guidance robustness with reduced system perturbation, the sensor-based incremental nonlinear dynamic inversion (INDI) control is used to design the INDI-SMC-based and INDI-TVSMC-based guidance laws. The sensor-based guidance laws exploit the LOS angular acceleration and guidance command output at the latest step, which result in smaller guidance gains to reject the perturbation than the NDI guidance laws. Numerical simulations in various cases and comparison studies are conducted to verify the effectiveness and robustness of the proposed method.

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Three-dimensional Impact Angle Control Guidance Law for Missiles Using Dual Sliding Surfaces

Cited by 11 publications

References 11 publications

Three-dimensional impact angle guidance with coupled engagement dynamics

Three-dimensional impact angle guidance with coupled engagement dynamics

Three-dimensional impact angles constrained integral sliding mode guidance law for missiles with input saturation

Sensor-Based Robust Incremental Three-Dimensional Guidance Law with Terminal Angle Constraint

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