Composite guidance laws using higher order sliding mode differentiator and disturbance observer

He, Shaoming; Wang, Jiang; Lin, Defu

doi:10.1177/0954410015576365

Cited by 18 publications

(18 citation statements)

References 33 publications

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“…Note that SMC have been widely used for various applications and proven to be efficient. [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.…”

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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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: 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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“…However, in the literature, SMC has been widely applied to the problem of impact angle, [15][16][17][18][19][20][21] impact time. [22][23][24][25] It has also been shown to be effective for wide varieties of aerospace applications, such as missile, [26][27][28][29] aircraft, 30 reentry vehicles, 31 and spacecraft. 32 In this paper, the problem of impact time and angle is addressed using an approach of two-stage guidance strategy with the first-order SMC theory.…”

Section: Introductionmentioning

confidence: 99%

Sliding mode guidance for impact time and angle constraints

Kumar

Ghose

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper proposes a guidance strategy, which caters to both impact angle and impact time terminal constraints. This guidance scheme is based on switching between impact time and impact angle guidance laws. Unlike the existing impact time guidance laws, the proposed guidance strategy takes into account the curvature of the trajectory due to requirement of impact angle. The guidance law is derived using sliding mode control theory with the switching surface based on impact time error. The interceptor first corrects its course to nullify the impact time error and then aims to achieve interception with desired impact angle. In order to reduce transitions between the two guidance laws, a novel hysteresis loop is introduced in the switching conditions. The guidance law is initially designed for stationary targets, and later it is extended to constant velocity targets using the notion of predicted interception point. In order to validate the efficacy of the proposed guidance strategy, simulation results are presented with constant as well as realistic time-varying speed interceptor models for different engagement scenarios against stationary and constant velocity targets. The performance of the guidance law is evaluated under noisy measurements and the presence of system lag and its performance is compared with other existing guidance laws.

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“…In Yan and Ji, 12 a novel input-to-state stability-based guidance (ISSG) law was proposed to suppress bounded target maneuvers and get bounded LOS angular rates. In order to attenuate the highfrequency chattering of classical sliding mode control, He et al 13 presented a continuous guidance law based on higher-order sliding mode technique. Assuming the upper bound of target maneuver can be obtained in advance, terminal sliding mode 14 and integral sliding mode 15 were used to design finite-time convergent guidance law.…”

Section: Introductionmentioning

confidence: 99%

Observer-based guidance law against maneuvering targets without line-of-sight angular rate information

Lin

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper presents a robust observer-based finite-time convergent guidance law to intercept maneuvering targets. To avoid the undesired chattering phenomenon existing in classical sliding mode control, the adaptive super-twisting algorithm is first introduced to design a robust guidance law to drive the line-of-sight (LOS) angular rates to a small region around the origin in finite time. The important feature of the proposed adaptation algorithm is in nonoverestimating the values of the guidance law gains, which is achieved by using a ‘detector’ scheme in the updating law. Moreover, with the proposed adaptive law, the presented guidance law requires no information on target maneuvers. Since the LOS angular rate is difficult for a pursuer to measure accurately for some seekers, a novel adaptive super-twisting observer is proposed to estimate it and a composite guidance law is then synthesized. Detailed finite-time stability analysis and comparison results with other guidance laws demonstrate the superiority of the proposed formulation.

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Composite guidance laws using higher order sliding mode differentiator and disturbance observer

Cited by 18 publications

References 33 publications

Three-dimensional impact angle guidance with coupled engagement dynamics

Three-dimensional impact angle guidance with coupled engagement dynamics

Sliding mode guidance for impact time and angle constraints

Observer-based guidance law against maneuvering targets without line-of-sight angular rate information

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