Finite time sliding sector guidance law with acceleration saturation constraint

Xu, Biao; Zhou, Di

doi:10.1049/iet-cta.2015.0199

Cited by 11 publications

(7 citation statements)

References 24 publications

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“…By adapting different control input and considering time rate of change in sliding surface slopes, an extended form of the theory for nonlinear state‐dependent single input systems was presented in Reference . In the derivation of a guidance law, VS control with finite‐time SS has been also utilized, which was designed by solving state‐dependent differential Riccati equation (SDDRE) to not only satisfy the finite time stability but also enhance the robustness against missile acceleration saturation constraint . According to Xu et al, the researches on SSC were only interested in dealing with matched parameter uncertainty and the disturbances with a known upper bound until 2016 .…”

Section: Introductionmentioning

confidence: 99%

“…In the derivation of a guidance law, VS control with finite-time SS has been also utilized, which was designed by solving state-dependent differential Riccati equation (SDDRE) to not only satisfy the finite time stability but also enhance the robustness against missile acceleration saturation constraint. 22 According to Xu et al, the researches on SSC were only interested in dealing with matched parameter uncertainty and the disturbances with a known upper bound until 2016. 23 Therefore, they had constructed an adaptation rule for estimating the upper bound of the disturbances to design a VS control law such that it was robust against both unmatched parameter uncertainty and the disturbances with unknown upper bound.…”

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confidence: 99%

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Nonlinear sliding sector design for multi‐input systems with application to helicopter control

Özcan

Salamcı

Nalbantoglu

2020

Intl J Robust & Nonlinear

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Summary The ability of helicopters to hover and land vertically has spurred an interesting field of research on the development of autonomous flight for these rotatory wing aircrafts. Linear control theory with gain scheduling, which is based on linearizing the system at the equilibrium points, dominated the helicopter autopilot design. Unlike the linear cascaded autopilot structure used in the existing literature, this paper uses state‐dependent linear like structure, including rate‐limited actuator dynamics, with cascaded autopilot topology. This approach allows nonlinear control laws to be implemented throughout the entire flight envelope, providing satisfactory robustness and stability over the various parameter uncertainties and time delays. The cascaded autopilot topology with nonlinear dynamical equations contains a new sliding sector control (SSC) mechanism which is derived for multi‐input nonlinear dynamical systems. The proposed SSC structure for multi‐input nonlinear systems is used in the inner loop of the cascaded autopilot system where the fastest dynamics are required to be controlled for rapid changes in the helicopter dynamical characteristics which enables one to stabilize the helicopter over a wide range of flight conditions. The proposed cascaded autopilot topology with the new SSC mechanism is tested in simulations to assess its robustness and stability properties. To establish its feasibility, the proposed control method is replaced with a suboptimal control method, namely state‐dependent differential Riccati equation (SDDRE) method, for the inner loop and the results of the proposed control architecture are compared with those of SDDRE method.

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Section: Introductionmentioning

confidence: 99%

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confidence: 99%

Nonlinear sliding sector design for multi‐input systems with application to helicopter control

Özcan

Salamcı

Nalbantoglu

2020

Intl J Robust & Nonlinear

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“…An optimal feedback law of an interceptor lateral acceleration was presented in [13] to achieve the impact angle with arbitrary order dynamics for the interceptor. In [14], a finite‐time guidance law was proposed for target interception, using a combination of proportional navigation variant and finite‐time sliding sector technique, under acceleration constraints. The sliding sector was determined by solving a modified differential SDRE equation analytically.…”

Section: Introductionmentioning

confidence: 99%

Suboptimal closed‐form feedback control of input‐affine non‐linear systems

Nanavati

Kumar

Maity

2020

IET Control Theory & Appl

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“…Therefore, it is necessary to design three-dimensional finite-time guidance laws against maneuvering targets with impact angle constraint. To intercept maneuvering targets, three-dimensional sliding mode guidance laws were given in Song and Song (2016), Li and Ji (2016) and Xu et al (2016). However, they did not consider the problem of terminal impact angle constraint.…”

Section: Introductionmentioning

confidence: 99%

Continuous reaching law based three-dimensional finite-time guidance law against maneuvering targets

Song

2018

Transactions of the Institute of Measurement and Control

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Three-dimensional finite-time guidance laws are proposed in this paper. Differing from the traditional approach that considers homing guidance problems as two identical and perpendicular channels, guidance laws proposed in this paper employ the coupled three-dimensional engagement dynamics to improve the guidance precision. A new reaching law is adopted to guarantee guidance laws continuous, which eliminates the chattering phenomenon caused by discontinuous terms. Moreover, the guidance law accelerates the convergence rate of closed-loop systems and avoids the singularity. Afterwards, the paper discusses the problem that the upper bound of the lumped uncertainty including the target information is unavailable. Therefore, to deal with this problem, another adaptive guidance law is presented, which can also guarantee the finite-time convergence of guidance systems. Numerical simulations have demonstrated that the two guidance laws have effective performance and outperform traditional terminal sliding mode guidance laws.

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Finite time sliding sector guidance law with acceleration saturation constraint

Cited by 11 publications

References 24 publications

Nonlinear sliding sector design for multi‐input systems with application to helicopter control

Nonlinear sliding sector design for multi‐input systems with application to helicopter control

Suboptimal closed‐form feedback control of input‐affine non‐linear systems

Continuous reaching law based three-dimensional finite-time guidance law against maneuvering targets

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