Sliding mode control based impact angle control guidance considering the seeker׳s field-of-view constraint

Wang, Xingliang; Zhang, Youan; Wu, Huali

doi:10.1016/j.isatra.2015.12.018

Cited by 57 publications

(35 citation statements)

References 49 publications

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“…Consider the parameterized hovercraft models (7) and (10) in the presence of parametric uncertainties and external disturbances and assume that Assumptions 5-8 are satisfied. If the update law for the path variable is chosen as (22), the desired heading angle of the hovercraft is calculated by (23), the auxiliary system is designed as (33), the adaptation laws for unknown parameters and external disturbances are given by (44) and (56), and the controllers are obtained from (43) Proof. (i) Construct the following candidate Lyapunov function:…”

Section: Stability Analysismentioning

confidence: 99%

“…However, in these methods, the state constraints remain difficult to guarantee in practical applications. More recently, a barrier Lyapunov function (BLF) has been proposed for nonlinear systems to ensure the state and output constraints [37,38], which has been applied to strict-feedback systems with output constraints [39], pure-feedback systems [40], switched systems [41], and practical applications for hypersonic flight vehicles [42] or missile guidance [43]. In addition to the conventional logarithmic function form, a modified tan-type BLF was proposed in [44], which is a general method for systems with state constraints because it works even if the state constraints are removed.…”

Section: Introductionmentioning

confidence: 99%

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Barrier Lyapunov Function‐Based Adaptive Control of an Uncertain Hovercraft with Position and Velocity Constraints

Wang

2019

Mathematical Problems in Engineering

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This paper considers the problem of constrained path following control for an underactuated hovercraft subject to parametric uncertainties and external disturbances. A four-degree-of-freedom hovercraft model with unknown curve-fitted coefficients is first rewritten into a parameterized form. By introducing a barrier Lyapunov function into the line-of-sight guidance, the specific transient tracking performance in terms of position error is guaranteed. A novel constrained yaw rate controller is proposed to ensure time-varying yaw rate constraint satisfaction, in which the yaw rate barrier is required to vary with the speed of the hovercraft. Moreover, a command filter is incorporated into the control design to generate the desired virtual controls and its time derivatives. Theoretical analyses show that, under the proposed controller, the position tracking error constraints and the yaw rate constraint can be strictly guaranteed. Finally, numerical simulations illustrate the effectiveness and advantages of the proposed control scheme.

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Section: Stability Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Barrier Lyapunov Function‐Based Adaptive Control of an Uncertain Hovercraft with Position and Velocity Constraints

Wang

2019

Mathematical Problems in Engineering

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“…As expressed in (27), N I has two values that will be discussed. The one(s) less than 1 should be considered according to Proposition 2.…”

Section: Implementation Of the Two-phased Guidance Lawmentioning

confidence: 99%

“…Step 4. Calculate N I using (27), in which there are parameters calculated in all the steps above, N F = kN I .…”

Section: Implementation Of the Two-phased Guidance Lawmentioning

confidence: 99%

“…A robust guidance law which was based on the switching logic was designed in [26] by an additional term and combined the sliding mode control. This kind of guidance problem was also solved by SMC [27] and handled without any additional switching logic. However, since most of these works dealt with stationary targets, the desired impact angle may not be achieved against moving targets when applying these works to homing missiles.…”

Section: Introductionmentioning

confidence: 99%

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A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit

Zhang

Tang

Guo

et al. 2018

International Journal of Aerospace Engineering

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A two-phased guidance problem with terminal impact angle constraints and seeker’s field-of-view limit is addressed in this paper for a missile against a nonmaneuvering incoming target. From the conventional PN guidance without any constraints, it is found that satisfying the impact angle constraint causes a more curved missile trajectory requiring a large look angle. To avoid the look angle exceeding the seeker’s physical limit, a two-phased look angle control guidance scheme with the terminal constraint is introduced. The PN-typed guidance law is designed for each guidance phase with a specific switching condition of line-of-sight. The proposed guidance law is comprised of two types of acceleration commands: the one in the initial phase which aims at controlling the missile’s look angle to reach the limit and the other for final phase which is produced by switching the navigation gain. The monotonicity of the line-of-sight angle and look angle is analyzed and proved to support the proposed method. To evaluate the specific navigation gains for both initial and final phases, the scaling coefficient between them is discussed by solving a quadratic equation with respect to the initial navigation gain. To avoid a great abrupt acceleration change at the switching instant, a minimum coefficient is chosen. Extensive simulations are performed to validate the efficiency of the proposed approach.

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Omnidirectional Autonomous Reentry Guidance Based on 3-D Analytical Glide Formulae Considering Influence of Earth’s Rotation

Chen

Zhang

et al. 2020

Steady Glide Dynamics and Guidance of Hypersonic Vehicle

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Sliding mode control based impact angle control guidance considering the seeker׳s field-of-view constraint

Cited by 57 publications

References 49 publications

Barrier Lyapunov Function‐Based Adaptive Control of an Uncertain Hovercraft with Position and Velocity Constraints

Barrier Lyapunov Function‐Based Adaptive Control of an Uncertain Hovercraft with Position and Velocity Constraints

A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit

Omnidirectional Autonomous Reentry Guidance Based on 3-D Analytical Glide Formulae Considering Influence of Earth’s Rotation

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