Optimal guidance of extended trajectory shaping

Wang, Hui; Lin, Defu; Zhen-xuan, Cheng; Wang, Jiang

doi:10.1016/j.cja.2014.03.022

Cited by 22 publications

(26 citation statements)

References 15 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In order to validate the effectiveness and superiority of the proposed SAFFTNTSMGL, a surface-to-air interceptor is taken into account in its terminal guidance phase against a maneuvering target, and extensive results of the performance of the proposed guidance law obtained from numerical simulation are presented. From these results, the desired final LOS angle is computed by (6), and the normal acceleration is obtained and bounded according to Equation (27) with the adaptive law (28). Here, the missile autopilot is considered as the following second-order system, which fully considers the time lag and autopilot dynamics between the acceleration command and the achieved acceleration always being existed:…”

Section: Simulation Resultsmentioning

confidence: 99%

“…Under such conditions, the missile cannot regulate the LOS angular ratėsuccessfully. In the work of Wang et al, 6 it has been demonstrated that, if m = ± /2, theṅm −̇≠ 0. Therefore, the scenarios m = ± /2 are not stable equilibrium points and the guidance system trajectory just across the points m = ± /2 and will not stay on them.…”

Section: Problem Formulationmentioning

confidence: 98%

“…Assume that t (t f ) and d are given. There exists a unique m (t f ), which satisfies the Equations (4) to (6).…”

Section: Proposition 2 (See the Work Of Kim Et Al 8 )mentioning

confidence: 99%

See 2 more Smart Citations

Adaptive terminal angle constraint interception against maneuvering targets with fast fixed‐time convergence

Zhang

Tang

Guo

2018

Intl J Robust & Nonlinear

View full text Add to dashboard Cite

In this paper, a modified adaptive fast nonsingular terminal sliding mode guidance law is proposed based on the theory of fixed-time convergence, which is applied for intercepting maneuvering targets considering terminal angle constraint. The proposed guidance law achieves system stabilization within bounded settling time independent on initial conditions and provides no singularity and globally rapid convergence property by accelerating the convergence rate when the system is close to the origin. The upper bound of settling time can be obtained in advance by the controller's parameters. Besides, in order to achieve chattering-free property, a continuous adaptive switching control is introduced and the achieved acceleration-magnitude constraints are rigorously enforced. Finally, the fixed-time convergence of the sliding mode manifold and the system states is demonstrated by Lyapunov stability theory. Extensive numerical simulations are presented to validate the efficiency and superiority of the proposed guidance law.

show abstract

Section: Simulation Resultsmentioning

confidence: 99%

Section: Problem Formulationmentioning

confidence: 98%

See 1 more Smart Citation

Adaptive terminal angle constraint interception against maneuvering targets with fast fixed‐time convergence

Zhang

Tang

Guo

2018

Intl J Robust & Nonlinear

View full text Add to dashboard Cite

show abstract

“…Based on the optimal control theory, and constrained by zero miss-distance and zero impact-angle error, Ref. (5) obtains the close-form solution of optimal guidance law with impact-angle constraints by using Schwartz inequality. Based on the theory of Model Predictive Static Programming (MPSP), the control quantity of the angle is updated iteratively to satisfy the constraint conditions of impact-angle in Ref.…”

Section: Introductionmentioning

confidence: 99%

New three-dimensional second-order sliding mode guidance law with impact-angle constraints

Zhao

You

2019

Aeronaut. j.

View full text Add to dashboard Cite

Aiming at the issue of missiles attacking on-ground maneuvering targets in three-dimensional space, a three-dimensional finite-time guidance law with impact-angle constraints is proposed. In order to improve convergence speed and restrain chattering phenomenon, the nonsingular fast terminal three-dimensional second-order sliding mode guidance law with coupling terms is designed based on the theory of nonhomogeneous fast terminal sliding surface and second-order sliding mode control. The system model need not be linearized during the design process, and the singular problem is avoided. A nonhomogeneous disturbance observer is designed to estimate and compensate the total disturbance, which is caused by target maneuvering information and coupling terms of line of sight. And the stability and finite-time convergence of the guidance law are proved strictly and mathematically. Finally, simulation results have verified the effectiveness and superiority of the proposed guidance law.

show abstract

“…Guidance laws with terminal angle control have been widely studied in the literatures. Most of the advanced guidance laws used optimal control theory [4][5][6] or sliding mode control [7][8][9] to intercept the targets with angular constraint. Usually, these guidance laws include relative range-or timeto-go information which cannot be measured by passive missiles directly.…”

Section: Introductionmentioning

confidence: 99%

Time-Varying Biased Proportional Guidance with Seeker’s Field-of-View Limit

Yang

Wang

Lin

2016

International Journal of Aerospace Engineering

Self Cite

View full text Add to dashboard Cite

Traditional guidance laws with range-to-go information or time-to-go estimation may not be implemented in passive homing missiles since passive seekers cannot measure relative range directly. A time-varying biased proportional guidance law, which only uses line-of-sight (LOS) rate and look angle information, is proposed to satisfy both impact angle constraint and seeker’s field-of-view (FOV) limit. In the proposed guidance law, two time-varying bias terms are applied to divide the trajectory into initial phase and terminal phase. The initial bias is designed as a function of LOS rate and look angle to maintain the seeker’s lock-on while the final bias eliminates the deviation between the integral value of angle control bias and the expected bias amount. A switching logic is adopted to change the biases continuously so that there is no abrupt acceleration change during the engagement. Extensive simulations considering both kinematic and realistic missile models are performed to illustrate the efficiency of the proposed method.

show abstract

Optimal guidance of extended trajectory shaping

Cited by 22 publications

References 15 publications

Adaptive terminal angle constraint interception against maneuvering targets with fast fixed‐time convergence

Adaptive terminal angle constraint interception against maneuvering targets with fast fixed‐time convergence

New three-dimensional second-order sliding mode guidance law with impact-angle constraints

Time-Varying Biased Proportional Guidance with Seeker’s Field-of-View Limit

Contact Info

Product

Resources

About