Impact Time Guidance Law Considering Autopilot Dynamics Based on Variable Coefficients Strategy for Maneuvering Target

Shang, Wei; Guo, Jie; Tang, Shijie; Ma, Yueyue; Zhang, Yao

doi:10.1155/2015/815149

Cited by 4 publications

(4 citation statements)

References 18 publications

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“…Using the kinematic equations ( 1) -( 3) and ( 8), the equivalent ITCG a eq m can be got by makingV 0, and from (12), the equivalent guidance law is given as…”

Section: Smc and Lyapunov Based Sl-itcg Designmentioning

confidence: 99%

Sliding mode control and Lyapunov based guidance law with impact time constraints

2017

Journal of Systems Engineering and Electronics

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This paper analyses the issue of impact time control of super-cavitation weapons impact fixed targets which mainly refer to the ships or submarines who lost power, but still have combat capability. Control over impact time constraints of guidance law (ITCG) is derived by using sliding mode control (SMC) and Lyapunov stability theorem. The expected impact time is realized by using the notion of attack process and estimated time-to-go to design sliding mode surface (SMS). ITCG contains equivalent and discontinuous guidance laws, once state variables arrive at SMS, the equivalent guidance law keeps the state variables on SMS, then the discontinuous guidance law enforces state variables to move and reach SMS. The singularity problem of ITCG is also analyzed. Theoretical analysis and numerical simulation results are given to test the effectiveness of ITCG designed in this paper.

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“…Using the kinematic equations ( 1) -( 3) and ( 8), the equivalent ITCG a eq m can be got by makingV 0, and from (12), the equivalent guidance law is given as…”

Section: Smc and Lyapunov Based Sl-itcg Designmentioning

confidence: 99%

Sliding mode control and Lyapunov based guidance law with impact time constraints

2017

Journal of Systems Engineering and Electronics

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“…The guidance law based on nonlinear control method is to derive guidance law by utilizing nonlinear control theory. The nonlinear control methods utilized extensively include variable structure control, Lyapunov optimizing feedback control, and H∞ [12][13][14][15][16][17]. In [12], the presented guidance law is based on nonsingular terminal sliding mode, smooth second-order sliding mode, and finite time convergence disturbance observer.…”

Section: Introductionmentioning

confidence: 99%

“…It is used to estimate and compensate the lumped uncertainty in missile guidance system; no prior knowledge of target maneuver is required. Shang et al [13] considered target maneuver as external disturbance. Under the circumstance of small target-missing amount, a collision time controllable guidance law was proposed based on the theory of finite time convergence control.…”

Section: Introductionmentioning

confidence: 99%

Terminal Guidance Law for UAV Based on Receding Horizon Control Strategy

Guan²,

Yang

et al. 2017

Complexity

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Terminal guidance law against the maneuvering target is always the focal point. Most of the literatures focus on estimating the acceleration of target and time to go in guidance law, which are difficult to acquire. This paper presents a terminal guidance law based on receding horizon control strategy. The proposed guidance law adopts the basic framework of receding horizon control, and the guidance process is divided into several finite time horizons. Then, optimal control theory and target motion prediction model are used to derive guidance law for minimum time index function with continuous renewal of original conditions at the initial time of each horizon. Finally, guidance law performs repeated iteration until intercepting the target. The guidance law is of subprime optimal type, requiring less guidance information, and does not need to estimate the acceleration of target and time to go. Numerical simulation has verified that the proposed guidance law is more effective than traditional methods on constant and sinusoidal target with bounded acceleration.

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“…Partial integrated guidance and control is that the guidance law is designed accounting for autopilot dynamics, by which the negative influence of autopilot lag is compensated. In [1][2][3], guidance laws are studied for the near space interception of maneuvering target, in which the autopilot is approximated as first-order dynamics. Actually, the autopilot 2 International Journal of Aerospace Engineering is of high-order dynamics.…”

Section: Introductionmentioning

confidence: 99%

Three-Dimensional Integrated Guidance and Control for Near Space Interceptor Based on Robust Adaptive Backstepping Approach

Gao

Jiang

Zhang

et al. 2016

International Journal of Aerospace Engineering

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This study presents a novel integrated guidance and control method for near space interceptor, considering the coupling among different channels of the missile dynamics, which makes the most of the overall performance of guidance and control system. Initially, three-dimensional integrated guidance and control model is employed by combining the interceptor-target relative motion model with the nonlinear dynamics of the interceptor, which establishes a direct relationship between the interceptor-target relative motion and the deflections of aerodynamic fins. Subsequently, regarding the acceleration of the target as bounded uncertainty of the system, an integrated guidance and control algorithm is designed based on robust adaptive backstepping method, with the upper bound of the uncertainties unknown. Moreover, a nonlinear tracking differentiator is introduced to reduce the “compute explosion” caused by backstepping method. It is proved that tracking errors of the state and the upper bound of the uncertainties converge to the neighborhoods of the origin exponentially. Finally, simulations results show that, compared to the conventional guidance and control design, the algorithm proposed in this paper has greater advantages in miss distance, required normal overload, and flight stability, especially when attacking high-maneuvering targets.

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Impact Time Guidance Law Considering Autopilot Dynamics Based on Variable Coefficients Strategy for Maneuvering Target

Cited by 4 publications

References 18 publications

Sliding mode control and Lyapunov based guidance law with impact time constraints

Sliding mode control and Lyapunov based guidance law with impact time constraints

Terminal Guidance Law for UAV Based on Receding Horizon Control Strategy

Three-Dimensional Integrated Guidance and Control for Near Space Interceptor Based on Robust Adaptive Backstepping Approach

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