New Integrated Guidance and Control of Homing Missiles with an Impact Angle against a Ground Target

Yang, Seung-Han; Guo, Jianguo; Zhou, Jun

doi:10.1155/2018/3968242

Cited by 16 publications

(13 citation statements)

References 25 publications

(44 reference statements)

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“…xðtÞdt; … (19) where xðt b Þ and xðt a Þ represents the state variables at time t b and t a , respectively. An LQR control-based optimisation framework was, therefore, formulated which utilises a set of dynamic constraints represented by Equations (1)-(4), path constraints shown in Equations (17) and terminal constraints of Equations (18), while minimising the performance measure represented by Equation (15). As a result of the optimisation process, steady-state values for the state and control variables along various optimal trajectories (governed by Equation (14)) were obtained.…”

Section: Formulation Of Optimal Control Problemmentioning

confidence: 99%

“…Due to the robustness of the control law, the proposed methodology could be applied to many realistic engagement scenarios including uncertainties such as a moving target. Similarly, Hou et al ( 15 ) utilised a combination of non-linear extended disturbance observer and sliding mode control techniques to design the integrated guidance and control law for homing missiles against ground-fixed targets. Vaddi ( 16 ) used the numerical state-dependent Riccati equation technique with a more comprehensive model characterised by non-linear motion in the dimensions.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Guidance and control of standoff air-to-surface carrier vehicle

Mir

Akhtar²,

Eisa

et al. 2019

Aeronaut. j.

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This paper presents an open framework, through which, conventional general purpose aerial munitions can be converted into smart munitions. The retrofit consists of a smart adaptation kit (SAK) having a dedicated Guidance and Control Module (GCM). The adaptation kit along with the GCM ensures that the SAK glide optimally towards the designated target. To reduce cost, the number of control surfaces of the SAK has been kept to a bare minimum, which resulted in an under actuated system. The methodology proposed utilises the theory of gain-scheduled control and leads to an efficient procedure for the design of the controllers, which accurately track reference trajectories defined in an inertial reference frame. The paper illustrates the application of this procedure to the design of stabilisation and tracking controller for the SAK. The design phase is summarised, and the performance of the resulting controllers is assessed in simulation using dynamic model of the vehicle. Simulation results show that apart from improved circular error probable (CEP) of hitting the target, munition ballistic range has also significantly increased with the proposed modification.

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Section: Formulation Of Optimal Control Problemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Guidance and control of standoff air-to-surface carrier vehicle

Mir

Akhtar²,

Eisa

et al. 2019

Aeronaut. j.

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show abstract

“…Some attempts have been made on the design of IGC law with impact angle constraint [31]. To achieve the desired terminal impact angle, a new IGC law is proposed for a homing missile [32]. In order to intercept the ground fixed target and ground maneuvering target, a new IGC law is investigated for a STT homing missile with impact angle constraints [33].…”

Section: Introductionmentioning

confidence: 99%

Impact Angle Constrained Three-Dimensional Integrated Guidance and Control Based on Fractional Integral Terminal Sliding Mode Control

et al. 2019

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In this paper, considering a class of skid-to-turn (STT) missile with impact angle constraint to intercept the maneuvering target, a three-dimensional integrated guidance and control law based on the fractional integral terminal sliding mode control (FITSMC) scheme is proposed. Firstly, a three-dimensional integrated guidance and control model is established for missile-target relative motion and nonlinear missile dynamics with multiple system uncertainties and unknown disturbances. Secondly, in order to achieve the desired impact angle in finite-time without singularity, a novel nonsingular FITSMC scheme is employed to construct the sliding surface, and a modified filter is applied to dynamic surface control design. Also, an extended state observer is introduced to estimate and compensate the system uncertainties and unknown disturbances. Then, a robust integrated guidance and control scheme with impact angle constraint is developed using aforementioned techniques. Furthermore, the finite-time stability of the closed-loop system is proven based on Lyapunov theory. Finally, the effectiveness and robustness of the proposed integrated guidance and control algorithm are verified through numerical simulations.INDEX TERMS Integrated guidance and control, impact angle constraint, fractional integral terminal sliding mode control, finite-time convergence, dynamic surface control.

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“…3–12 In Gao et al., 3 an adaptive guidance law was proposed for attacking a ground target in the presence of impact angle using adaptive control technique and feedback guidance strategy. In Yang et al., 4 a new integrated guidance and control law was proposed for a homing missile subject to impact angle, which can be applied for an efficient salvo attack of ground target. In Park et al., 5 Tsalik and Shima, 6 and Lee and Seo, 7 based on the optimal control theory, the optimal guidance laws were proposed.…”

Section: Introductionmentioning

confidence: 99%

Adaptive back-stepping sliding mode guidance laws with autopilot dynamics and acceleration saturation consideration

Geng

Zhang

Sun

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper studies the guidance scheme for the terminal guidance problem subject to input constraints, attack angle constraints, and second-order dynamics of missile autopilot. Firstly, the guidance system model with the above multi-constraint model is given. Secondly, an anti-saturation back-stepping guidance law which makes use of the low-pass filter to avoid the differential of the virtual control signals is designed based on the terminal sliding mode method, auxiliary system, and adaptive technique. Finally, Lyapunov theory and numerical simulations are utilized to prove that the states of the system under the proposed guidance law are uniformly ultimately bounded.

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New Integrated Guidance and Control of Homing Missiles with an Impact Angle against a Ground Target

Cited by 16 publications

References 25 publications

Guidance and control of standoff air-to-surface carrier vehicle

Guidance and control of standoff air-to-surface carrier vehicle

Impact Angle Constrained Three-Dimensional Integrated Guidance and Control Based on Fractional Integral Terminal Sliding Mode Control

Adaptive back-stepping sliding mode guidance laws with autopilot dynamics and acceleration saturation consideration

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