Design of 3D Guidance Law for Tactical Missiles

Pandit, Sikander; Panchal, Bhavnesh; Talole, S. E.

doi:10.1007/978-981-10-5849-3_7

Cited by 2 publications

(4 citation statements)

References 7 publications

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“…Differentiating equation (11) with respect to time, it follows from equations (10) and (13) that where…”

Section: Formulationmentioning

confidence: 99%

“…In practice, the target-to-interceptor engagement is constituted in the three-dimensional (3D) environment, and so the engagement is rigorously governed by a set of nonlinear coupling equations. Some existing 3D guidance laws 9,10 are hardly used in the guidance of KKV, as it requires the strong capability anti-disturbances and very fast convergence to guarantee the guidance precision for intercepting maneuvering hypersonic targets via hit-to-kill.…”

Section: Introductionmentioning

confidence: 99%

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Extended state observer-based finite-time guidance laws on account of thruster dynamics

Duan

Zhou

Da-lin³

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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Guidance laws are designed for a near space interceptor with line-of-sight angle as input and on–off type thrust as output. The dynamics of thruster is viewed as a first-order lag with on–off working style and is integrated with the target–interceptor engagement dynamics to design bang-bang type sliding mode guidance laws. An extended state observer is designed to estimate the line-of-sight angular rate and the acceleration of target with the line-of-sight angle as a measurement. It is rigorously proved that the states of guidance system converge to a neighborhood of sliding mode in finite time and the line-of-sight angular rate converges to a neighborhood of the origin along the sliding mode in finite time under the designed guidance laws. Furthermore, in order to reduce the switching frequency of thruster, a sliding mode guidance law with hysteresis-band according to the sufficient condition for finite time convergence is proposed. Then, it is integrated with the bang-bang type sliding mode guidance law to yield a composite guidance law. Simulation results show that the extended state observer can effectively estimate the line-of-sight angular rate and the target acceleration, and the proposed sliding mode guidance laws have better performance than typical proportional guidance law.

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“…Differentiating equation (11) with respect to time, it follows from equations (10) and (13) that where…”

Section: Formulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Extended state observer-based finite-time guidance laws on account of thruster dynamics

Duan

Zhou

Da-lin³

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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show abstract

“…In [3,4], a bias pure proportional guidance law is designed for intercepting stationary or slow targets. In order to achieve the best damage effect, a three-dimensional proportional guidance law with angle constraint is designed for the relative motion model of three-dimensional missile and target [5,6]. In [7,8], based on the optimal control theory, the guidance law with impact angle constraint is designed.…”

Section: Introductionmentioning

confidence: 99%

“…The relative kinematic equation of the missile and target is as follows [13] a and zt a are the target accelerations in the pitch and yaw directions, respectively. Based on (5) and 7, then the following equation holds…”

Section: Introductionmentioning

confidence: 99%

Design of Three-Dimensional Guidance Law With Impact Angle Constraints and Input Saturation

Qian

2020

IEEE Access

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This thesis studies the problem of three-dimensional guidance considering maneuvering acceleration and input saturation based on the background of missile intercepting maneuvering target. On the basis of the three-dimensional guidance model with impact angle constraints, an adaptive integral sliding mode three-dimensional guidance law is designed using integral sliding mode control theory and adaptive algorithm. By introducing an auxiliary system, an adaptive anti-saturation integral sliding mode three-dimensional guidance law is designed, which can solve the problem of input saturation, The stability of the designed guidance law is proved by Lyapunov theory, which ensures that the sliding mode manifold converges to zero in finite time. The effectiveness of the designed guidance law is verified by simulation analysis.

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Design of 3D Guidance Law for Tactical Missiles

Cited by 2 publications

References 7 publications

Extended state observer-based finite-time guidance laws on account of thruster dynamics

Extended state observer-based finite-time guidance laws on account of thruster dynamics

Design of Three-Dimensional Guidance Law With Impact Angle Constraints and Input Saturation

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