Design of Three-Dimensional Guidance Law for Tactical Missiles

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

doi:10.2514/6.2018-1323

Cited by 4 publications

(2 citation statements)

References 23 publications

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“…Due to this fact, different variants of PN guidance such as modified proportional navigation [3], switched biased proportional navigation [4], predictive proportional navigation [5], augmented proportional navigation [6] etc have been proposed in the literature to minimize the miss distance by either estimating or predicting the target maneuver. Various guidance laws based on control theory [7,8,9] and optimal theory [10,11,12] have also been proposed. However, they require information about target states which must be estimated.…”

Section: Introductionmentioning

confidence: 99%

Improvements in Classical Proportional Navigation Guidance Using Fuzzy Logic

Balraj Sharma

2023

joast

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The performance of classical Proportional Navigation guidance is limited against highly maneuvering targets and in presence of measurements noise resulting into large miss distances and lower hit probability. Also, the advanced Augmented PN guidance technique requires target state estimation. In this paper, fuzzy logic has been used to implement PN guidance and Membership Functions of fuzzy logic has been tuned using genetic algorithm. The proposed Fuzzy Based PN (FBPN) guidance gives superior performance than PN and APN in terms of lower miss distance, higher hit ratio and better ability to handle measurement noise at all target attack aspects. Deterministic simulations have proved the superior performance and robustness of proposed scheme for various conditions such as step target maneuver upto 9g, weaving maneuver and presence of measurement noise. Further, Monte Carlo simulations have proved that proposed scheme enhances interception performance in realistic scenarios by improving the hit ratio upto 48% and rms miss distance upto 41%. Limitations of APN scheme in terms of target state estimation is also mitigated in the proposed guidance scheme. Finally, global asymptotic stability of fuzzy homing guidance loop is proved using circle criterion.

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Section: Introductionmentioning

confidence: 99%

Improvements in Classical Proportional Navigation Guidance Using Fuzzy Logic

Balraj Sharma

2023

joast

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“…However, the cross-coupling effects between the two planes are neglected in this simplified method, which will make the guidance precision reduce. [1][2][3] Therefore, to improve the guidance performance of the missile system, various guidance techniques in three-dimensional space have been investigated, such as proportional navigation guidance law, 4,5 optimal guidance law, 6 feedback linearisation-based guidance law 7 and nonlinear guidance law. 8,9 Li et al 9 designed a novel finite-time three-dimensional nonlinear terminal guidance law for intercepting manoeuvring targets by using the theory of finite-time input-to-state stability.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional impact angles constrained integral sliding mode guidance law for missiles with input saturation

Qian

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper proposes the three-dimensional impact angles constrained integral sliding mode guidance laws for the missile with the constraint of the input saturation. To solve the problem of the input constraint, an integral sliding mode surface is given for the first time by using the saturation function. The first three-dimensional integral sliding mode guidance law can solve the impact angle constraint and the target accelerations with known upper bound, while the second one can solve the impact angle constraint, input saturation, and the target accelerations with unknown upper bound simultaneously. Finally, numerical simulations are used to verify the effectiveness of the guidance laws.

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Three-Dimensional Optimal Guidance with Lyapunov Redesign for UAV Interception

Zhu

2021

Guid. Navigat. Control

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Three-dimensional guidance laws are designed to intercept non-maneuvering targets and maneuvering targets in this paper. An optimal control approach with constant or time-variant feedback gain is proposed for interception. The cost function is designed with considerations on energy-efficiency and time-efficiency in the transient process. Lyapunov redesign method is applied to treat the target acceleration, where the precise information of target accelerations is not necessarily required. Efficacy of the proposed guidance laws is proved theoretically and verified by simulation results.

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Design of Three-Dimensional Guidance Law for Tactical Missiles

Cited by 4 publications

References 23 publications

Improvements in Classical Proportional Navigation Guidance Using Fuzzy Logic

Improvements in Classical Proportional Navigation Guidance Using Fuzzy Logic

Three-dimensional impact angles constrained integral sliding mode guidance law for missiles with input saturation

Three-Dimensional Optimal Guidance with Lyapunov Redesign for UAV Interception

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