A novel robust proportional navigation guidance law design for missile considering autopilot dynamic

Moosapour, Seyyed Sajjad; Alizadeh, Ghasem; Khanmohammadi, Sohrab; Moosapour, Hamzeh

doi:10.1177/0142331212468480

Cited by 11 publications

(9 citation statements)

References 15 publications

(16 reference statements)

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“…Kumar et al [20] presented a guidance law to intercept the targets from any initial heading angle without exhibiting any singularity. Furthermore, some guidance laws take autopilot dynamics into consideration [25,26]. Sun et al [27] studied a second order sliding mode guidance law with autopilot dynamics.…”

Section: Introductionmentioning

confidence: 99%

Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics

Wang

Tang

Shang³

et al. 2018

International Journal of Aerospace Engineering

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Terminal guidance law for missiles intercepting high maneuvering targets considering the limited available acceleration and autopilot dynamics of interceptor is investigated. Conventional guidance laws based on adaptive sliding mode control theory were designed to intercept a maneuvering target. However, they demand a large acceleration for interceptor at the end of the terminal guidance, which may have acceleration saturation especially when the target acceleration is close to the available acceleration of interceptor. In this paper, a terminal guidance law considering the available acceleration and autopilot dynamics of interceptor is proposed. Then, a fuzzy system is utilized to approximate and replace the variable structure term, which can handle the unknown target acceleration. And an adaptive neural network system is adopted to compensate the effects caused by the designed overlarge acceleration of interceptor such that the interceptor with small available acceleration can intercept the high maneuvering target. Simulation results show that the guidance law with available acceleration and autopilot dynamics (AAADG) is highly effective for reducing the acceleration command and achieving a small final miss distance.

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Section: Introductionmentioning

confidence: 99%

Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics

Wang

Tang

Shang³

et al. 2018

International Journal of Aerospace Engineering

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“…However, the performance of PNG law and its generalisations will become worse, and lack of robustness as the target's manoeuvrability increases (3) . In order to achieve satisfactory results for intercepting manoeuvring targets, many effective guidance laws based on modern control theories have been reported, such as nonlinear H ∞ guidance law (5) , sliding mode control (SMC) based guidance law (6)(7)(8) , L 2 gain guidance law (9) , Lyapunov-based guidance law (10) , adaptive guidance law (11) , differential game-based optimal guidance law (12) , robust proportional navigation guidance (RPNG) law (13) , Integral Sliding Mode Control (ISMC)based guidance law (14) and references therein. To name a few, the authors in Ref.…”

Section: Introductionmentioning

confidence: 99%

Sliding mode-based continuous guidance law with terminal angle constraint

Lin

2016

Aeronaut. j.

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In this paper, sliding mode control and disturbance observer are used to design a new continuous composite guidance law with terminal angle constraint. The robustness and finite-time convergence of the proposed guidance law is established using the Lyapunov stability theory. For performance improvement, a nonlinear disturbance observer, which can be viewed as a ‘patch’ for the original guidance law, is designed to estimate the target manoeuvre. Theoretical analysis and simulation results demonstrate the effectiveness of the proposed method.

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“…7) In Ref. 8), the authors derived a novel robust guidance law for maneuvering targets by combining integral sliding mode control theory with the classical PNG law. Shkolnikov et al 9) applied the second-order sliding mode observer to estimate the target maneuver and augmented it with PNG law to obtain a robust, augmented PNG (APNG) law.…”

Section: Introductionmentioning

confidence: 99%

Continuous Robust Guidance Law for Intercepting Maneuvering Targets

Lin

2015

Trans. Japan Soc. Aero. S Sci.

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This paper documents a new guidance law for tactical missiles to intercept maneuvering targets. By incorporating linear and fractional power nonlinear terms, a faster convergent and chatter-free acceleration command is derived. With the aid of Lyapunov stability criteria, we prove that the line-of-sight angular rate can converge to a small region around the origin in finite time. Since the target maneuver cannot be obtained or measured in real applications, a nonlinear finite time convergence disturbance observer for target maneuver estimation is introduced and a composite guidance law with finite time convergence is presented to improve the overall performance. Theoretical analysis and numerical simulations demonstrate the effectiveness of the proposed method.

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A novel robust proportional navigation guidance law design for missile considering autopilot dynamic

Cited by 11 publications

References 15 publications

Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics

Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics

Sliding mode-based continuous guidance law with terminal angle constraint

Continuous Robust Guidance Law for Intercepting Maneuvering Targets

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