Autopilot Design for Bank-to-Turn Missiles Using Receding Horizon Predictive Control Scheme

Kim, Myung Joon; Кwon, Wook Hyun; Kim, Yong Ho; Song, Chanho

doi:10.2514/2.4184

Cited by 16 publications

(8 citation statements)

References 12 publications

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“…In recent years, the nonlinear design method has also developed rapidly, some researchers applied the feedback linearization method and the backstepping design method into the BTT autopilot design to solve the problem of strong coupling nonlinear characteristics in the system in Adams and Banda (1993), Reiner et al (1996) and Zhang et al (2010). Some intelligent control methods such as the neural networks and the fuzzy control are attempted for the BTT controller design and ideal simulation results are obtained in , Kim et al (1997), Lin and Wang (1998), McDowell and Irwin (1997), Huey and Bor (2002), Lin (2005), Duan et al (2009) and Zheng et al (2011).…”

Section: Introductionmentioning

confidence: 98%

μ-Synthesis robust controller design for the supercavitating vehicle based on the BTT strategy

et al. 2014

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Section: Introductionmentioning

confidence: 98%

μ-Synthesis robust controller design for the supercavitating vehicle based on the BTT strategy

et al. 2014

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“…Various strategies have been proposed to deal with these complexities and difficulties in the past few decades. Some conventional control methods – gain-scheduling control (Carter and Shamma, 1996), model predictive control (Kim et al, 1997), switching control (Liu et al, 2015) and characteristic model-based adaptive control (Zhang and Hu, 2012) – have been employed for advanced autopilot designs. These methods are conceptually straightforward and can improve the performance from different aspects.…”

Section: Introductionmentioning

confidence: 99%

On a novel equivalent control-based adaptive sliding mode approach for autopilot design of BTT missiles

Guo

2016

Transactions of the Institute of Measurement and Control

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This paper presents a novel equivalent control-based adaptive sliding mode control (EASMC) approach for designing the autopilot of a bank-to-turn (BTT) missile under model uncertainties and external disturbances. The sliding surface is constructed with a tracking error between the real attitude angle and the reference command. The equivalent control technique works as a mechanism for the gains over-bounded by uncertainties and this information is implemented in the adaption progress. The method guarantees that the sliding surface reaches zero in finite time and the error tracks the command value asymptotically. The advantage of this method is that the gains will be adapted to counteract uncertainties and enable the control deflection magnitude to be reduced to the minimum value, keeping the property of a finite-time convergence. The skill in choosing the gains is also given in this paper. Simulation results demonstrate that the approach proposed is able to improve the dynamic performance and robustness of a BTT missile system.

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“…[5][6][7][8][9] Also, receding horizon predictive control (RHPC) has been applied and its good tracking performance has been reported particularly in this industry. 10 Tail-controlled missiles like anti-tank missiles are non-minimum phase system. [11][12][13][14] Although both the three-loop and pole-placement control strategies can deal with non-minimum phase systems, these approaches are not successful as much as RHPC.…”

Section: Introductionmentioning

confidence: 99%

Design and comparison of autopilots of an air-to-surface antitank missile and its terminal guidance study

Ada

Kural

2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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The design of the autopilot is one of the most important algorithms of missiles. Performance of the autopilot and its robustness are significant matters to hit a target accurately. The autopilot should satisfy the desired performance under disturbances. In the scope of this study, three autopilots were offered for tracking pitch acceleration command using different control methods: three-loop classic control, pole-placement control and receding horizon predictive control. The aim of the autopilot designed by employing receding horizon predictive control is to minimize the flight control effort, and to make the close-loop system insensitive against modelling uncertainties and stochastic shattering factors. This study comes up with that the missile is able to move in desired performance under disturbances such as control surface misplacement, thrust misalignment, wind and aerodynamic uncertainties with more robustness, less control effort and minimum miss distance and terminal time using an alternative control method instead of classic and poleplacement control methods which are generally referred by the defence industry. KeywordsMissile pitch autopilot, three-loop control, pole-placement control, receding horizon predictive control, pitch mathematical model of missile Date

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Autopilot Design for Bank-to-Turn Missiles Using Receding Horizon Predictive Control Scheme

Cited by 16 publications

References 12 publications

μ-Synthesis robust controller design for the supercavitating vehicle based on the BTT strategy

μ-Synthesis robust controller design for the supercavitating vehicle based on the BTT strategy

On a novel equivalent control-based adaptive sliding mode approach for autopilot design of BTT missiles

Design and comparison of autopilots of an air-to-surface antitank missile and its terminal guidance study

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