Non-fragile H&amp;infin; controller for combustion process in rocket motors

Wu, Yongbo; Zhang, Hexin; Hui, Junjun; Zhou, Xin

doi:10.1504/ijaac.2018.092848

Cited by 2 publications

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“…This actuation hardware, which is generally pretty different to typical valves, is able to quickly adjust the combustion input in terms of injection timing instead of the traditional spatial distribution modification. Some research works concerning monopropellant rocket-engine combustion control via pintle devices or pressure regulators are [26,27,28]. However, that loop lies beyond the scope of this review, devoted to the control of the engine system as a whole.…”

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confidence: 99%

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A survey of automatic control methods for liquid-propellant rocket engines

Pérez-Roca

Marzat

Piet-Lahanier

et al. 2019

Progress in Aerospace Sciences

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The main purpose of this survey paper is to review the field of convergence between the liquid-propellant rocketpropulsion and automatic-control disciplines. A comprehensive collection of academic works and some industrial developments are summarised and discussed, making the link to the current context of launcher reusability. The main control problem in liquid-propellant rocket engines (LPRE), the target of this survey, generally consists in tracking set-points in combustion-chamber pressure and mixture ratio, their main operating quantities. This goal is attained via the adjustment of flow-control valves while complying with operating constraints. Each aspect of control systems, ranging from modelling to the actual control techniques, is reviewed and subsequently related to the rest of aspects. The comparison of the different approaches points to the general use of linearised models about concrete operating points for deriving steady-state controllers, which in most cases are of PID type. Other more sophisticated approaches present in the literature, incorporating some nonlinear, hybrid or robust techniques, improve certain aspects of performance and robustness. Nevertheless, no fully nonlinear or hybrid frameworks, which may allow the control of a wider throttling domain, have been published. In addition, control during the thermally and structurally demanding transient phases is usually in open loop, and hence with low correction margins. This sort of control enhancements, probably together with more sophisticated monitoring architectures, would serve to extend the life of LPRE, a significant factor in their reusability. Therefore, this survey intends to draw a path for the future control design trends which will certainly be more suitable for reusable LPRE.

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Section: ) With Turbopump-redlines Verification Bymentioning

confidence: 99%

“…The damaging combustion instabilities, which might be specifically controlled in simple engines (e.g. monopropellant pressure-fed [26,28]), are more prone to appear in those cases. The management of this problem, apart from involving other design considerations, directly affects the control system.…”

Section: Mimo Lpv Lftmentioning

confidence: 99%

A survey of automatic control methods for liquid-propellant rocket engines

Pérez-Roca

Marzat

Piet-Lahanier

et al. 2019

Progress in Aerospace Sciences

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“…Recently, a delay-dependent state-feedback controller design for uncertain linear time-varying delay systems is established in Venkatesh et al (2018b) using LK functional and Wirtinger's inequality. A robust non-fragile H ∞ controller for combustion process in rocket motors is analysed using free-weighting matrix approach in Wu et al (2018). On the other hand, when the states are not available, a state estimator is required in the design process.…”

Section: Introductionmentioning

confidence: 99%

Observer-based controller design for linear time-varying delay systems using a new Lyapunov-Krasovskii functional

Venkatesh¹,

Patra

Ray

2021

IJAAC

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This paper presents an observer-based controller design method for linear systems with interval time-varying state-delay. In this work, using a new Lyapunov-Krasovskii (LK) functional, a less conservative stabilisation criterion is derived. The Wirtinger's inequality and reciprocally convex combination lemma are exploited to develop a computationally tractable method by representing the design constraints in linear matrix inequality (LMI) framework. Numerical examples are given to demonstrate the superiority of the proposed results over the existing method.

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Non-fragile H∞ controller for combustion process in rocket motors

Cited by 2 publications

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A survey of automatic control methods for liquid-propellant rocket engines

A survey of automatic control methods for liquid-propellant rocket engines

Observer-based controller design for linear time-varying delay systems using a new Lyapunov-Krasovskii functional

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