Actuator Fault Tolerant System For Cryogenic Combustion Bench Cooling Circuit

Sarotte, Camille; Marzat, Julien; Piet-Lahanier, Hélène; Iannetti, A.; Galeotta, Marco; Ordonneau, G.

doi:10.1016/j.ifacol.2018.09.636

Cited by 5 publications

(8 citation statements)

References 10 publications

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“…Another easier modelling alternative is defining equations already in the frequency domain in a linear way [38,39,37]. Describing functions have been used in one reference [47]; in fact most authors have linearised their nonlinear models about steady-state points [29,31,24,40,41,42,43,44,5,26,45], which limits representativeness to a narrow region around those points, as explicitly stated by [43] for instance. The only control-oriented nonlinear modelling approaches present in the literature dealt with engine performance simulations [48,51,49], state-space analysis [50], OL optimisation [36,54,55], neural networks [52,53] and hybrid models [56].…”

Section: Summary and Discussionmentioning

confidence: 99%

“…Indeed, the interaction of HMS and control, currently still pretty separate, is considered as a major development area by [68], since it would enhance engine robustness and reliability and hence reusability. The recent work of [45] proposes concrete solutions in this direction, applied to an LPRE subsystem. Besides, transient sequences like start-up or shutdown present discrete-events phases which are still performed in OL nowadays.…”

Section: Summary and Discussionmentioning

confidence: 99%

“…The presence of algebraic equations complicates the process, attaining a matrix of dimension 99. Further examples of linearised models can be found in [44], [45], or in [26] and [27], where the Crocco monopropellant combustion model [46] is used.…”

Section: Linearised Modelsmentioning

confidence: 99%

“…A proposed solution may be delaying the thrust computation based on the valve position until the algorithm converges. Another fault-tolerant strategy is carried out by Sarotte et al [45] for the cooling circuit of a cryogeniccombustion test bench. This test bench, Mascotte by CNES/ONERA, was developed so as to investigate heat transfer in combustion chambers and jet separation in nozzles in realistic conditions comparable to the Vulcain 2 engine.…”

Section: Reconfigurable Controlmentioning

confidence: 99%

See 3 more Smart Citations

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: Summary and Discussionmentioning

confidence: 99%

Section: Summary and Discussionmentioning

confidence: 99%

Section: Linearised Modelsmentioning

confidence: 99%

Section: Reconfigurable Controlmentioning

confidence: 99%

See 2 more Smart Citations

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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“…where we denote B + c as the pseudo-inverse of B c , −B + c B cfk is the fault compensation part and W c (X c,k − X k ) is the reconfiguration part. The fault magnitude estimationf k is assumed to be estimated with a filter and the gain W c is calculated with a linear quadratic regulator [13], [14]. The reference state trajectory X k is predetermined and its dynamics is given by:…”

Section: System Descriptionmentioning

confidence: 99%

Anti-windup Design for Linear Discrete-time Systems Subject to Actuator Additive Faults and Saturations

Sarette¹,

Marzat²,

Piet-Lahanier³

et al. 2019

2019 American Control Conference (ACC)

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In this paper a method is proposed to design an anti-windup scheme for discrete time linear systems with input saturations and actuator additive failures. This method provides a fault tolerant system reconfiguration mechanism with a control law which compensates for the estimated actuator additive faults and maintains the overall system stability in spite of actuator saturations. The design approach is derived from the solution of linear matrix inequalities (LMI) to guarantee the stability regions. For that purpose the fault tolerant control method is based on a linear quadratic regulator (LQR) and a fault estimator for compensation purposes. This method was tested in realistic simulations with the software Carins (CNES) on a pressure and mass flow rate model of a cryogenic test bench cooling circuit.

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Trajectory Planning and Tracking via MPC for Transient Control of Liquid-Propellant Rocket Engines

Pérez-Roca

Marzat

Piet-Lahanier

et al. 2022

Lecture Notes in Control and Information Sciences - Proceedings

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The new scenarios associated with launchers reusability force the enhancement of control algorithms for their liquid-propellant rocket engines. The transient phases of these engines are generally executed in open loop. The goal of this paper is to improve the control performance and robustness throughout the fully continuous phase of the start-up transient of a generic gas-generator cycle. The controller has to guarantee an accurate tracking in terms of combustion-chamber pressure and chambers mixture ratios, as well as to satisfy a set of hard operational constraints. The selected strategy comprises a nonlinear preprocessor and a linearised MPC (Model-Predictive Control) controller, making use of nonlinear state-space models of the engine. The former plans the reference trajectory of states and control, which is tracked by the latter. Control goals are attained with sufficient accuracy while verifying constraints within the desired throttling range. Robustness to internal parameters variations is considered in the MPC controller by means of an epigraph formulation of the minimax robust optimisation problem, where a finite set of parameter-variation scenarios is treated.

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Actuator Fault Tolerant System For Cryogenic Combustion Bench Cooling Circuit

Cited by 5 publications

References 10 publications

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

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

Anti-windup Design for Linear Discrete-time Systems Subject to Actuator Additive Faults and Saturations

Trajectory Planning and Tracking via MPC for Transient Control of Liquid-Propellant Rocket Engines

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