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An MPC Approach to Transient Control of Liquid-Propellant Rocket Engines

机译：液相色调火箭发动机瞬态控制的MPC方法

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The current context of launchers reusability requires the improvement of control algorithms for their liquid-propellant rocket engines. Their transient phases are generally still performed in open loop. In this paper, it is aimed at enhancing the control performance and robustness during the fully continuous phase of the start-up transient of a generic gas-generator cycle. The main control goals concern end-state tracking in terms of combustion-chamber pressure and chambers mixture ratios, as well as the verification of a set of hard operational constraints. A controller based on a nonlinear preprocessor and on linear MPC (Model-Predictive Control) has been synthesised, making use of nonlinear state-space models of the engine. The former generates the full-state reference to be tracked while the latter achieves the aforementioned goals with sufficient accuracy and verifying constraints for the required pressure levels. Robustness considerations are included in the MPC algorithm via an epigraph formulation of theminimaxrobust optimisation problem, where a finite set of perturbation scenarios is considered.
机译：目前发射器可重用性的上下文需要改进其液体推进剂火箭发动机的控制算法。它们的瞬态阶段通常仍在开环中执行。在本文中，旨在在通用气体发生器周期的启动瞬态的完全连续相位期间提高控制性能和鲁棒性。主控制目标涉及燃烧室压力和腔室混合比的终端状态跟踪，以及验证一组硬操作约束。已经合成了基于非线性预处理器和线性MPC（模型预测控制）的控制器，利用发动机的非线性状态空间模型。前者在后者以足够的准确度和验证所需压力水平验证约束的情况下，将跟踪要跟踪的全状态参考。鲁棒性考虑因素包括在MPC算法中，通过主题XOSROS优化问题的ePIGRAPH制定，其中考虑了一组有限的扰动场景。

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