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Improvement of Min-Max limit protection in aircraft engine control: An LMI approach

机译:改进飞机发动机控制中的最大-最大极限保护:LMI方法

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Current aircraft engine control logic employs a Min-Max selector structure. This structure must provide desired thrust and prevent the engine from exceeding any safety or operational limits. Careful analysis shows that there is no assurance for traditional Min-Max algorithm with linear compensators to protect output limits in transient regime, while limit violation can cause serious damages and even lead to loss of engine. In this paper, according to analysis outcomes, a strategy is presented to design linear regulators of Min-Max selector control to improve transient limit protection. For this objective, the isolated limitation loops are designed overshoot/undershoot-free to reduce the possibility of limit violation during activeness of the individual limit regulator. Despite the success of this approach, it is observed that some outputs influenced by engine acceleration or deceleration exceed their limits when other loop regulators are active. To overcome this problem, the limit values of these outputs are considered in controller design process of other loops using state feedback method and a set of linear matrix inequalities (LMIs). Simulation results show that the proposed approach effectively decreases the possibility of transient limit violation and can improve Min-Max limit protection in aircraft engine control. (C) 2017 Elsevier Masson SAS. All rights reserved.
机译:当前的飞机发动机控制逻辑采用最小-最大选择器结构。这种结构必须提供所需的推力,并防止发动机超过任何安全或操作极限。仔细的分析表明,使用线性补偿器的传统Min-Max算法无法保证在瞬态状态下保护输出限值,而违反限值可能会造成严重损害,甚至导致发动机损失。本文根据分析结果,提出了一种设计最小最大选择器控制的线性调节器的策略,以改善瞬态极限保护。为此,隔离式限制回路设计为无过冲/下冲,以减少单个限制调节器工作期间发生违反限制的可能性。尽管这种方法取得了成功,但可以观察到,当其他环路调节器处于活动状态时,受发动机加速或减速影响的某些输出会超出其极限。为了克服这个问题,在使用状态反馈方法和一组线性矩阵不等式(LMI)的其他回路的控制器设计过程中考虑了这些输出的极限值。仿真结果表明,该方法有效降低了瞬态极限违反的可能性,可以改善飞机发动机控制中的最小-最大极限保护。 (C)2017 Elsevier Masson SAS。版权所有。

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