Multi-objective H2/H∞/Impulse-to-Peak Control of a Space Launch Vehicle
Multi-objective H2/H∞/Impulse-to-Peak Control of a Space Launch Vehicle
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航天运载火箭的多目标 H2/H∞/脉冲峰值控制
DOI：
10.3166/ejc.12.57-70
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发表时间：
2006
期刊：
影响因子：
--
通讯作者：
D. Peaucelle
中科院分区：
文献类型：
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作者：
D. Arzelier;B. Clement;D. Peaucelle
研究了一个涉及h2、H∞和脉冲峰值性能的多目标综合问题。一般来说，多目标控制问题是很难解决的问题，并且没有精确的解。本文提出了LTI离散系统在H∞约束下的混合h2 /冲峰优化的LMI公式。这个框架然后被用来控制空间发射器的姿态。定义了特定的控制结构，求解了多目标H 2 / H∞/脉冲峰值综合问题。定义了包括设计参数调整在内的系统综合程序，并给出了仿真结果。
A multi-objective synthesis problem involving H 2 , H ∞ and impulse-to-peak performances is investigated. In general, multi-objective control problems are hard problems to solve and do not have exact solutions. Here, an LMI formulation is proposed for the mixed H 2 /impulse-to-peak optimization under an H ∞ constraint for LTI discrete-time systems. This framework is then used to control the attitude of a space launcher. A particular control structure is defined and a multiobjective H 2 / H ∞ /impulse-to-peak synthesis problem is solved to tackle specific specifications. A systematic synthesis procedure including the tuning of design parameters is defined and results from simulations are presented.