Structured H∞ synthesis for flexible launcher control

In this paper, the feasibility of structured H∞ control design is demonstrated in representative environment for flexible launcher control during non-stationary ascent phase. Robust control is achieved and performances are improved with respect to non structured H∞ controller; furthermore, numerous simplifications in control design process are highlighted providing flight control development cost reduction perspectives. These results pave the way towards industrial application of structured H∞ framework for existing and future European launcher control. Further research axes are currently under investigation in the frame of co-funded AIRBUS DS and CNES researches.