A sequential co-design framework has been developed in a previous study (Nguyen-Van et al., IFAC-PapersOnLine 52(12):514–519, https://doi.org/10.1016/j.ifacol.2019.11.295, 2019)) to design an aircraft using active differential thrust. Differential thrust is used instead of a rudder to generate the yawing moment. The objective is to dimension in parallel the vertical tail surface area, the electric motor bandwidth and control laws while maintaining imposed handling qualities. This paper focuses on the development of a single step co-design taking into account handling qualities, flight envelop requirements and motor saturation. Additional and compatible optimisation constraints are found based on a sensitivity analysis. It reveals the importance of electric motor bandwidth with respect to aircraft natural stability. The direct co-design leads to an optimised trade-off between vertical tail and electric motor bandwidth.
Co-design of aircraft vertical tail and control laws with distributed electric propulsion and flight envelop constraints
CEAS Aeronaut J
CEAS Aeronautical Journal ; 12 , 1 ; 101-113
2021-01-01
13 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Distributed electric propulsion , Differential thrust , Vertical tail reduction , Aircraft handling qualities , Co-design , <inline-formula id="IEq1"><alternatives><mml:math><mml:msub><mml:mi>H</mml:mi><mml:mi>∞</mml:mi></mml:msub></mml:math><inline-graphic xlink:href="13272_2020_481_Article_IEq1.gif" /></alternatives></inline-formula> Control design Engineering , Aerospace Technology and Astronautics
British Library Conference Proceedings | 2018
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