Structural load alleviation using distributed delay shaper: Application to flexible aircraft



Alam, M ORCID: 0000-0001-6663-8670 and Hromcik, M
(2019) Structural load alleviation using distributed delay shaper: Application to flexible aircraft. Control Engineering Practice, 89. 130 - 142.

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Abstract

© 2019 Elsevier Ltd Lightweight flexible aircraft suffers from unwanted oscillatory vibrations during aircraft manoeuvres. A recently developed distributed-delay signal (DZV) shaper is therefore proposed to be applied as a feedforward controller to alleviate the manoeuvre loads, as an alternative to traditional structural filters used routinely in this context. Structural filters are essentially linear low-pass filters with bandwidth below the significant flexible modes, applied to control signals generated either by the pilot's direct input or by the flight control system. It has been showed that if instead a properly tuned signal shaper is used, better performance can be achieved: first, the target modes are significantly attenuated while the responsiveness of the aircraft is less compromised and secondly, the oscillatory nature of the vibrations are reduced. The high fidelity simulation results on a full scaled dynamic model of a highly flexible blended wing–body (BWB) aircraft show that in comparison to traditional structural filters, signal shapers significantly reduce the wing root loading (forces and moments) which provides potential structural benefits.

Item Type: Article
Depositing User: Symplectic Admin
Date Deposited: 22 Jul 2019 15:38
Last Modified: 25 Aug 2021 13:11
DOI: 10.1016/j.conengprac.2019.05.005
URI: https://livrepository.liverpool.ac.uk/id/eprint/3050201