Capturing nonlinear time-dependent aircraft dynamics using a wind tunnel manoeuvre rig

Sergio Araujo-Estrada*, Mark H Lowenberg , Simon A Neild

*Corresponding author for this work

Research output: Contribution to journalArticle (Academic Journal)peer-review

4 Citations (Scopus)
21 Downloads (Pure)

Abstract

This paper considers a novel multi-degree-of-freedom dynamic manoeuvre rig,
with the aim of assessing its potential for capturing aircraft model nonlinear time dependent dynamics in the wind tunnel. The dynamic manoeuvre rig capabilities are demonstrated via a series of experiments involving a model aircraft in a closed section low-speed wind tunnel. A series of open loop experiments show that the aircraft model exhibits nonlinear time dependent dynamics. This nonlinear behaviour manifests itself as limit cycle oscillations that increase in complexity with the number of degrees-of-freedom in which the aircraft is allowed to move. Two real-time closed loop control experiments further illustrate the manoeuvre rig potential: first, using a pitch motion configuration, an experiment is conducted to investigate the limit cycle behaviour in more detail, allowing the stability properties of the pitch oscillations to be assessed; secondly, using a 5-DOF motion configuration, the test motion envelope is extended by using a compensating feedback control law to track the aircraft’s roll motion. Together, these experiments demonstrate the manoeuvre rig potential to reveal aircraft nonlinear and unsteady phenomena.
Original languageEnglish
Article number107325
Number of pages37
JournalAerospace Science and Technology
Volume121
Early online date13 Jan 2022
DOIs
Publication statusPublished - 1 Feb 2022

Bibliographical note

Funding Information:
S. A. Araujo-Estrada's research was supported by the National Council of Science and Technology, Mexico (CONACYT-Mexico), studentship # 215262. S. Neild was supported by an EPSRC fellowship (EP/K005375/1). The authors thank Prof. Mikhail Goman for his insights and suggestions on the development of this rig and the work described in this paper. The authors would like to thank and acknowledge Mr Lee Winter from the University of Bristol wind tunnel laboratory, for his invaluable support and work during the refitting, assembly and modification of the equipment used to carry out the experiments presented in this paper.

Funding Information:
S. A. Araujo-Estrada's research was supported by the National Council of Science and Technology, Mexico (CONACYT-Mexico), studentship # 215262 . S. Neild was supported by an EPSRC fellowship ( EP/K005375/1 ). The authors thank Prof. Mikhail Goman for his insights and suggestions on the development of this rig and the work described in this paper. The authors would like to thank and acknowledge Mr Lee Winter from the University of Bristol wind tunnel laboratory, for his invaluable support and work during the refitting, assembly and modification of the equipment used to carry out the experiments presented in this paper.

Publisher Copyright:
© 2022 Elsevier Masson SAS

Keywords

  • wind tunnel
  • dynamic testing
  • limit cycle oscillations
  • bifurcations
  • nonlinear dynamics
  • aerodynamic hysteresis

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