Linear Frequency Domain and Harmonic Balance Predictions of Dynamic Derivatives

Ronch, Andrea Da; McCracken, A.J.; Badcock, K. J.; Widhalm, Markus; Campobasso, M. Sergio

doi:10.2514/1.c031674

Cited by 70 publications

(25 citation statements)

References 44 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…This method is able to decompose the flow into several modes with a single frequency and growth rate, which has been extensively used to study linear, periodic and even nonlinear flow cases [66][67][68][69]. The harmonic balance method allows a direct calculation of the periodic state, which has been used for both aeroelastic simulations [70] and dynamic derivative predictions [71]. The Jacobian-based Taylor expansion methods also belong to projection-based methods as the full-order system is projected onto a basis formed by a small number of eigenvectors of the Jacobian matrix, which have been successfully used in the control design of flexible aircraft [72].…”

Section: Reduced-order Model For the Unsteady Flowmentioning

confidence: 99%

Transonic aeroelasticity: A new perspective from the fluid mode

Gao

Zhang

2020

Progress in Aerospace Sciences

View full text Add to dashboard Cite

Within the transonic regime, the aeroelastic problems exhibit many unique characteristics compared with subsonic and supersonic cases. Although a lot of research has been carried out in this field, the underlying mechanisms of these complex phenomena are not clearly understood yet, resulting in a challenge in the design and use of modern aircraft. This review summarizes the recent investigations on nonclassical transonic aeroelastic problems, including transonic buzz, reduction of transonic buffet onset, transonic buffeting response and frequency lock-in phenomenon in transonic buffet flow. After introducing the research methods in unsteady aerodynamics and aeroelastic problems, the dynamical characteristics as well as the physical mechanisms of these phenomena are discussed from the perspective of the fluid mode. In the framework of the ROM (reduced order model) -based model, the dominant fluid mode (or the eigenvalue) and its coupling process with the structural model can be clearly captured. The flow nonlinearity was believed to be the cause of the complexity of transonic aeroelasticity. In fact, this review indicates that the complexity lies in the decrease of the flow stability in the transonic regime. In this condition, the fluid mode becomes a principal part of the coupling process, which results in the instability of the fluid mode itself or the structural mode, and thus, it is the root cause of different transonic aeroelastic phenomena.

show abstract

Section: Reduced-order Model For the Unsteady Flowmentioning

confidence: 99%

Transonic aeroelasticity: A new perspective from the fluid mode

Gao

Zhang

2020

Progress in Aerospace Sciences

View full text Add to dashboard Cite

show abstract

“…Equation (3) can provide convincing insights into the application of the aerodynamic stability derivatives approach. Whereas a large body of work has been done on prescribed flight mechanics trajectories, [6][7][8]28 a consistent study to assess the stability derivatives approach for a flying vehicle is missing, apart from a recent work by McCracken et al 29 This research work aims to expand previous investigations. The aerodynamic moment around the centre of gravity can be expressed as…”

Section: Ivb1 Model Based On Aerodynamic Stability Derivativesmentioning

confidence: 89%

Assessing the Impact of Aerodynamic Modelling on Manoeuvring Aircraft

Ronch

McCracken

Tantaroudas

et al. 2014

AIAA Atmospheric Flight Mechanics Conference

View full text Add to dashboard Cite

This paper investigates the impact of aerodynamic models on the dynamic response of a free-flying aircraft wing. Several options for the aerodynamics are evaluated, from two-dimensional thin aerofoil aerodynamics and unsteady vortex-lattice method up to computational fluid dynamics. A nonlinear formulation of the rigid body dynamics is used in all cases. Results are generated using a numerical framework that will allow in the near future multi-disciplinary fluid/structure/flight analysis. In this paper, flexibility effects are neglected. A validation for fluid/flight models is presented. The well-established approach based on stability derivatives is also used, and is found in good agreement with solutions obtained from linear aerodynamic models. The uncertainties in predicted trajectories of the free-flying wing are, in general, large and attributed to the aerodynamics only. This suggests that a careful control law synthesis should be done to account for uncertainties from modelling techniques.

show abstract

“…The results were shown to correlate well with experimental data. Additional details regarding some of these results have been presented by Da Ronch et al [28,29].…”

Section: Introductionmentioning

confidence: 93%

“…The time-spectral stability derivative formulation presented in the following section is similar to the methods presented by Murman [21] and Da Ronch et al [27,29] in that it uses a time-periodic approximation to the unsteady CFD solution to reduce the cost of the computation. However, the forced oscillation motions used here and the linear regression approach used to determine the derivatives in this work differ somewhat from those previously used.…”

Section: Theorymentioning

confidence: 99%