Flight Dynamics Modeling of a Body Freedom Flutter Vehicle for Multidisciplinary Analyses

Leitner, Martin; Knoblach, Andreas; Kier, Thiemo; Moreno, Claudia P.; Kotikalpudi, Aditya; Pfifer, Harald; Balas, Gary J.

doi:10.2514/6.2015-0905

Cited by 4 publications

(3 citation statements)

References 8 publications

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“…One of the modes then goes quickly across the imaginary axis at the airspeed of 23 ms −1 . That phenomenon, body-freedom flutter (BFF) (22,23) , usually appears when there is a fly-wing aerodynamic configuration, or a high aspect ratio wing with a large weight. This case proves that this special flutter condition can also occur for a small aircraft with a conventional aerodynamic configuration and a light wing because the natural frequency of the 1 st structural mode with twisting dominated mode shape can decrease very fast due to the aerodynamic changes.…”

Section: Coupling Analysis For Inertial and Elastic Features Of The Wmentioning

confidence: 99%

Flight dynamic coupling analysis of a bio-inspired elastic-wing aircraft

Zhang

Wang

et al. 2018

Aeronaut. j.

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It is a challenge for small, fixed-wing aerial vehicles to maintain flight stability under gusts. Inspired by the geometric features and the structural dynamic characteristics of the gliding bird wing, an elastic wing with similar characteristics was designed and optimised for use as part of unmanned aerial vehicle. A flight dynamic model, which includes the coupling of the longitudinal flight modes and the aeroelastic modes of the flexible wing, was built to analyse the mechanisms of specific coupling for the structural characteristics of the wing design, and how these specific couplings affect flight dynamics. The results showed that the bio-inspired elastic wing effectively allows alleviation of the gust response of the prototype through coupling effects of the short period and the first aeroelastic mode, even with a considerable frequency gap. These effects become more significant when the airspeed becomes larger. The conclusions of this research can facilitate further development of bird-sized unmanned aerial vehicles to extend their applications and make these vehicles more adaptive for flight in complex atmospheric environments.

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Section: Coupling Analysis For Inertial and Elastic Features Of The Wmentioning

confidence: 99%

Flight dynamic coupling analysis of a bio-inspired elastic-wing aircraft

Zhang

Wang

et al. 2018

Aeronaut. j.

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“…Typically, for swept-back flying wing configurations, this involves the coupling of the short-period pitch mode with a bending mode. Several studies have appeared in the recent literature examining this phenomenon [9,[19][20][21][22][23] . The X-56A MUTT (Multi-Utility Technology Testbed) [24] is an ongoing program to study active control methods to suppress BFF.…”

Section: Introductionmentioning

confidence: 98%

A Load-Based Feedback Approach for Distributed Aeroservoelastic Control

Suryakumar

Mangalam

Babbar

et al. 2016

AIAA Atmospheric Flight Mechanics Conference

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An approach to aeroservoelastic control for flexible flight vehicles using the Fly-ByFeel (FBF) sensing concept is introduced. An essential feature of this sensing paradigm is the real-time measurement of circulation. Recent experiments have shown that sectional unsteady aerodynamic loads may be accurately estimated using the leading-edge stagnation point (LESP). Experimental demonstrations have also shown the use of this sensing concept for flutter suppression and gust load alleviation using a low-order energy-based approach. This work extends the sectional control formulation to flying wing configurations. Control objectives include suppressing Body-Freedom-Flutter phenomena. Aeroservoelastic control for this case may be accomplished using a spanwise-distributed, co-located sensing and controls architecture. Using load-based feedback, low-order control structures are shown to be effective for flutter suppression. Controller performance comparisons with conventional high-order state-feedback methods are investigated.

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“…The model includes the dynamics of both the rigid-body and the elastic degrees of freedom, whereas the subject vehicle is designed to flutter within its flight envelope. Leitner et al (Leitener et al , 2015) developed an integrated flight dynamic model of a body freedom flutter vehicle for multidisciplinary analyses. Krüger (2008) presented an approach to model an aeroelastic aircraft based on multi-body dynamics.…”

Section: Introductionmentioning

confidence: 99%

Gust response analysis based on a nonlinear structural model and the unsteady aerodynamics of a flexible aircraft

Masrour

Sadati²,

Shahravi³

2023

AEAT

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Purpose This study aims to simulate gust effects on the aeroelastic behavior of a flexible aircraft. The dynamic response of the system for different discreet gust excitations is obtained using numerical simulations. Design/methodology/approach Coupled dynamics, including rigid and flexible body coordinates, are considered for modeling the dynamic behavior of the aircraft. Wing is considered flexible and other parts are considered rigid. Wing is modeled with nonlinear Euler Bernoulli beam. Moreover, unsteady aerodynamics based on the Wagner function are used for aerodynamic loading, and the results are compared with those of quasi-steady aerodynamics. Findings Von Kármán continuous gust is applied to this aircraft. In addition, the discrete “1- cosine” gust with different gust lengths is applied to the aircraft, and the maximum and minimum accelerations are computed. It is shown that the nonlinear modeling of the system represents the actual behavior and causes limit cycle oscillation phenomena. Originality/value This methodology can yield a relatively simple dynamic model for high aspect ratio aircrafts to provide insights into the vehicles’ dynamics, which can be available early in the design cycle.

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Flight Dynamics Modeling of a Body Freedom Flutter Vehicle for Multidisciplinary Analyses

Cited by 4 publications

References 8 publications

Flight dynamic coupling analysis of a bio-inspired elastic-wing aircraft

Flight dynamic coupling analysis of a bio-inspired elastic-wing aircraft

A Load-Based Feedback Approach for Distributed Aeroservoelastic Control

Gust response analysis based on a nonlinear structural model and the unsteady aerodynamics of a flexible aircraft

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