Effect of geometry and mass distribution on tumbling characteristics of flying wings

Fremaux, C. Michael; Vairo, D. M.; Whipple, R. D.

doi:10.2514/3.46730

Cited by 9 publications

(3 citation statements)

References 3 publications

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“…Their development histories are introduced, respectively, below. [26][27][28][29][30][31][32][33][34][35][36][37][38][39], free spin [40], free tumble [41], and free fall [7]. A VFT architecture proposed by Standard Missile Company [85].…”

Section: Progress Of Vftmentioning

confidence: 99%

A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems

Huang

Wang

2015

International Journal of Aerospace Engineering

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Wind tunnel based Virtual Flight Testing (VFT) is a dynamic wind tunnel test for evaluating flight control systems (FCS) proposed in recent decades. It integrates aerodynamics, flight dynamics, and FCS as a whole and is a more realistic and reliable method for FCS evaluation than traditional ground evaluation methods, such as Hardware-in-the-Loop Simulation (HILS). With FCS evaluated by VFT before flight test, the risk of flight test will be further reduced. In this paper, the background, progress, and prospects of VFT are systematically summarized. Specifically, the differences among VFT, traditional dynamic wind tunnel methods, and traditional FCS evaluation methods are introduced in order to address the advantages of evaluating FCS with VFT. Secondly, the progress of VFT is reviewed in detail. Then, the test system and key technologies of VFT for FCS evaluation are analyzed. Lastly, the prospects of VFT for evaluating FCS are described.

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Section: Progress Of Vftmentioning

confidence: 99%

A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems

Huang

Wang

2015

International Journal of Aerospace Engineering

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“…The experimental investigations showed that the tumbling modes are very sensitive to geometric and inertial characteristics of the aircraft [2]. The initial conditions also essentially in §uence the tumbling motion.…”

Section: Nomenclaturementioning

confidence: 99%

Calculation of tumbling boundaries of a generic wing-only airliner

Храбров

Sidoryuk

2015

Progress in Flight Physics – Volume 7

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The aerodynamic model of a generic wing-only airliner con¦guration is developed for a whole range of angles of attack (−180 • . . . +180 • ), based on experimental data obtained in wind tunnels using static, and forced oscillations. Two di¨erent approaches for the tumbling boundaries calculation are used. In the ¦rst approach, the steady pitch autorotation is calculated. In the second approach, for various angles of attack, the minimum pitch rate disturbance is considered which can result in tumbling. The tumbling boundaries are calculated via the use of a continuation technique. The dependence of these boundaries on such parameters as §ight altitude, aircraft center of gravity position, and total velocity is analyzed.

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“…A problem similar in many aspects to that of sheet debris flight is the flutter, tumble and vortex induced autorotation of falling wings or plates. This could be considered a limit state of debris flight when the wind velocity is very small and was studied among others by Fremaux et al (1995), Mittal and Seshadri (2004) and Gallaway and Hankey (1985), who found in numerical simulations that free falling autorotating plates experienced considerably larger autorotation coefficients than those obtained at static angles of attack.…”

Section: Introductionmentioning

confidence: 98%

Analysis of the two dimensional sheet debris flight equations: initial and final state

Scarabino¹,

Giacopinelli²

2010

Wind and Structures An International Journal

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This work presents some analytical and numerical results of a dynamic analysis of the dimensionless 2-D sheet flight equations. Two empirical models for aerodynamic forces and moments are used and compared. Results show that the initial condition of rest is always unstable, and for long times three distinct flight regimes are possible, depending on the initial angle of attack, the Tachikawa number, Ta (in fact, the parameter chosen was its inverse, Ω), and a mass ratio Φ. The final orbits in the velocity space and their maximum kinetic energy are compared with a theoretical asymptotic state of the motion equations, and some design considerations are proposed.

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Effect of geometry and mass distribution on tumbling characteristics of flying wings

Cited by 9 publications

References 3 publications

A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems

A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems

Calculation of tumbling boundaries of a generic wing-only airliner

Analysis of the two dimensional sheet debris flight equations: initial and final state

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