Numerical Analyses of Discrete Gust Response for an Aircraft

Yang, Guowei; Obayashi, Shigeru

doi:10.2514/1.2531

Cited by 25 publications

(10 citation statements)

References 11 publications

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“…4. Moreover, the aspect ratio was λ = 11, the spanwise length was b = 52.12 m and the distance from the reference point of pitching moment to the head was 8.23 m. The gust for calculation is discrete 1-cos gust (Yang and Obayashi 2004), and the gust model is (Eq. 3):…”

Section: Resultsmentioning

confidence: 99%

“…The early study of aircraft gust response was mainly performed in the frequency domain by using the linear plate aerodynamic force and combining with aeroelastic equation (Wu et al 2010). With the development of computational fluid dynamics, the gust response of aircraft was calculated by solving the unsteady Euler and Navier-Stokes equations in the time domain (Singh and Baeder 1997;Zhan and Qian 2007;Gu et al 2013;Yang and Obayashi 2004). Later, the reduced-order model method based on CFD emerged and the gust response of aircraft was calculated by employing the reducedorder model (Zaide and Raveh 2006;Gennaretti and Mastroddi 2004;Zhang et al 2009).…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Longitudinal Aerodynamic and Stability Characteristics of High-Aspect-Ratio Unmanned Aerial Vehicles in Gust Response

Wang

Zhang

Feng

et al. 2019

J.Aerosp. Technol. Manag.

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The aim of this work is to propose an accurate and reliable numerical simulation method of gust response, so as to analyze longitudinal stability characteristics of high-aspect-ratio unmanned aerial vehicles (UAVs) under gust response. Based on the dual-time stepping method, the unsteady Navies-Stokes equation was solved. By introducing grid velocity to study the effects of gust, the numerical simulation of gust response was realized. Moreover, the numerical simulation method was verified to be accurate by using the theoretical value and reference value obtained in previous research. The calculation results of the high-aspect-ratio UAV under the 1-cos gust reveal that longitudinal aerodynamic forces of high-aspect-ratio UAVs changed. In the whole range of gust gradient length, the UAVs were always in the state of static stability. However, with the increase of gust velocity, static stability margin decreased. The numerical simulation method of gusts established in this study preferably overcomes the possible numerical oscillations and divergence problems caused by excessive gust velocity. The analysis on longitudinal static stability and stability margin of high-aspect-ratio UAVs under the effects of gusts can ensure flight quality and safety of UAVs under the effects of gusts.

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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Longitudinal Aerodynamic and Stability Characteristics of High-Aspect-Ratio Unmanned Aerial Vehicles in Gust Response

Wang

Zhang

Feng

et al. 2019

J.Aerosp. Technol. Manag.

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show abstract

“…The static aeroelastic solver was developed based on our dynamic aeroelastic solver [19,20], in which the structural modes were employed and the characteristics of aileron buzz and gust responses were analyzed; the static aeroelastic solver still needs to be validated, due to the use of stiffness matrix in the structure.…”

Section: A Static Aeroelastic Analysesmentioning

confidence: 99%

Response Surface Technique for Static Aeroelastic Optimization on a High-Aspect-Ratio Wing

Yang

Chen

Cui

2009

Journal of Aircraft

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“…Gust velocity inputs were introduced into the EZNSS [8] (Elastic Zonal Navier-Stokes Simulation) CFD code using the fieldvelocity method, proposed by Parameswaran and Baeder [9] and practiced by Singh and Baeder [10,11]. Yang and Obayashi [12] presented CFD gust simulation of a complete aircraft configuration to one-minus-cosine gust profile, using two rigid-body degrees of freedom of pitch and plunge, with and without elastic effects.…”

mentioning

confidence: 99%

Gust-Response Analysis of Free Elastic Aircraft in the Transonic Flight Regime

Raveh

2011

Journal of Aircraft

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The study presents a methodology for introducing computational fluid dynamics to gust-response analysis in a computationally efficient manner. Two approaches for computational-fluid-dynamics-based gust-response analysis of free elastic aircraft are presented. The direct approach involves full aeroelastic simulation within the computational fluid dynamics run. The hybrid approach involves computing rigid sharp-edge gust responses in a computational fluid dynamics run, computing the gust input forces due to arbitrary gust profiles via convolution, and applying a linear aeroelastic feedback loop to compute the aeroelastic gust responses. The latter is highly computationally efficient, as only one relatively short computational fluid dynamics run is required for the computation of the sharp-edge gust response, after which responses to arbitrary gust profiles can be computed in seconds. The former is more elaborate and time-consuming and can be used in cases of critical responses. The use of the two methods is demonstrated on a transport aircraft, flying trimmed at Mach 0.85, 10,000 ft, that passes through one-minus-cosine shaped gusts, as required by the Federal Aviation Regulations.

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Numerical Analyses of Discrete Gust Response for an Aircraft

Cited by 25 publications

References 11 publications

Longitudinal Aerodynamic and Stability Characteristics of High-Aspect-Ratio Unmanned Aerial Vehicles in Gust Response

Longitudinal Aerodynamic and Stability Characteristics of High-Aspect-Ratio Unmanned Aerial Vehicles in Gust Response

Response Surface Technique for Static Aeroelastic Optimization on a High-Aspect-Ratio Wing

Gust-Response Analysis of Free Elastic Aircraft in the Transonic Flight Regime

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