Wind tunnel test of an unmanned aerial vehicle (UAV)

Jindeog, Chung; Lee, Jang-Yeon; Sung, Bongzoo; Koo, Sam-Ok

doi:10.1007/bf02983873

Cited by 7 publications

(2 citation statements)

References 2 publications

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“…To determine the validity of the values calculated, comparable data was investigated for various similar sized UAV aircraft. The aircraft investigated were a 1/3 scale YAK-54 12 , SIG Rascal 110 R/C aircraft 13 , and a UAV Developed by the Korean Aerospace Research Institute (KARI) 14 . Not all of these publications encompassed the complete set of stability derivatives, but as a whole provided sufficient information to justify the results presented herein.…”

Section: Stability and Control Derivatives And Validationmentioning

confidence: 99%

Hawkeye UAV Dynamic Analysis

Vanskike

Williams

Stastny

et al. 2011

AIAA Modeling and Simulation Technologies Conference

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A dynamic analysis of the Hawkeye unmanned aerial vehicle (UAV) produced by University of Kansas students has been completed and results are presented herein. Geometric data was collected through measurements of the aircraft and its control surfaces, from which a computerized model was developed. Stability and control derivatives and steady state trimmed flight conditions were calculated with the Advanced Aircraft Analysis (AAA) software package. These results were then verified by comparison with similar aircraft platforms and simulated using a 6 degree of freedom nonlinear MATLAB/Simulink interface. The resulting system demonstrated stable phugoid, short period, roll, and dutch roll modes with an unstable spiral mode. Subsequent research should focus on further verification of the current stability derivatives and investigation of dynamic stability by computation of multiple trim conditions within a flight envelope ranging between a stall speed of 28 knots and a dash speed of 80 knots. The results presented have potential application for use in the design of control systems capable of autonomously controlling this UAV as well as similar sized vehicles.

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Section: Stability and Control Derivatives And Validationmentioning

confidence: 99%

Hawkeye UAV Dynamic Analysis

Vanskike

Williams

Stastny

et al. 2011

AIAA Modeling and Simulation Technologies Conference

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“…The analysis outcomes were characterized and compared in terms of the main lift (CL) and drag (CD) characteristics of the Mark 1 and Mark 2 Neo-Ptero models. Improving these distributions over the Neo-Ptero model may further improve its power usage for the micro-UAV and prolong its flight endurance [1,6,7].…”

Section: Introductionmentioning

confidence: 99%

Investigations of Lift and Drag Performances on Neo-Ptero Micro UAV Models

Ismail

Basri

Sharudin

et al. 2021

ARFMTS

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This paper presents the investigation and improvement of lift and drag characteristics of Neo-Ptero micro-UAV models based on the virtual wind tunnel method. Despite its successful development and flight stability, the lift and drag coefficients characteristics of the current Mark 1 Neo-Ptero remain unknown. To improve the Mark 1 Neo-Ptero performances, Mark 2 Neo-Ptero model has given a new unsymmetrical airfoil wing configuration. The computational aerodynamic analysis was executed and focused on certain lift and drag coefficient characteristics. Lift coefficient results showed that Mark 2 improved in overall lift characteristics such as zero-lift angle, maximum lift magnitude and stall angle magnitude. Conversely, Mark 2 model suffered a slightly higher drag coefficient magnitude and more significant drag increment percentage than Mark 1. However, the trade-off between superior lift magnitude and minor drag generation induced by Mark 2 boosts the model’s aerodynamic efficiency performances but is only limited at early angle stages.

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