Investigations on stability and control characteristics of a CS-VLA certified aircraft using wind tunnel test data

Nguyen, Nhu Van; Tyan, Maxim; Lee, Jae Woo; Kim, Sangho

doi:10.1177/0954410016632016

Cited by 6 publications

(4 citation statements)

References 15 publications

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“…The performances being compared are the lift and drag characteristics, stall conditions, efficiency, stability, and maneuverability. To ensure that the performances are comprehended in various flight conditions, the angle of attack and sideslip angle need to be considered since they influence stability [23]. The angle of attack, α, is the angle between the longitudinal axis x and the projection of the vector speed → V on the plane of symmetry x, z.…”

Section: Methodsmentioning

confidence: 99%

Aerodynamic Performance Analysis of VTOL Arm Configurations of a VTOL Plane UAV Using a Computational Fluid Dynamics Simulation

Nugroho

Hutagaol

Zuliardiansyah

2022

Drones

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A vertical take-off and landing plane (VTOL plane) is a fixed-wing unmanned aerial vehicle (FWUAV) configuration with the ability to take off and land vertically. It combines the benefits of fixed-wing and multirotor configurations, which gives it a high cruising range and independence from a runway. This configuration requires arms as mountings for the VTOL’s motors. This study discusses the design of a VTOL Plane with various VTOL arm configurations, and a computational fluid dynamics (CFD) simulation was conducted to find out which configuration performs the best aerodynamically. The VTOL arm configurations analyzed were a quad-plane, a twin-tail boom, a tandem wing, and a transverse arm. The interpreted performances were the lift and drag performances, stall conditions, flight efficiency, stability, and maneuverability. The relative wind directions toward the longitudinal axis of the UAV, which are the sideslip angle and the angle of attack, were varied to simulate various flying conditions. The results showed that the twin tail-boom is the most advantageous based on the interpreted performances.

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Section: Methodsmentioning

confidence: 99%

Aerodynamic Performance Analysis of VTOL Arm Configurations of a VTOL Plane UAV Using a Computational Fluid Dynamics Simulation

Nugroho

Hutagaol

Zuliardiansyah

2022

Drones

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“…In this paper, the KLA-100 light aircraft model is generated and simulated in the JSBSim Flight Dynamics Model (FDM). The KLA-100 is a two-seater light aircraft with low-wing configuration developed by the Light Aircraft Development Center of Konkuk University, Korea (6,30,31) . The simulation model database consists of four modules: configuration DB, propulsion DB, mass and balance DB and aerodynamic DB.…”

Section: Aircraft Model Specificationsmentioning

confidence: 99%

“…The basic aerodynamic coefficients are classified into static and dynamic terms; the static components are obtained from CFD analysis or W/T static stability experiment data (31,32) ; (30) .…”

Section: Aerodynamic Database Constructionmentioning

confidence: 99%

Enhancement of light aircraft 6 DOF simulation using flight test data in longitudinal motion

et al. 2021

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This paper proposes a procedure to improve the accuracy of the light aircraft 6 DOF simulation model by implementing model tuning and aerodynamic database correction using flight test data. In this study, the full-scale flight testing of a 2-seater aircraft has been performed in specific longitudinal manoeuver for model enhancement and simulation validation purposes. The baseline simulation model database is constructed using multi-fidelity analysis methods such as wind tunnel (W/T) test, computational fluid dynamic (CFD) and empirical calculation. The enhancement process starts with identifying longitudinal equations of motion for sensitivity analysis, where the effect of crucial parameters is analysed and then adjusted using the model tuning technique. Next, the classical Maximum Likelihood (ML) estimation method is applied to calculate aerodynamic derivatives from flight test data, these parameters are utilised to correct the initial aerodynamic table. A simulation validation process is introduced to evaluate the accuracy of the enhanced 6 DOF simulation model. The presented results demonstrate that the applied enhancement procedure has improved the simulation accuracy in longitudinal motion. The discrepancy between the simulation and flight test response showed significant improvement, which satisfies the regulation tolerance.

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“…The control and stability maintenance of aircraft using wind tunnel test data is discussed (Nguyen et al, 2016). The stability and control analysis of unmanned aircraft is done using system identification techniques (Rohlf et al, 2012).…”

Section: Introductionmentioning

confidence: 99%

Stabilisation of network-controlled aircraft pitch control system with time delay

Subramanian

Kokil

2022

Transactions of the Institute of Measurement and Control

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This paper describes the stability assurance of network-controlled aircraft pitch control system with time delays. A frequency-domain method is used to determine the upper bound of time delay for aircraft pitch control system with gain and phase margin constraint. The effectiveness of proportional-integral (PI) and fractional-order PI controller on aircraft pitch control system stability and performance is investigated in presence of time delay. The parametric space of the PI and fractional-order PI controller are plotted in two-dimensional space to determine the stability region and controller is designed with concern to the time delay. The relation between controller parameters and time delay is estimated and these findings contribute significantly for the design of the controller for aircraft pitch control system. The accuracy of the proposed results is validated using simulation benchmark.

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Investigations on stability and control characteristics of a CS-VLA certified aircraft using wind tunnel test data

Cited by 6 publications

References 15 publications

Aerodynamic Performance Analysis of VTOL Arm Configurations of a VTOL Plane UAV Using a Computational Fluid Dynamics Simulation

Aerodynamic Performance Analysis of VTOL Arm Configurations of a VTOL Plane UAV Using a Computational Fluid Dynamics Simulation

Enhancement of light aircraft 6 DOF simulation using flight test data in longitudinal motion

Stabilisation of network-controlled aircraft pitch control system with time delay

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