A study of instability in a miniature flying-wing aircraft in high-speed taxi

Song, Lei; Yang, Hua; Yan, Xufeng; Ma, Cong; Huang, Jun

doi:10.1016/j.cja.2015.04.001

Cited by 19 publications

(6 citation statements)

References 13 publications

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“…The lateral-directional motion modes generally contain the roll mode, Dutch roll mode, and spiral mode. It is reasonable to give up estimating the lateral-directional static stability derivative and set the dynamic stability as the criterion to guarantee the flying quality in aircraft conceptual design (Song et al 2015).…”

Section: Calculation Of Parameters For Stability Assessmentmentioning

confidence: 99%

Effect of Aerodynamic Configuration Parameters on Lateral-Directional Stability of Double-Swept Flying Wing Aircraft

Pan

Huang

2019

J.Aerosp. Technol. Manag.

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Poor lateral-directional stability due to the absence of vertical stabilizer is a great risk to the aircraft with flying wing layout. In this paper, an unmanned aerial vehicle with this kind of configuration is chosen as the research object. A threedimensional model of the unmanned aerial vehicle is established, and then the sensitivity analysis is performed to obtain the effects of main aerodynamic shape parameters on lateral-directional flying quality. The results show that the roll mode and spiral mode of the aircraft meet the requirements of Level 1 flying quality in MIL-F-8785C. But the Dutch roll mode is generally divergent, which means that the flying quality of the aircraft is unacceptable. Thus it can be seen that the Dutch roll mode is the key to the dynamic stability of the aircraft. Further studies show that increasing the value of wing aspect ratio or decreasing the values of dihedral angle and torsion angle are useful for improving the Dutch roll mode. It is valuable to reveal the influence mechanism of aerodynamic shape parameters on lateral-directional flying quality for the design of flying wing aircraft.

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Section: Calculation Of Parameters For Stability Assessmentmentioning

confidence: 99%

Effect of Aerodynamic Configuration Parameters on Lateral-Directional Stability of Double-Swept Flying Wing Aircraft

Pan

Huang

2019

J.Aerosp. Technol. Manag.

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“…Whether lateral-directional of aircraft has sufficient stability is up to flying qualities of three modes (Song et al, 2015). Flying quality of roll mode is usually assessed with time constant (T r ).…”

Section: Calculation Of Flying Quality Assessment Parametersmentioning

confidence: 99%

Influences of airfoil profile on lateral-directional stability of aircraft with flying wing layout

Pan

Huang

2019

AEAT

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Purpose The purpose of this study is to analyze influence of airfoil profile on lateral-directional flying quality of flying wing aircraft. The lateral-directional stability is always insufficient for aircraft with the layout due to the absence of vertical stabilizer. A flying wing aircraft with double-swept wing is used as research object in the paper. Design/methodology/approach The 3D model is established for the aircraft with flying wing layout, and parametric modeling is carried out for airfoil mean camber line of the aircraft to analyze lateral-directional stability of the aircraft with different camber line parameters. To increase computational efficiency, vortex lattice method is adopted to calculate aerodynamic coefficients and aerodynamic derivatives of the aircraft. Findings It is found from the research results that roll mode and spiral mode have a little effect on lateral-directional stability of the aircraft but Dutch roll mode is the critical factor affecting flying quality level of such aircraft. Even though changes of airfoil mean line parameters can greatly change assessment parameters of aircraft lateral-directional flying quality, that is kind of change cannot have a fundamental impact on level of flying quality of the aircraft. In case flat shape parameters are determined, the airfoil profile has a limited impact on Dutch roll mode. Originality/value Influences of airfoil profile on lateral-directional flying quality of aircraft with double-swept flying wing layout are revealed in the thesis and some important rules and characteristics are also summarized to lay a theoretical basis for design of airfoil and flight control system of aircraft with the layout.

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“…The model is then linearized using small perturbation theory and further work has been done on the design of its controller. Another model for taxiing has been developed in [6]. The forces and moments used in this model are the lateral friction of the wheels and support forces from ground to the nose gear.…”

Section: 𝐹 𝑓 = 𝜇 𝑓 𝑁mentioning

confidence: 99%

Taxi model of unmanned aerial vehicle: Formulation and simulation

Wasim

Ullah

Iqbal

2018

2018 1st International Conference on Power, Energy and Smart Grid (ICPESG)

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Unmanned Aerial Vehicles cannot work efficiently without a control system. Before any form of control is applied to it, modeling of the system is necessary. This work focuses on the development of a Taxi model of UAV. The reformulated model has been developed and simulated in Simulink and Simscape. Three scenarios have been considered in Simulation: Normal conditions with no wind, head and tail wind of 15 m/s and steering angle of 1 radian. The key objective of this model is to include all the necessary dynamics of UAV when it is in taxi phase. This has been done by modifying the vehicle body model in Simscape to fit to the specifications of the UAV and moreover integrating it with an undercarriage model from previous literature to include the forces.

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A study of instability in a miniature flying-wing aircraft in high-speed taxi

Cited by 19 publications

References 13 publications

Effect of Aerodynamic Configuration Parameters on Lateral-Directional Stability of Double-Swept Flying Wing Aircraft

Effect of Aerodynamic Configuration Parameters on Lateral-Directional Stability of Double-Swept Flying Wing Aircraft

Influences of airfoil profile on lateral-directional stability of aircraft with flying wing layout

Taxi model of unmanned aerial vehicle: Formulation and simulation

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