Analysis of partial wing damage on flying-wing unmanned air vehicle

Kim, Ki-joon; Ahn, Jongmin; Kim, Taegyun; Choi, Jong‐Soo; Suk, Jinyoung; Lim, Heungsik; Hur, Gi-Bong

doi:10.1177/0954410012472292

Cited by 8 publications

(6 citation statements)

References 13 publications

(17 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…After the 21st century, UAVs began to develop vigorously, and the flying wing layout has become the focus of research because of its outstanding tactical advantages. At present, in addition to the x-45 and x-47b of the United States, there are Russian rays, French led Neurons, British Thor, Chinese sword and so on [1][2][3].…”

Section: Original Research Articlementioning

confidence: 99%

Flutter Modelling and Computation of a Flying Wing Aircraft

Bai

Zhang

2022

JERR

View full text Add to dashboard Cite

Flying wing aircraft has many encouraging advantages, but there still were many unsteady aerodynamic uncertainty of the structures. Dynamic stability is a most significant analysis object. This paper wants to propose the flutter characteristic of a real flying wing aircraft. Firstly, an efficient finite element modelling method was taken to find basic dynamic features of the presented aircraft with effective mode analysis. Typical dynamic characteristics including bending and twisting modes of the structure were analyzed to propose possible dynamic stability of the aircraft. Secondly, a frequency domain fluid-structure interaction method was proposed to solve flutter analysis problem of the aircraft. With different heights and Ma number, flutter features of the aircraft were presented. It was seen from the computational results that dynamic stability analysis is necessary for the flying wing aircraft with proper flight velocity and height. The present dynamic modelling method and flutter computation process can give an effect reference for the design of flying wing aircraft. Also it can provide useful suggestions for existing flying wing aircraft structures.

show abstract

Section: Original Research Articlementioning

confidence: 99%

Flutter Modelling and Computation of a Flying Wing Aircraft

Bai

Zhang

2022

JERR

View full text Add to dashboard Cite

show abstract

“…13 and Kim et al. 14 General force and moment equations are derived from the assumption that an airplane is symmetric. However, in the case of an aircraft with partial wing-loss, this assumption is not valid.…”

Section: Numerical Modelingmentioning

confidence: 99%

“…It is also required to check the dominant coupling effects in C l and to examine the seriousness of the effect of this change in the longitudinal static stability related to C m on the normal flight dynamic characteristics, through investigation of the changes in the poles of each flight mode. For more detailed aerodynamic data, please refer to Ahn et al 13 and Kim et al 14 General force and moment equations are derived from the assumption that an airplane is symmetric. However, in the case of an aircraft with partial wing-loss, this assumption is not valid.…”

Section: Change Of Aerodynamic Coefficients In Force and Moment Equatmentioning

confidence: 99%

Flight test of flying-wing type unmanned aerial vehicle with partial wing-loss

Kim

Suk

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

Self Cite

View full text Add to dashboard Cite

This paper investigates experimental evaluation via flight tests for applying adaptive neural network controller to a flying-wing type unmanned aerial vehicle experiencing partial wing-loss. For this, six-degree-of-freedom numerical model is constructed taking into account damage-induced changes to the unmanned aerial vehicle in aerodynamic coefficients, mass, center of gravity, and moments of inertia. Numerical simulations are performed to investigate the flight dynamics change and to verify the performance of the neural network based controller. During the flight test, main wing-loss is artificially generated by 22% or 33% area moment. The flight test verifies that the damaged unmanned aerial vehicle shows drastic roll behavior with the unstable longitudinal response, and the neural network based adaptive controller combined with feedback linearization successfully compensates for the wing damage.

show abstract

“…A blended-wing body type UAV is considered for this study, and partial loss of right wing and vertical tail is considered as the aircraft's damage [5]: in detail, 22% loss of area moment of the right main wing and 25% loss of effectiveness of the vertical tail. Fig.…”

Section: Uav Numerical Modelmentioning

confidence: 99%

Adaptive Neural Network Controller Design for a Blended-Wing UAV with Complex Damage

Kim¹,

Ahn²,

Kim³

et al. 2018

JKSAS

Self Cite

View full text Add to dashboard Cite

This paper presents neural network controller design for complex damage to a blended wing UAV (Unmanned Aerial Vehicle): partial loss of main wing and vertical tail. Longitudinal/lateral axis instability and the change of flight dynamics is investigated via numerical simulation. Based on this, neural network based adaptive controller combined with feedback linearization is designed in order to compensate for the complex damage. Numerical simulation verifies that the instability from the complex damage of the UAV can be stabilized via the proposed adaptive controller.

show abstract

Analysis of partial wing damage on flying-wing unmanned air vehicle

Cited by 8 publications

References 13 publications

Flutter Modelling and Computation of a Flying Wing Aircraft

Flutter Modelling and Computation of a Flying Wing Aircraft

Flight test of flying-wing type unmanned aerial vehicle with partial wing-loss

Adaptive Neural Network Controller Design for a Blended-Wing UAV with Complex Damage

Contact Info

Product

Resources

About