Adaptive neural tracking control for high angle of attack maneuver with average dwell time

2021 ◽  
Author(s):  
Dawei Wu ◽  
Yonghui Sun ◽  
Xiaohui Yan
Keyword(s):  
Tracking Control ◽  
Dwell Time ◽  
Angle Of Attack ◽  
Average Dwell Time ◽  
High Angle ◽  
High Angle Of Attack

High AOA short landing robust control for an aircraft

2018 ◽  
Vol 91 (1) ◽  
pp. 38-49
Author(s):  
Yang Tingting ◽  
Li Aijun ◽  
Muhammad Taimoor ◽  
Rooh ul Amin
Keyword(s):  
Robust Control ◽  
Angle Of Attack ◽  
Average Dwell Time ◽  
Vital Role ◽  
Asynchronous Switching ◽  
High Angle ◽  
Robust Controller ◽  
High Angle Of Attack ◽  
Content Type ◽  
Polytopic Systems

Purpose The purpose of this paper is to propose a high angle of attack short landing model for switched polytopic systems as well as to derive an equation for fluidic thrust vector deflection angle based on pressure to reduce the velocity during the landing phase of flight. Design/methodology/approach In this paper, robust control algorithm is proposed for a non-linear high angle of attack aircraft under the effects of non-linearities, tottering hysteresis, irregular and wing rock atmosphere. High angle of attack short landing flight under asynchronous switching is attained by using the robust controller method. Lyapunov function and the average dwell time scheme is used for obtaining the switched polytopic scheme. The asynchronous switching and loss of data are controlled asymptotically. The velocity of aircraft has been lucratively reduced during the landing phase of flight by using the robust controller technique. Findings The proposed algorithm based on robust controller including the effects of non-linearities guarantee the successful reduction of velocity for high angle of attack switched polytopic systems. Practical implications As the landing phase of an aircraft is one of the complicated stage, this algorithm plays a vital role in stable and short landing under the condition of high angle of attack (AOA). Originality/value In this paper, not only the velocity of flight has been reduced, but also the high angle of attack has been attained during the landing phase, because of which the duration of landing has been reduced as well, while in most of the previous research, it is based on low angle of attack and long landing duration.

scholarly journals Leading Edge Blowing to Mimic and Enhance the Serration Effects for Aerofoil

2021 ◽  
Vol 11 (6) ◽  
pp. 2593
Author(s):  
Yasir Al-Okbi ◽  
Tze Pei Chong ◽  
Oksana Stalnov
Keyword(s):  
Boundary Layer ◽  
Angle Of Attack ◽  
Leading Edge ◽  
Boundary Layer Separation ◽  
Shear Instability ◽  
Vortical Flow ◽  
High Angle ◽  
High Angle Of Attack ◽  
Layer Separation ◽  
Aerodynamic Performances

Leading edge serration is now a well-established and effective passive control device for the reduction of turbulence–leading edge interaction noise, and for the suppression of boundary layer separation at high angle of attack. It is envisaged that leading edge blowing could produce the same mechanisms as those produced by a serrated leading edge to enhance the aeroacoustics and aerodynamic performances of aerofoil. Aeroacoustically, injection of mass airflow from the leading edge (against the incoming turbulent flow) can be an effective mechanism to decrease the turbulence intensity, and/or alter the stagnation point. According to classical theory on the aerofoil leading edge noise, there is a potential for the leading edge blowing to reduce the level of turbulence–leading edge interaction noise radiation. Aerodynamically, after the mixing between the injected air and the incoming flow, a shear instability is likely to be triggered owing to the different flow directions. The resulting vortical flow will then propagate along the main flow direction across the aerofoil surface. These vortical flows generated indirectly owing to the leading edge blowing could also be effective to mitigate boundary layer separation at high angle of attack. The objectives of this paper are to validate these hypotheses, and combine the serration and blowing together on the leading edge to harvest further improvement on the aeroacoustics and aerodynamic performances. Results presented in this paper strongly indicate that leading edge blowing, which is an active flow control method, can indeed mimic and even enhance the bio-inspired leading edge serration effectively.

High Angle of Attack Parameter Estimation of Cascaded Fins Using Neural Network

2013 ◽  
Vol 50 (1) ◽  
pp. 272-291 ◽  
Author(s):  
Manoranjan Sinha ◽  
Rajesh Ayilliath Kuttieri ◽  
Ajoy Kanti Ghosh ◽  
Ajay Misra
Keyword(s):  
Neural Network ◽  
Parameter Estimation ◽  
Angle Of Attack ◽  
High Angle ◽  
High Angle Of Attack
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