scholarly journals The choice of sliding surface for robust roll control: Better suppression of high angle of attack/sideslip perturbations

2018 ◽  
Vol 10 (4) ◽  
pp. 330-339 ◽  
Author(s):  
S Seyedtabaii ◽  
M Delavari
Keyword(s):  
Sliding Mode ◽  
Angle Of Attack ◽  
Sliding Surface ◽  
High Angle ◽  
High Angle Of Attack ◽  
Control Effort ◽  
Roll Control ◽  
Dynamic Uncertainty ◽  
Aerodynamic Parameters ◽  
And Control

The nominal aerodynamic parameters of aircraft are often approximate and aircraft may experience high value of angle of attack/sideslip perturbations during their manoeuvres. Preventing instability and air crash requires a robust controller capable of containing the dynamic uncertainty and the perturbations. In this respect, the problems of roll control in such a situation are studied and a better choice of sliding surface is proposed. Sliding mode control manages the uncertainty and adaptive fuzzy is employed to shape the transient response. As a result, a setup is formed which outperforms the basic controller both in terms of transient speed, response robustness and control effort. The strength of the method is more appreciated in case of high angle of attack/sideslip perturbed manoeuvres. This is proved theoretically and illustrated by simulations.

High-angle-of-attack stability and control improvements for the EA-6B Prowler

1987 ◽  
Author(s):  
FRANK JORDAN ◽  
DAVID HAHNE ◽  
MATTHEW MASIELLO ◽  
WILLIAM GATO
Keyword(s):  
Angle Of Attack ◽  
High Angle ◽  
High Angle Of Attack ◽  
Stability And Control ◽  
And Control

scholarly journals Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of Attack

2021 ◽  
Vol 11 (2) ◽  
pp. 505
Author(s):  
Wencheng Li ◽  
Wenyun Wang ◽  
Xiaomao Huang ◽  
Shun Zhang ◽  
Chenyang Li
Keyword(s):  
Input Saturation ◽  
Angle Of Attack ◽  
Synthetic Jet ◽  
Control Surface ◽  
Roll Motion ◽  
High Angle ◽  
High Angle Of Attack ◽  
Morphing Aircraft ◽  
Roll Control ◽  
Saturation Constraint

Flow separation and dynamic stall occurring at a high angle of attack will lead to difficulty in control and maneuverability for morphing aircraft. This study proposes a novel active flow control technology using a synthetic jet actuator for the roll motion of morphing aircraft. With the help of the computational fluid dynamics method and vortex lattice method, the roll control model of morphing aircraft undergoing large shape change at a high angle of attack is established. In this model, both the array of the actuator with an optimized cavity shape and morphing span, which are subject to the input saturation constraint, are used to mimic the conventional control surface. Integrated flight control based on the sliding mode control method is designed to ensure the desired closed-loop asymptotic stability, wherein the radial basis function neural network is employed to provide the compensation induced by the input saturation constraint. To demonstrate the effectiveness of the control scheme, various control strategies for different combinations of input are proposed to maintain the roll motion. The numerical results show that the designed control law could track the target signal well, which suggests that the virtual control surface is an effective tool for maintaining the high flight performance of morphing aircraft.

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