Control Surface Faults Neural Adaptive Compensation Control for Tailless Flying Wing Aircraft with Uncertainties

Zhang, Shaojie; Shuang, Weifang; Meng, Qingkai

doi:10.1007/s12555-017-0454-y

Cited by 17 publications

(6 citation statements)

References 32 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“… is the new pseudocontrol input based on the PPB transformation. Therefore, the standard NDI controller, based on Equations (6), (20), (29) and (30), is given as…”

Section: Outer Loop Controlmentioning

confidence: 99%

See 1 more Smart Citation

Finite Time Convergence Incremental Nonlinear Dynamic Inversion-Based Attitude Control for Flying—Wing Aircraft with Actuator Faults

2020

Self Cite

View full text Add to dashboard Cite

In this paper, a two-loop fault-tolerant attitude control scheme is proposed for flying-wing aircraft with actuator faults. A regular nonlinear dynamic inversion (NDI) control is used in the outer attitude loop, and a finite time convergence incremental nonlinear dynamic inversion (FINDI) control combined with control allocation strategy is used in the inner angular rate loop. Prescribed performance bound (PPB) is designed to constrain the tracking errors within a residual set, so the prescribed system performance can be guaranteed. An optimal anti-windup (AW) compensator is introduced to solve the actuator saturation problem. Simulation results demonstrate the effectiveness of the proposed approach.

show abstract

“… is the new pseudocontrol input based on the PPB transformation. Therefore, the standard NDI controller, based on Equations (6), (20), (29) and (30), is given as…”

Section: Outer Loop Controlmentioning

confidence: 99%

“…If the PPB system is stable, the tracking errors will be within the prescribed error bounds all the way through. In [29], a command filtered adaptive backstepping compensation approach based on PPB is proposed for the flying-wing aircraft system with actuator stuck or loss of effectiveness and achieves some good results.…”

Section: Introductionmentioning

confidence: 99%

Finite Time Convergence Incremental Nonlinear Dynamic Inversion-Based Attitude Control for Flying—Wing Aircraft with Actuator Faults

2020

Self Cite

View full text Add to dashboard Cite

show abstract

“…A neural network with lyapunov-based adaptation law is used to robust control of an airplane [23]. The tracking control scheme with a radial base function neural network compensator for a commercial aircraft has been proposed [24]. In the mentioned paper, the saturation of the actuators and the uncertainty of the aerodynamic parameters are considered.…”

Section: Introductionmentioning

confidence: 99%

A New Type-2 Fuzzy Sliding Mode Control for Longitudinal Aerodynamic Parameters of a Commercial Aircraft

Tavoosi¹

2020

JESA

View full text Add to dashboard Cite

Although sliding mode control has many advantages such as stability and robustness but there are two important disadvantages as follow: Chattering phenomenon and mathematical nonlinear dynamic equivalent controller part. So, this paper presents a new method of adaptive sliding mode control based on general type-2 fuzzy logic to overcome on the mentioned problems. First, the longitudinal motion equations of a commercial aircraft and the upper limits of the unknown functions are introduced, which include the driving errors and uncertain parameters of the model. Then, a general type-2 fuzzy neural network (GT2FNNs), with adaptive rules, estimates these limits. Estimating the limits can reduce the computational load with less rules and weight than the dynamic matrix. The Boeing 747 is being studied and an attempt has been made to use a model very close to this aircraft. The stability of the control system has been proven. The simulation results show that by applying three models of faults to the aircraft system, the proposed type-2 fuzzy-based sliding mode control has excellent performance, especially in controlling the Aileron and Rudder angles.

show abstract

“…Medford (2012) has investigated the aerodynamics of a maneuvering unmanned aircraft vehicle (UAV) model and its control through leading-edge curvature change. Scientists have examined flight dynamics and control modeling of damaged asymmetric aircraft (Ogunwa and Abdullah 2016;Bacon and Gregory 2018;Nguyen et al 2006;Zhang et al 2018;Asadi et al 2014).…”

Section: Introductionmentioning

confidence: 99%

Vortex Dynamics Analysis of Straight-Body-Type-Fuselage Fighter Using CFD Simulation

Sutrisno

Deendarlianto

Rohmat

et al. 2020

J.Aerosp. Technol. Manag.

View full text Add to dashboard Cite

The choice for using a fighter fuselage in a fighter jet design affects a vortex generation advantageous in maneuverability. To study the effect of straight-body-type-fuselage (SBTF) on the vortex dynamic, a computational fluid dynamics (CFD) method is used, in order to simulate a model of SBTF fighter. The simulation uses Q-criterion to probe vortices, and a logarithmic grid to emphasize the micro-gridding effect of the turbulent boundary layer. The results show detailed quantitative velocity, pressure, trajectory of the vortex core, and wing negative surface pressure distribution (SPD), providing clear pictures of opportunity for performance improvement, better lift, agility, and maneuverability of a fighter if a model requires a new design.

show abstract

Control Surface Faults Neural Adaptive Compensation Control for Tailless Flying Wing Aircraft with Uncertainties

Cited by 17 publications

References 32 publications

Finite Time Convergence Incremental Nonlinear Dynamic Inversion-Based Attitude Control for Flying—Wing Aircraft with Actuator Faults

Finite Time Convergence Incremental Nonlinear Dynamic Inversion-Based Attitude Control for Flying—Wing Aircraft with Actuator Faults

A New Type-2 Fuzzy Sliding Mode Control for Longitudinal Aerodynamic Parameters of a Commercial Aircraft

Vortex Dynamics Analysis of Straight-Body-Type-Fuselage Fighter Using CFD Simulation

Contact Info

Product

Resources

About