Yaw Control of a Tailless Aircraft Configuration

Stenfelt, Gloria; Ringertz, Ulf

doi:10.2514/1.c031017

Cited by 41 publications

(23 citation statements)

References 1 publication

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“…15 In contrast, this paper examines a method to increase the lateral dynamic stability on pure tailless aircraft through use of dihedral layout optimization. Considering a global and multidisciplinary audience, the planform and airfoil of each spanwise section of the tailless aircraft are designed to meet applicable aerodynamic and low observability requirements.…”

Section: Introductionmentioning

confidence: 94%

Dihedral influence on lateral–directional dynamic stability on large aspect ratio tailless flying wing aircraft

Song

Yang

Zhang

et al. 2014

Chinese Journal of Aeronautics

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The influence of dihedral layout on lateral-directional dynamic stability of the tailless flying wing aircraft is discussed in this paper. A tailless flying wing aircraft with a large aspect ratio is selected as the object of study, and the dihedral angle along the spanwise sections is divided into three segments. The influence of dihedral layouts is studied. Based on the stability derivatives calculated by the vortex lattice method code, the linearized small-disturbance equations of the lateral modes are used to determine the mode dynamic characteristics. By comparing 7056 configurations with different dihedral angle layouts, two groups of stability optimized dihedral layout concepts are created. Flight quality close to Level 2 requirements is achieved in these optimized concepts without any electric stability augmentation system.

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Section: Introductionmentioning

confidence: 94%

Dihedral influence on lateral–directional dynamic stability on large aspect ratio tailless flying wing aircraft

Song

Yang

Zhang

et al. 2014

Chinese Journal of Aeronautics

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“…In this way, FCS performances of unsteady maneuvers can be effectively evaluated by WT-HILS. Some departments had developed rigs to evaluate the control algorithms of free spin [9][10], free wing rock [11], free pitching-rolling coupling motions [14].…”

Section: B What Fcs Performances Wt-hils Can Evaluate?mentioning

confidence: 99%

“…In Russia, a 3-DOF rig in T-203 low-speed wind tunnel was built by SibNIA in 2002 [9] for evaluating the spin recovery strategies of combat aircrafts [10]. In Sweden, a yaw-degree-of-freedom test rig was developed by the Royal Institute of Technology in 2010 [11] for evaluating the control laws of tailless aircrafts. In France, a 3-DOF (free pitch, yaw, and roll) test setup for an autonomous projectile prototype was built by the FrenchGerman Research Institute of Saint-Louis (ISL) in 2015 [12] in order to assess several control approaches for the projectile.…”

Section: Introductionmentioning

confidence: 99%

Wind Tunnel Hardware-in-the-loop Simulation Techniques for Flight Control System Evaluation

Huang

Wang

Zhang

et al. 2017

Proceedings of the 2017 2nd International Conference on Control, Automation and Artificial Intelligence (CAAI 2017)

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I.INTRODUCTION As the traditional hardware-in-the-loop simulation (HILS) in the laboratory for flight control system (FCS) evaluation has to build the mathematical models for aircraft aerodynamics and attitude motions, it still has a great distance away from the totally real flight tests. To replace the mathematical aerodynamic models and attitude models in HILS with real factors, wind-tunnel hardware-in-the-loop simulation (WT-HILS) was used. In WT-HILS, the aerodynamic forces act on the aircraft model in real-time by putting the aircraft model under the simulated airflow in wind tunnel and the aircraft model perform the real attitude motions under the control of the real FCS as shown in FIG. I. Obviously, the WT-HILS is more realistic than the traditional laboratory based HILS. If the WT-HILS is applied to evaluate the FCS before flight tests and after HILS, some FCS errors, such as the control loss in unsteady motions that may occur in real flights and are not detected in HILS can be exposed by WT-HILS. Therefore, the risks of flight tests can be farther reduced by WT-HILS.

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“…In previous studies, stability and control investigations have shown that the model is not stable in yaw for low angles of attack (AOA), and a simple control model has been implemented to handle the instability at moderate sideslip angles [4,5].…”

Section: Introductionmentioning

confidence: 99%