Boosted Incremental Nonlinear Dynamic Inversion for Flexible Airplane Gust Load Alleviation

Active gust load alleviation is an important technology for reducing loads on future commercial airplanes so that the structure can be designed to be lighter in order to save fuel. For the intense reduction of gust loads, a highly reactive control system of sensors, control algorithms, and actuators...

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Bibliographic Details
Published in:Journal of guidance, control, and dynamics control, and dynamics, 2024-07, Vol.47 (7), p.1394-1413
Main Authors: Beyer, Yannic, Steen, Meiko, Hecker, Peter
Format: Article
Language:English
Subjects:
Acceleration
Actuators
Algorithms
Center of gravity
Commercial aircraft
Control algorithms
Control systems
Control theory
Dynamic inversion
Dynamical systems
Feedback
Gust loads
Load alleviation
Nonlinear dynamics
Time lag
Trailing edge flaps
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Summary:Active gust load alleviation is an important technology for reducing loads on future commercial airplanes so that the structure can be designed to be lighter in order to save fuel. For the intense reduction of gust loads, a highly reactive control system of sensors, control algorithms, and actuators is required, which is not yet available. In this paper, a control algorithm based on incremental nonlinear dynamic inversion is extended so that actuators respond faster. The control algorithm is applied to a future medium-range aircraft with distributed trailing-edge flaps. It is assumed that the vertical acceleration of the center of gravity and the displacement, velocity, and acceleration of the first wing bending mode are available as feedback variables. To allow comparability with other actuator and sensor setups, the authors abstract the actuator dynamics and sensor filter as control system time delay. The feedback gains are adjusted automatically to the control system time delay. In simulation, the authors investigate the influence of the control system time delay on the peak gust loads. They show that gust loads can indeed be intensely reduced with sufficiently small control system time delay in simulation.
ISSN:0731-5090
1533-3884
DOI:10.2514/1.G007984