Design and Analysis of a Launcher Flight Control System Based on Incremental Nonlinear Dynamic Inversion

This paper investigates the application of Incremental Nonlinear Dynamic Inversion (INDI) for launch vehicle flight control, addressing the limited exploration of nonlinear control architectures and their potential benefits in the context of the current “New Space” era. In this context, this study a...

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Vydané v:	Aerospace Ročník 12; číslo 4; s. 296
Hlavní autori:	Simplício, Pedro, Acquatella, Paul, Bennani, Samir
Médium:	Journal Article
Jazyk:	English
Vydavateľské údaje:	Basel MDPI AG 01.04.2025
Predmet:	acceleration feedback Actuators Aerodynamics Aircraft Angular acceleration Artificial intelligence Attitude control Automatic pilot (Airplanes) Closed loops Context Control algorithms Control systems Controllers Design Dynamic inversion Dynamical systems Feedback Flight control systems Gain scheduling Launch vehicles Launchers Linear control load relief Methods Noise sensitivity Nonlinear control Nonlinear dynamics Nonlinearity robust control Robustness Sensors Stability analysis Vehicles
ISSN:	2226-4310, 2226-4310
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