A robust control method for an oblique flying wing aircraft includes computing an angular velocity error between a reference angular velocity and an actual angular velocity and computing a moment command with an angular velocity controller based at least in part on the angular velocity error. The angular velocity controller decouples two or more of a yaw rate axis, a pitch rate axis, and a roll rate axis of the asymmetric aircraft for the moment command.
Robust Control of Oblique Flying Wing Aircraft
2024-10-10
Patent
Electronic Resource
English