This article proposes an adaptive bounding-based dynamic inversion controller, composed of a baseline controller and an adaptive controller, for a coaxial compound helicopter. The static output-feedback baseline controller is designed using a linear matrix inequality-based iterative algorithm and the dynamic inversion concept, aiming for model following performance and guaranteed closed-loop fuselage–rotor stability under periodic perturbations. The adaptive controller is designed based on the adaptive bounding concept to augment the baseline controller for vibration attenuation. A benchmark example of a linear periodic system is first studied to demonstrate the effectiveness of the proposed control design method. A mathematical model is developed to study the flexible multibody dynamics of a coaxial compound helicopter. Such a model is used to examine the performance of the proposed controller in helicopter high-speed flight via numerical simulations.
Adaptive Bounding-Based Dynamic Inversion Control of a Coaxial Compound Helicopter
IEEE Transactions on Aerospace and Electronic Systems ; 59 , 6 ; 9451-9462
2023-12-01
5136650 byte
Article (Journal)
Electronic Resource
English