On the controllers' design to stabilize ground resonance helicopter

On the controllers' design to stabilize ground resonance helicopter

Ground resonance (GR) in helicopters is a potentially catastrophic instability commonly caused by coalescence of the regressive cyclic blade lag mode with the fuselage motion in certain rotor speed ranges. It can limit the helicopter operational envelope and the design of this type of vehicle can be...

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Bibliographic Details
Published in:Journal of vibration and control Vol. 25; no. 23-24; pp. 2894 - 2909
Main Authors: Ignácio da Silva, José A., Bueno, Douglas D., Abreu, Gustavo L. C. M. de
Format: Journal Article
Language:English
Published: London, England SAGE Publications 01-12-2019
SAGE PUBLICATIONS, INC
Subjects:
Active control
Actuators
Airframes
Coalescence
Coalescing
Computational geometry
Computer simulation
Control stability
Control systems
Control systems design
Controllers
Convexity
Design
Feedback
Formulations
Fuselages
Ground resonance
Helicopters
Linear matrix inequalities
Matrix methods
Optimization
Parameter uncertainty
Resonance
Robust control
Rotor speed
Stability criteria
Viability
robust control gain
Ground resonance helicopter
linear matrix inequalities
controller design
rotor speed range stabilization
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Description
Summary:Ground resonance (GR) in helicopters is a potentially catastrophic instability commonly caused by coalescence of the regressive cyclic blade lag mode with the fuselage motion in certain rotor speed ranges. It can limit the helicopter operational envelope and the design of this type of vehicle can become a difficult task. Although a broad class of actuators allows the use of active and semi-active techniques to design feedback-based control systems, a limited number of works in the literature introduce formulations to compute the controller gain to suppress this phenomenon. Also, commonly, a control approach defines a feedback, particularly to a specific rotor speed. In this context, this work introduces an alternative methodology to design an active control system to stabilize GR of a helicopter. The proposed approach can suppress this instability in all rotor speed ranges by using only one control gain. Two strategies are proposed based on linear matrix inequalities (LMIs). The Lyapunov stability criteria are used and the unstable rotor speed is considered as an uncertain parameter to define an associated convex space. Using convex optimization, a robust control gain is computed until all the unstable rotor speed range is stabilized. Numerical simulations are carried out to demonstrate the effectiveness of this methodology. The results confirm the viability of the proposed approach to design active and semi-active controllers.
ISSN:1077-5463
1741-2986
DOI:10.1177/1077546319873797