A Novel Emergent State Control Law for an Integrated Helicopter/Turboshaft Engine System

A Novel Emergent State Control Law for an Integrated Helicopter/Turboshaft Engine System

Zhang, H.
Li, Y.
Deng, S.

Aerospace Engineering

Aerodynamics, Wind Energy & Propulsion

2014-02-11

A two-layer robust control scheme is proposed to get a better response ability for emergency maneuvers of helicopter. Note that the power used in ascending flight is the main coupling between helicopter and its turboshaft engines; therefore vertical flight control is separated from conventional helicopter control loops and combined with fuel flow and turbine bleeding to new control loops denoted as an inner layer, whereas the mission level flight control is as the out layer. A conclusion in global asymptotically tracking for devising this new scheme is firstly derived from a Generalized Gronwall-Bellman approach. Due to this integrated designing, not only is the helicopter better controlled, but also much better power rapid tracking is realized for engines. Simulations are conducted to validate the new scheme in emergent ascending and descending flights, and the results illustrate that the response time of the closed-loop system is dramatically reduced when compared to the traditional one. Moreover, the presented system also has better dynamic performance under inferences.

http://resolver.tudelft.nl/uuid:b3cbae91-30e0-495c-ace4-2b0a5c995d0f

Hindawi Publishing Corporation

1563-5147

Mathematical Problems in Engineering, Volume 2014 (2014), Article ID 385807

Institutional Repository

journal article

© 2014 Haibo Zhang et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.