Abstract
A helicopter flight control system is designed to incorporate variable rotor speed while handling torque limits and other constraints. The vertical axis controller uses a fixed non-linear mapping to find the combination of collective pitch and rotor speed to optimize performance in level flight, climbing/descending flight, and steady turns. In this scheme, the controller is open-loop, making it an inexpensive and reliable solution. The mapping is designed to produce a desired power level for a given pilot input. Thus the mapping can take into account the performance limits associated with the vertical axis such as power limits, torque limits, and maximum rate of descent. A model following controller is implemented for the pitch, roll, and yaw axes. The control system is demonstrated using the GENHEL simulation of a UH-60A helicopter.
Original language | English (US) |
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Pages (from-to) | 1617-1627 |
Number of pages | 11 |
Journal | Annual Forum Proceedings - AHS International |
Volume | 2 |
State | Published - 2009 |
Event | 65th Annual Forum Proceedings - AHS International - Grapevine, TX, United States Duration: May 27 2009 → May 29 2009 |
All Science Journal Classification (ASJC) codes
- General Engineering