Control system for gas turbine helicopter engines and the like
US5303142A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jul 2, 1993 |
| Grant date | Apr 12, 1994 |
| Priority date | — |
| Expiry date | Jul 2, 2013 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05B13/024
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
A engine control system for helicopters and the like in which free turbine speed is isochronously controlled by a more robust control system having increased bandwidth due to loop architecture and filter implementation accomplished via closed loop control. Dual notch (feedback compensation) is used with design forward path compensation, including variable lead/position of the lead, variable gain and implementation of integrator/proportional. Superior transient control is achieved by the use of a multi-loop governing design using different error compensations when on "NF" loop control and when not on "NF" loop control, and with "bumpless" inner loop reference by the combination of compensation switching and re-initialization of a common integrator. Parallel select logic with dynamic compensation is used separating the system control loops and the selection process of the controlling functions, as they pertain to the application of control loops designed form small signal stability to large transients. A torque loop limitation as a direct function of the speed loop gains provides a predetermined limit to the governed speed excursion in the event of an in-range failure of the torque s…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.