Helicopter autorotation detection and recovery
US5046923A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Oct 2, 1989 |
| Grant date | Sep 10, 1991 |
| Priority date | — |
| Expiry date | Oct 2, 2009 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/04
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
The existence of autorotation of a load (e.g., a helicopter rotor system) coupled to the free turbine of a gas turbine engine is determined and a signal indicative thereof enables an integrator which, upon autorotation, integrates rate-based recovery anticipation provided thereto, the integrator output providing a time-composite bias signal to the main control portion of the engine fuel control to increase the speed of the gas generator of the engine in anticipation of rotor reengagement with the free turbine. The amount of recovery error is determined from the rotor speed error and is multiplied with the integrator output, the product being fed, upon completion of autorotation recovery, to the integrator input whose output now provides a controlled removal of the bias signal from the main control portion so as to minimize transients induced therein.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.