Starting system for a helicopter power plant control
US3938320A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jul 17, 1974 |
| Grant date | Feb 17, 1976 |
| Priority date | — |
| Expiry date | Jul 17, 1994 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/329
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A control system for a helicopter power plant with three power units driving the lifting rotor system through a main gearbox. Each power unit comprises a gas turbine engine of the gas-coupled type, a hydromechanical fuel control receiving electrical inputs to set a gas generator governor in the fuel control, an engine electronic control, and various engine accessories. The operation of the power plant is normally controlled by the pilot through condition levers and switches on a control quadrant, through a pitch control by which the collective pitch of the rotor blades is controlled, and through a master beeper switch which is operable to trim the setting of an isochronous governor for the rotor system and the gas generator governors. The condition lever of each engine transmits a speed command signal through the electronic control of each power unit to its gas generator governor. A signal of collective pitch transmitted from the rotor control system to each engine electronic control is another factor in setting the governor. The power plant includes a power management control, the principal function of which is to equalilze the power outputs of the engines. It also includes the ro…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.