Fuel control system
US5513493A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jul 11, 1986 |
| Grant date | May 7, 1996 |
| Priority date | — |
| Expiry date | Jul 11, 2006 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/051
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Fuel for the combustion equipment of the engine of a vertical take off aircraft is supplied via pumps 50,24 through a metering valve 22, which is under the control of a digital electronic control unit (DECU) 10. A pressure drop regulator 30 and spill valve 32 ensure there is a constant pressure drop across the metering valve 22. To provide a rapid reduction in fuel output when the aircraft pilot slams shut his control lever 16 when he touches down after a vertical landing, and therefore prevent the aircraft from bouncing, the DECU 10 detects the sudden slamming closed of the lever 16, and opens a solenoid valve 60. Fuel now bleeds along line 58, and the input 54 of the regulator 30 sees an increased pressure drop determined by a potentiometer formed by two flow restricting orifices 56,62. The regulator 30 therefore opens the spill valve 32 giving the desired rapid reduction in fuel flow through the metering valve 22.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.