FUEL CONTROL SYSTEM
Assignee
ROLLS-ROYCE PLC
Filed
Jul 11, 1986
Granted
May 7, 1996
Location
BRISTOL EN GB
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: Google Patents
35 USC §181 Secrecy Order
Imposed
May 6, 1987
Rescinded
Sep 26, 1995
Duration
8 years, 4 months
Inventor
- 1MICHAEL J. SEVERN
Record Details
- Patent number
- US 5513493
- Application
- 06887373
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
Browse by Assignee
ROLLS-ROYCE PLCMore from this assignee
Related by domain
COMPACT YAGI ANTENNA ARRAY FOR AIRCRAFT
GRUMMAN AEROSPACE CORPORATION
FIRE CONTROL DEVICE FOR, IN PARTICULAR, TRANSPORTABLE AIR DEFENSE SYSTEMS
STN ATLAS ELEKTRONIK GMBH
AIRCRAFT INFRARED GUIDED DEFENSE MISSILE SYSTEM
PROPELLED PYROTECHNIC DECOY FLARE
SECRETARY OF STATE FOR DEFENCE IN HER BRITANNIC MAJESTY'S GOVERNMENT OF THE UNITED KINGDOM OF GREAT BRITAIN AND NORTHERN IRELAND, THE
SEALING ASSEMBLY FOR REDUCING GAPS BETWEEN MOVABLE CONTROL SURFACES OF AN AIRCRAFT
Lockheed/Skunk Works
AIMING POINT SYSTEM AND TECHNIQUE