AIRBORNE AIRCRAFT FUEL FLOW METER SYSTEM WITH FUEL TEMPERATURE AND DIELECTRIC PERMEABILITY COMPENSATION Russian patent published in 2008 - IPC B64D37/00 B64D37/14 G01F23/26 

FIELD: aircraft instrument.

SUBSTANCE: system may be used to meter fuel stock and flow in a maneuverable aircraft. The system incorporates fuel flow rate pickups (6) mounted in operating lines and in return lines (8) of aircraft power plant (19), counter of mass flow fuel rate (13) mounted in the fuel feeding line (15), fuel level pickups (1) and fuel level signalling devices (20) mounted in fuel tanks, fuel temperature pickups (4) and fuel dielectric permeability pickups (3) mounted in the lines and aircraft power plant tanks. The system incorporates, also, airborne computer (23), comparator (29), indicator (30) and the following electronic units, i.e. overflow unit (24), return unit (27), fuelling unit (25), refuelling unit (26) and balancing unit (28). Proceeding from the data on fuel coming from the aforesaid system pickups, signalling devices and the counter, and in compliance with data received from the aircraft outer systems on types of fuelling, refueling and returning kept in the airborne computer, comparator and counter memory, the system defines the amount of fuel fed into the tanks on ground, current stock of fuel in flight, the amount of fuel fed from the aircraft and aerodynamic amount of fuel required for aircraft return. With the aircraft lateral centering disturbed, the system balancing unit recovers the required centering.

EFFECT: higher accuracy and efficiency of control over fuel flow rates and distribution.

1 dwg