Safety control system with electronic procedure of data acquisition for the inline-regulation of the max. permissible pressure during refueling of the aircraft

Abstract

Safety control system with electronic data acquisition for the inline regulation of the max. permissible pressure during refueling of the aircraft. With this procedure the driving speed of the feed pump is regulated to so that no higher refueling pressure than 35 respectively 50 PSI can develop. The diesel engines were equipped already some years ago with an interface for an external control of number of revolutions. www.manted.de The received messages for the control modules are given binarily with parameters. In case of leakages within the pressure range or deviations from the differential pressure the refueling of the aircraft is interrupted automatically. The inline regulation examines itself independently by the audible change of the number of revolutions of the engine during each aircraft refueling. If one single person does the refueling of the aircraft the automatic control is of significant importance. In case of refueling with the wrong quality the electronic safety characteristic is left, which causes an automatic stop of aircraft refueling. With this procedure a substantial progress regarding the increase of safety of aircraft refueling is given.

1 . Safety control system with electronic procedure of data acquisition for the inline regulation of the max. permissible pressure during refueling of the aircraft. 
 Characterized by the fact that only the energy respectively regulated driving speed of diesel engines for the max. permissible pressure of the feed pump is used.    
   
   
       2 . Inline regulation according to patent  claim 1 . 
 Characterized by the fact that flow resistances in the pressure conducting piping and their armatures such as measuring instruments, filters and quantity counters are measured with a piston differential pressure gauge ( 9 ).    characterized by the fact that the patterns ( 10 ) of the black not reflecting and white reflector surfaces or mirror surfaces alternatively in the piston are scanned with reflex light conductors and the resulting binary code is used for the calculation of the already known interface MAN-message external number of revolutions of the motor.    characterized by the fact that for the data determination the measuring point X 1  is equipped with a pressure sensor.    characterized by the fact that the refueling of the aircraft is interrupted in case of deviation of the calculated characteristics.