Pulse-jet aircraft and engine and diffusion systems for use therein

Claim 1

A PULSE-JET ENGINE COMPRISING TWO COMBUSTION CHAMBERS, A RESONATOR HAVING A SUBSTANTIALLY U-SHAPED CROSS-SECTION INCLUDING A MEDIAL SECTION AND TWO ARMS CONNECTING THE MEDIAL SECTION WITH THE CORRESPONDING CHAMBERS, A PARTITION DIVIDING EACH ARM INTO TWO DUCTS OF WHICH ONE FLARES TOWARDS THE COMBUSTION CHAMBER AND OPENS INTO THE LATTER AND THE OTHER FLARES TOWARDS THE MEDIAL SECTION, MEANS FOR PROVIDING AN INPUT OF AIR INTO THE OUTWARDLY CONCAVE WALL OF THE MEDIAL SECTION OF THE RESONATOR BETWEEN THE ARMS THEREOF, A CORE EXTENDING ACROSS THE RESONATOR PERPENDICULARLY TO THE U-SHAPED CROSS-SECTION AND HAVING A CROSS-SECTIONAL SHAPE WHICH IS SUBSTANTIALLY THAT OF A CURVILINEAR TRIANGLE FACING THE AIR INPUT THROUGH AN APEX IN PROXIMITY WITH THE LATTER, A SERIES OF PARTITIONS EXTENDING IN EACH CHANNEL FORMED BETWEEN SAID CORE AND THE COOPERATING WALL OF THE MEDIAL SECTION TO SUBDIVIDE SAID CHANNEL LONGITUDINALLY, PRESSURESENSITIVE MEANS SUBJECTED TO THE PRESSURE IN EACH ARM, AN ELECTRONIC SYSTEM CONTROLLED BY SAID PRESSURE-SENSITIVE MEANS AND ADAPTED TO PRODUCE PULSES EACH TIME THE PRESSURE PASSES IN THE CORRESPONDING ARM THROUGH A PREDETERMINED VALUE AND FUEL-INJECTING AND FIRING MEANS IN EACH COMBUSTION CHAMBER AND CONTROLLED BY THE PULSES FED BY THE PRESSURE-SENSITIVE MEANS SUBJECTED TO THE PRESSURE IN THE ARM OPENING INTO THE OTHER COMBUSTION CHAMBER.