A variable cycle propulsion system for a supersonic airplane, the system comprising
at least one engine having at least one compressor and capable of generating thrust
for supersonic flight speeds, and at least one auxiliary propulsion assembly separate
from said engine, and capable of generating additional thrust for takeoff, landing,
and subsonic cruising speeds, at least one pipe connecting the engine to the auxiliary
propulsion assembly to convey thereto compressed air produced by the compressor
so as to enable the auxiliary propulsion assembly to generate additional thrust
for takeoff, landing, and subsonic cruising flight, there being at least one valve
enabling the pipe to be closed off for supersonic cruising flight.
