Thrust control apparatus

Claim 1

IN COMBINATION WITH AN AIRCRAFT HAVING A TURBO-JET ENGINE, SAID ENGINE HAVING A COMPRESSOR AND TURBINE OPERATIVELY CONNECTED TOGETHER, A TURBINE OUTPUT SHAFT EXTENDING FROM SAID TURBINE, THE IMPROVED COMPRISING, REDUCTION GEAR MEANS HAVING AT LEAST ON OUTPUT SHAFT, AIR BLEED MEANS CONNECTED TO SAID COMPRESSOR, BOUNDARY LAYER FORMING MEANS RECEIVING AIR FROM SAID BLEED MEANS AND SUPPLYING SAID BLEED AIR TO THE WING SURFACES, SAID ENGINE OUTPUT SHAFT BEING COUPLED TO REDUCTION GEAR MEANS, SAID REDUCTION GEAR MEANS OUTPUT SHAFT HAVING A VARIABLE PITCH PROPELLER MOUNTED THEREON, POWER ABSORBING MEANS OPERATIVELY CONNECTED TO SAID REDUCTION GEAR MEANS, CONTROL MEANS FOR VARYING THE AMOUNT OF POWER ABSORBED BY SAID POWER ABSORBING MEANS, WHEREBY THE R.P.M. OF SAID ENGINE MAY BE INCREASED THUS PROVIDING A GREATER AMOUNT OF BLEED AIR WHICH MAY BE USED TO INCREASE THE LIFT COEFFICIENT WHILE THE R.P.M. OF SAID PROPELLERS MAY BE MAINTAINED AT A CONSTANT R.P.M. BY MEANS OF SAID POWER ABSORPTION MEANS.