Propulsion power plants for aircraft

Claim 1

AIRCRAFT JET PROPULSION POWER PLANT COMPRISING WALLS ENCLOSING A MAIN DUCT HAVING A FORWARDLY FACING AIR INTAKE OPENING AT ONE END AND AN OUTLET END, AT LEAST ONE TURBOJET ENGINE AND AT LEAST ONE COMBUSTOR DUCT ENGINE, THE ENGINES BEING MOUNTED IN THE MAIN DUCT SIDE BY SIDE AND SPACED FROM THE INLET AND OUTLET ENDS, AND WALLS EXTENDING FROM THE ENGINES TO THE OUTLET END OF THE MAIN DUCT SO AS TO DIVIDE THAT PART OF THE MAIN DUCT INTO SEPARATE OUTLET NOZZLES, ONE FOR EACH ENGINE, THE WALLS OF THE TURBOJET NOZZLE INCLUDING MEANS FOR CHANGING ITS DIVERGENCE BUT NOT ITS THROAT AREA AND THE WALLS OF THE COMBUSTOR DUCT NOZZLE INCLUDING THROAT AREA CHANGING MEANS, AND MEANS RESPONSIVE TO CHANGE OF POSITION OF A NORMAL SHOCK WAVE IN THE MAIN DUCT BETWEEN THE INLET AND THE ENGINES, AND OPERATIVE UPON THE COMBUSTOR NOZZLE THROAT AREA CHANGING MEANS TO OPPOSE SUCH CHANGE OF POSITION, A COMBUSTOR FUEL FLOW CONTROL AND MEANS RESPONSIVE TO THE COMBUSTOR NOZZLE THROAT AREA APPROACHING ITS MAXIMUM FOR ACTING ON THE COMBUSTOR FUEL FLOW CONTROL TO REDUCE THE SUPPLY OF FUEL.