Jet sustained and propelled aircraft

Claim 1

IN A WINGLESS GAS JET DISCHARGE ENGINE-PROPELLED HEAVER THAN AIR FLYING VEHICLE WHICH IS DEVOID OF CONNECTION TO SUBJACENT GROUND OR WATER WHEN IN FLIGHT, SO AS TO BE ADAPTED FOR HIGH SPEED FLYING AT FROM LOW TO HIGH ALTITUDES SAID VEHICLE HAVING WALLS PROVIDING A HOLLOW FUSELAGE WHICH IS SUBSTANTIALLY PLANE BOTTOM WALL AND FUSELAGE PROVIDING A SUBSTANTIALLY PLANE BOTTOM WALL AND MERGING SIDE AND TOP WALLS WHICH ARE CONVEXLY CURVED BOTH TRANSVERSELY AND LONGITUDINALLY THROUGHOUT THEIR EXTENT AND THE LENGTH OF THE FUSELAGE, SAID FUSELAGE HAVING AN INTERIOR AND FORWARDLY CLOSED ENGINE-RECEIVING SPACE AT LEAST IN PART PROVIDED BY SAID TOP, BOTTOM AND SIDE FUSELAGE WALLS; TWO FIRST AND ONE SECOND GAS DISCHARGE TYPE REACTION ENGINES DISPOSED ENTIRELY WITHIN SAID FUSELAGE SPACE, THE TWO FIRST ENGINES IN SAID SPACE BEING LOCATED APPROXIMATELY MIDWAY THE LENGTH OF SAID FUSELAGE AND ADJACENT OPPOSITE SIDES OF THE LATTER; THE BOTTOM WALL OF SAID ENGINE-RECEIVING SPACE CONSTITUTING THE BOTTOM WALL OF SAID FUSELAGE AND PROVIDED WITH AN OPENING EXTENDING THERETHROUGH ADJACENT EACH SIDE, MOUNTING MEANS FOR EACH OF SAID FIRST ENGINES CARRIED BY SAID BOTTOM WALL AND SURROUNDING THE RESPECTIVE OPENINGS THEREIN AS A BOTTOM FUSELAGE WALL REINFORCEMENT AT THE SITE OF SAID OPENINGS, SAID FIRST ENGINES BEING DISPOSED IN A DOWNWARDLY DISCHARGING AND SUBSTANTIALLY VERTICAL POSITION AND DIRECTING THEIR REACTING FORCES DOWNWARDLY THROUGH SAID BOTTOM WALL OPENINGS, WHEREBY TO VERTICALLY LIFT OR CONTROLLEDLY LOWER THE VEHICLE FOR A LANDING, THE SECOND SINGLE GAS DISCHARGE TYPE REACTION ENGING HAVING A REARWARDLY DIRECTED GAS DISCHARGE END AND CONSTITUTING THE STEERING AND FORWARD PROPULSION MEANS FOR SAID VEHICLE, SAID SINGLE SECOND ENGINE LOCATED ADJACENT THE REAR END OF BOTH THE VEHICLE FUSELAGE AND ENGINE-RECEIVING SPACE, SAID REAR FUSELAGE END HAVING AN OPENING THEREIN COMMUNICATING DIRECTLY WITH SAID ENGINE-RECEIVING SPACE, AT LEAST THE TOP AND SIDE WALLS OF SAID ENGINE-PROVIDING SPACE BEING IMPERFORATE WHEN THE VEHICLE IS IN FLIGHT SAID REAR FUSELAGE OPENING BEING OF SUBSTANTIALLY GREATER WIDTHWISE AREA THAN THE GAS DISCHARGE END OF SAID SECOND ENGINE, A CIRCULAR TRACKING WITHIN SAID SPACE AND AFFIXED TO ONE OF THE TOP AND BOTTOM WALLS AS A REINFORCEMENT FOR SAME, A MEMBER ON WHICH SAID SECOND ENGINE IS AFFIXED AND WHICH MEMBER IS REVOLUBLY ENGAGED WITH SAID TRACKING TO TURN IN A HORIZONTAL PLANE AROUND ITS AXIS THROUGH ANY DESIRED ANGLE, THE DISCHARGE END OF SAID SECOND ENGINE BEING DISPOSED WITH RELATION TO SAID REAR FUSELAGE OPENING TO DIRECT ITS REACTION FORCE THERETHROUGH DURING ALL POSITIONS OF OPERATIVE ADJUSTMENT THEREOF RELATIVE TO SAID FIXED TRACKWAY, AN UPSTANDING STABILIZING FIN FIXEDLY CARRIED BY THE UPPER EXTERIOR PORTION OF SAID FUSELAGE EXTENDING LONGITUDINALLY OF THE LATTER ABOVE SAID SECOND ENGINE TO A POINT ADJACENT THE PLANE OF THE FIRST TWO ENGINES AND BEING OF SUBSTANTIAL HEIGHT CAS COMPARED TO FUSELAGE DEPTH, WHEREBY TO COOPERATE WITH THE LATTER AS AN AID IN PREDETERMINEDLY CONTROLLING TURNING OF THE VEHICLE IN FLIGHT, AND SAID FIRST AND SECOND ENGINES COOPERATING T<O PROPESL SAID VEHICLE IN FLIGHT WITH A MAXIMUM DRAG AND A MAXIMUM EFFICIENCY.