though for the sake of simplicity only the fig1 reference numerals will be identified the dual mode aircraft 11 operates like a helicopter for vertical take off in this mode exhaust gases from the engines 23 and 25 flow through the rotor blade passages 27 and 29 exiting from tip nozzles 31 and 33 to thereby drive the rotor wing 17 rotationally about the hub 15 because of the use of this type of reaction drive the need for conventional transmission and antitorque systems is eliminated though conventional drives could be employed if desired during rotary wing flight the rotor wing 17 acts like a conventional helicopter rotor as noted above flight is controlled by means of the gimbaled teetering hub 15 and the feathering hinges 35 and 37 for controlling the pitch of the rotor blades using conventional cyclic and collective pitch control mechanisms with yaw control being provided by nozzles 41 on each side of the fuselage when the aircraft reaches a suitable altitude appropriate control adjustments are made to begin translational horizontal flight in the helicopter mode alternatively the aircraft may continue to hover like a helicopter indefinitely the rotorcraft converts into fixed wing mode by transitioning from a pure helicopter to a compound helicopter at about 60 knots at this speed the canard 43 and.