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An aircraft including an airframe having a fuselage which extends longitudinally, and having fixed wings including a main wing, a horizontal tail wing and a vertical tail wing. A propeller-rotor torque transmission has a bevel gear which transmits the rotation of an input shaft simultaneously to a p

An aircraft including an airframe having a fuselage which extends longitudinally, and having fixed wings including a main wing, a horizontal tail wing and a vertical tail wing. A propeller-rotor torque transmission has a bevel gear which transmits the rotation of an input shaft simultaneously to a propeller shaft and to a rotor shaft. An engine gearbox supplies the above-mentioned input shaft with rotationalal motive power. The aircraft further includes a propeller collective pitch controller, a rotor collective pitch controller, an engine power controller which controls the output of the above-mentioned engine gearbox for the purpose of changing the rotational speed of the input shaft, and a flight control system having a directional (yaw) control system which controls the flight direction of the aircraft by controlling the positions of the above-mentioned control surfaces.

대표청구항 ▼

1. An aircraft comprising:(a) an airframe having (1) a fuselage extending longitudinally, (2) a set of fixed wings consisting of a main wing and a horizontal tail wing both of which are connected to said fuselage at two locations longitudinally apart from each other and both of which extend laterall

1. An aircraft comprising:(a) an airframe having (1) a fuselage extending longitudinally, (2) a set of fixed wings consisting of a main wing and a horizontal tail wing both of which are connected to said fuselage at two locations longitudinally apart from each other and both of which extend laterally and are capable of producing lifts during forward flight, and a vertical tail wing, (3) two ailerons one of which is installed on the right-hand section of said main wing and the rest of which is installed in the left-hand section of said main wing, (4) two elevators one of which is installed on the right-hand section of the above mentioned horizontal tail wing and the rest of which is installed in the left-hand section of the above mentioned horizontal tail wing, and (5) a rudder installed on the above mentioned vertical tail wing; (b) a propeller-rotor torque transmission having (1) a shaft support coupler wherein one end each of a propeller shaft support and a rotor shaft support both of which lie at right angles to each other, and one end of an input shaft which lies at right angles to said propeller shaft support and to said rotor shaft support or which lies coaxially with either said propeller shaft support or with said rotor shaft support, are coupled together in such a way as to preclude rotation, (2) a cylindrical input shaft which is installed in such a way as to permit rotation around said input shaft support, (3) a cylindrical propeller shaft which is installed in such a way as to permit rotation around said propeller shaft support and on which a variable pitch propeller for producing a propelling force is installed, (4) a cylindrical rotor shaft which is installed in such a way as to permit rotation around said rotor shaft support and on which is installed a rotor head that supports a rotor blade for producing a lift such that only the collective pitch is variable, and (5) a bevel gear which transmits the rotation of said cylindrical input shaft (hereinafter referred to as an input shaft), simultaneously to said cylindrical propeller shaft (hereinafter referred to as a propeller shaft), and to said cylindrical rotor shaft (hereinafter referred to as a rotor shaft); (c) an engine gearbox which supplies said input shaft with rotational motive power; and (d) a flight control system having (1) a propeller collective pitch controller which controls the pitch angle of said variable pitch propeller, (2) a rotor collective pitch controller which controls the collective pitch of said rotor blade, (3) an engine power controller which controls the output of said engine gearbox for the purpose of changing the rotational speed of said input shaft, and (4) a directional (yaw) control system which controls the deflection angles of said ailerons and said rudder to control the flight direction of the aircraft during forward flight.