초록 ▼

An aircraft with a long body 1 which has a forward end 2 and an aft end 3, which is able to achieve vertical take-off by means of a tilt-able rotor and blade assembly 4 at the forward part of the aircraft and a tilt-able turbojet 19 at the rear of the aircraft. The rotor and blade assembly is rotate

An aircraft with a long body 1 which has a forward end 2 and an aft end 3, which is able to achieve vertical take-off by means of a tilt-able rotor and blade assembly 4 at the forward part of the aircraft and a tilt-able turbojet 19 at the rear of the aircraft. The rotor and blade assembly is rotated by an engine assembly 8, with the engine assembly, the rotor and blades all positioned on top a multi-directional tilt enabling joint 9. The turbojet is fitted to a multi-directional tilt enabling joint 27 to allow control of lateral movement of the aircraft as well as providing vertical lift and forward propulsion during forward flight. The turbojet is connected to the tilt enabling joint 27 by a rivet 30 such that the turbojet can be rotated relative to the tilt enabling joint.

대표청구항 ▼

What I claim as my invention is: 1. An aircraft comprising a main body, a primary lifting mechanism and a secondary lifting mechanism, said lifting mechanisms being located along the longitudinal centerline of said aircraft, which main body has a forward end and an aft end, with the primary lifting

What I claim as my invention is: 1. An aircraft comprising a main body, a primary lifting mechanism and a secondary lifting mechanism, said lifting mechanisms being located along the longitudinal centerline of said aircraft, which main body has a forward end and an aft end, with the primary lifting mechanism and the secondary lifting mechanism connected to the main body of the aircraft in tandem order, and with the aircraft able to achieve flight by means of upward forces exerted on the main body of the aircraft by the primary lifting mechanism and the secondary lifting mechanism while the primary lifting mechanism and the secondary lifting mechanism are connected to the main body of the aircraft in tandem order, and which primary lifting mechanism comprises a power plant as a means for providing downwardly extending thrust to the aircraft, and which secondary lifting mechanism comprises a power plant as a means for providing downwardly extending thrust to the aircraft, and which primary lifting mechanism is connected to the main body of the aircraft by a tilt enabling joint such that during flight of the aircraft the primary lifting mechanism can be tilted in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner, and such that the primary lifting mechanism can be tilted in forward, rearward and lateral directions relative to the main body of the aircraft during flight of the aircraft, in a controlled manner, and such that a direction of travel of the aircraft during flight can be altered by altering the lateral direction or angle of tilt of the primary lifting mechanism relative to the main body of the aircraft, which said tilt enabling joint is a primary tilt enabling joint, and which primary tilt enabling joint is connected to the main body of the aircraft, with the primary lifting mechanism able to exert an upward force on the forward end of the main body of the aircraft through the primary tilt enabling joint, and which secondary lifting mechanism is connected to an additional tilt enabling joint, which said additional tilt enabling joint is a secondary tilt enabling joint, and which said secondary tilt enabling joint is such that during flight of the aircraft the secondary lifting mechanism can be tilted in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner, and such that the secondary lifting mechanism can be tilted in forward, rearward and lateral directions relative to the main body during flight of the aircraft, in a controlled manner, by means of the secondary tilt enabling joint, and such that a direction of travel of the aircraft during flight can be altered by altering the lateral direction or angle of tilt of the secondary lifting mechanism relative to the main body, and which secondary tilt enabling joint is such that the secondary lifting mechanism can be tilted in a controlled manner in a lateral direction with respect to the main body of the aircraft during flight of the aircraft that is opposite to a lateral direction that the primary lifting mechanism can be tilted in with respect to the main body of the aircraft by means of the primary tilt enabling joint during flight of the aircraft, and which secondary lifting mechanism is able to exert an upward force on the aft end of the main body of the aircraft through the secondary tilt enabling joint, with the secondary lifting mechanism connected to the secondary tilt enabling joint by means such that the secondary lifting mechanism is able to be rotated relative to the secondary tilt enabling joint in a controlled manner, and with the aircraft able to achieve flight by means of an upward force exerted on the main body of the aircraft by the primary lifting mechanism extending thrust in a downward direction and an upward force exerted on the main body of the aircraft by the secondary lifting mechanism extending thrust in a downward direction while the primary lifting mechanism and the secondary lifting mechanism are maintained in tandem order, and with controlled lateral tilting of the primary lifting mechanism and the secondary lifting mechanism able to occur during flight. 2. An aircraft comprising a main body, a primary lifting mechanism and a secondary lifting mechanism, which main body has a forward end and an aft end, with the primary lifting mechanism and the secondary lifting mechanism connected to the main body of the aircraft in tandem order, and with the aircraft able to achieve flight by means of upward forces exerted on the main body of the aircraft by the primary lifting mechanism and the secondary lifting mechanism while the primary lifting mechanism and the secondary lifting mechanism are connected to the main body of the aircraft in tandem order, and which primary lifting mechanism comprises a rotor, an engine assembly, and a plurality of blades, with the said blades connected to the rotor, and which said engine assembly is able to rotate the said rotor, with the blades connected to the rotor such that when the rotor is rotated by the said engine assembly air can be forced in a downward direction by means of the blades rotating around the rotor, with the primary lifting mechanism able to exert an upward force on the forward end of the main body of the aircraft by forcing air in a downward direction by way of the blades rotating around the rotor, and which primary lifting mechanism is connected to the main body of the aircraft by a tilt enabling joint such that during flight of the aircraft the primary lifting mechanism can be tilted in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner, and such that the primary lifting mechanism can be tilted in forward, rearward and lateral directions relative to the main body of the aircraft during flight of the aircraft, in a controlled manner, and such that a direction of travel of the aircraft during flight can be altered by altering the lateral direction or angle of tilt of the primary lifting mechanism relative to the main body of the aircraft, which said tilt enabling joint is a primary tilt enabling joint, and which primary tilt enabling joint is connected to the main body of the aircraft, with the primary lifting mechanism able to exert an upward force on the forward end of the main body of the aircraft through the primary tilt enabling joint, and which secondary lifting mechanism is connected to an additional tilt enabling joint, which said additional tilt enabling joint is a secondary tilt enabling joint, and which said secondary tilt enabling joint is such that during flight of the aircraft the secondary lifting mechanism can be tilted in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner, and such that the secondary lifting mechanism can be tilted in forward, rearward and lateral directions relative to the main body during flight of the aircraft, in a controlled manner, by means of the secondary tilt enabling joint, and such that a direction of travel of the aircraft during flight can be altered by altering the lateral direction or angle of tilt of the secondary lifting mechanism relative to the main body, and which secondary tilt enabling joint is such that the secondary lifting mechanism can be tilted in a controlled manner in a lateral direction with respect to the main body of the aircraft during flight of the aircraft that is opposite to a lateral direction that the primary lifting mechanism can be tilted in with respect to the main body of the aircraft by means of the primary tilt enabling joint during flight of the aircraft, and the secondary lifting mechanism comprises at least one jet engine, which said at least one jet engine is attached to the secondary tilt enabling joint such that the said at least one jet engine is able to force exhaust gas from the at least one jet engine to travel in a downward direction and such that by forcing exhaust gas to travel in a downward direction the said at least one jet engine can exert an upward force on the aft end of the main body, and which secondary lifting mechanism is able to exert an upward force on the aft end of the main body of the aircraft through the secondary tilt enabling joint, with the secondary lifting mechanism connected to the secondary tilt enabling joint by means such that the secondary lifting mechanism is able to be rotated relative to the secondary tilt enabling joint in a controlled manner, and with the aircraft able to achieve flight by means of an upward force exerted on the main body of the aircraft by the primary lifting mechanism forcing air in a downward direction and an upward force exerted on the main body of the aircraft by the secondary lifting mechanism forcing exhaust gas to travel in a downward direction while the primary lifting mechanism and the secondary lifting mechanism are maintained in tandem order, and with controlled lateral tilting of the primary lifting mechanism and the secondary lifting mechanism able to occur during flight. 3. The aircraft of claim 2 wherein the said at least one jet engine is a turbojet. 4. The aircraft of claim 3 wherein the engine assembly of the primary lifting mechanism comprises a single engine. 5. The aircraft of claim 3 wherein the engine assembly of the primary lifting mechanism comprises a plurality of engines. 6. The aircraft of claim 2 wherein the said at least one jet engine is a turbofan. 7. The aircraft of claim 6 wherein the engine assembly of the primary lifting mechanism comprises a single engine. 8. The aircraft of claim 6 wherein the engine assembly of the primary lifting mechanism comprises a plurality of engines. 9. The aircraft of claim 2 wherein the engine assembly of the primary lifting mechanism comprises a single engine. 10. The aircraft of claim 2 wherein the engine assembly of the primary lifting mechanism comprises a plurality of engines. 11. An aircraft comprising a main body, a primary lifting mechanism and a secondary lifting mechanism, said lifting mechanisms being located along the longitudinal centerline of said aircraft, which main body has a forward end and an aft end, with the primary lifting mechanism and the secondary lifting mechanism connected to the main body of the aircraft in tandem order, and with the aircraft able to achieve flight by means of upward forces exerted on the main body of the aircraft by the primary lifting mechanism and the secondary lifting mechanism while the primary lifting mechanism and the secondary lifting mechanism are connected to the main body of the aircraft in tandem order, and which primary lifting mechanism is connected to the main body of the aircraft by a tilt enabling joint such that during flight of the aircraft the primary lifting mechanism can be tilted in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner, and such that the primary lifting mechanism can be tilted in forward, rearward and lateral directions relative to the main body of the aircraft during flight of the aircraft, in a controlled manner, and such that a direction of travel of the aircraft during flight can be altered by altering the lateral direction or angle of tilt of the primary lifting mechanism relative to the main body of the aircraft, which said tilt enabling joint is a primary tilt enabling joint, and which primary tilt enabling joint is connected to the main body of the aircraft, with the primary lifting mechanism able to exert an upward force on the forward end of the main body of the aircraft through the primary tilt enabling joint, and which secondary lifting mechanism is connected to an additional tilt enabling joint, which said additional tilt enabling joint is a secondary tilt enabling joint, and which said secondary tilt enabling joint is such that during flight of the aircraft the secondary lifting mechanism can be tilted in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner, and such that the secondary lifting mechanism can be tilted in forward, rearward and lateral directions relative to the main body during flight of the aircraft, in a controlled manner, by means of the secondary tilt enabling joint, and such that a direction of travel of the aircraft during flight can be altered by altering the lateral direction or angle of tilt of the secondary lifting mechanism relative to the main body, and which secondary tilt enabling joint is such that the secondary lifting mechanism can be tilted in a controlled manner in a lateral direction with respect to the main body of the aircraft during flight of the aircraft that is opposite to a lateral direction that the primary lifting mechanism can be tilted in with respect to the main body of the aircraft by means of the primary tilt enabling joint during flight of the aircraft, and which secondary lifting mechanism is able to exert an upward force on the aft end of the main body of the aircraft through the secondary tilt enabling joint, with the secondary lifting mechanism connected to the secondary tilt enabling joint by means such that the secondary lifting mechanism is able to be rotated relative to the secondary tilt enabling joint in a controlled manner, and with the aircraft able to achieve flight by means of an upward force exerted on the main body of the aircraft by the primary lifting mechanism through the primary tilt enabling joint and an upward force exerted on the main body of the aircraft by the secondary lifting mechanism through the secondary tilt enabling joint while the primary lifting mechanism and the secondary lifting mechanism are maintained in tandem order, and with controlled lateral tilting of the primary lifting mechanism and the secondary lifting mechanism able to occur during flight. 12. An aircraft comprising a main body, a primary lifting mechanism and a secondary lifting mechanism, which main body has a forward end and an aft end, with the primary lifting mechanism and the secondary lifting mechanism connected to the main body of the aircraft in tandem order, and with the aircraft able to achieve flight by means of upward forces exerted on the main body of the aircraft by the primary lifting mechanism and the secondary lifting mechanism while the primary lifting mechanism and the secondary lifting mechanism are connected to the main body of the aircraft in tandem order, and which primary lifting mechanism is connected to the main body of the aircraft by a tilt enabling joint such that during flight of the aircraft the primary lifting mechanism can be tilted in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner, and such that the primary lifting mechanism can be tilted in forward, rearward and lateral directions relative to the main body of the aircraft during flight of the aircraft, in a controlled manner, and such that a direction of travel of the aircraft during flight can be altered by altering the lateral direction or angle of tilt of the primary lifting mechanism relative to the main body of the aircraft, which said tilt enabling joint is a primary tilt enabling joint, and which primary tilt enabling joint is connected to the main body of the aircraft, which primary lifting mechanism is a turboprop, and which primary lifting mechanism is attached to the primary tilt enabling joint such that air can be forced in a downward direction by the primary lifting mechanism, and such that by forcing air in a downward direction the primary lifting mechanism is able to exert an upward force on the forward end of the main body of the aircraft, with the primary lifting mechanism able to exert an upward force on the forward end of the main body of the aircraft through the primary tilt enabling joint, and which secondary lifting mechanism is connected to an additional tilt enabling joint, which said additional tilt enabling joint is a secondary tilt enabling joint, and which said secondary tilt enabling joint is such that during flight of the aircraft the secondary lifting mechanism can be tilted in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner, and such that the secondary lifting mechanism can be tilted in forward, rearward and lateral directions relative to the main body during flight of the aircraft, in a controlled manner, by means of the secondary tilt enabling joint, and such that a direction of travel of the aircraft during flight can be altered by altering the lateral direction or angle of tilt of the secondary lifting mechanism relative to the main body, and which secondary tilt enabling joint is such that the secondary lifting mechanism can be tilted in a controlled manner in a lateral direction with respect to the main body of the aircraft during flight of the aircraft that is opposite to a lateral direction that the primary lifting mechanism can be tilted in with respect to the main body of the aircraft by means of the primary tilt enabling joint during flight of the aircraft, and the secondary lifting mechanism comprises at least one jet engine, which said at least one jet engine is attached to the secondary tilt enabling joint such that the said at least one jet engine is able to force exhaust gas from the at least one jet engine to travel in a downward direction and such that by forcing exhaust gas to travel in a downward direction the said at least one jet engine can exert an upward force on the aft end of the main body, and which secondary lifting mechanism is able to exert an upward force on the aft end of the main body of the aircraft through the secondary tilt enabling joint, with the secondary lifting mechanism connected to the secondary tilt enabling joint by means such that the secondary lifting mechanism is able to be rotated relative to the secondary tilt enabling joint in a controlled manner, and with the aircraft able to achieve flight by means of an upward force exerted on the main body of the aircraft by the primary lifting mechanism forcing air in a downward direction and an upward force exerted on the main body of the aircraft by the secondary lifting mechanism forcing exhaust gas to travel in a downward direction while the primary lifting mechanism and the secondary lifting mechanism are maintained in tandem order, and with controlled lateral tilting of the primary lifting mechanism and the secondary lifting mechanism able to occur during flight. 13. The aircraft of claim 12 wherein the said at least one jet engine is a turbojet. 14. The aircraft of claim 12 wherein the said at least one jet engine is a turbofan.