초록 ▼

A compound Vertical TakeOff and Landing (VTOL) aircraft. In a specific embodiment, the VTOL aircraft includes a gas-powered tip-jet driven rotary-wing and a fixed-wing that is capable of providing necessary lift to the aircraft during certain forward-flight regimes so that lift from the rotary-wing

A compound Vertical TakeOff and Landing (VTOL) aircraft. In a specific embodiment, the VTOL aircraft includes a gas-powered tip-jet driven rotary-wing and a fixed-wing that is capable of providing necessary lift to the aircraft during certain forward-flight regimes so that lift from the rotary-wing is not required. This enables slowing of the rotor, thereby reducing drag during forward flight and enabling flight above and below mu-1. Valves and accompanying ducting are employed to control compressed gas flow to the rotary-wing. Various reaction jets are employed for attitude control during VTOL and transition operations. The aircraft further includes a jet exhaust nozzle to provide forward thrust to facilitate forward flight.

대표청구항 ▼

I claim: 1. A compound aircraft comprising: an engine; first means for propelling the aircraft in flight, wherein the first means includes: ducting and valves for passage and control of compressed gases derived from the engine and a gas-powered tip-jet driven rotor system having one or more blades

I claim: 1. A compound aircraft comprising: an engine; first means for propelling the aircraft in flight, wherein the first means includes: ducting and valves for passage and control of compressed gases derived from the engine and a gas-powered tip-jet driven rotor system having one or more blades to which the compressed gases are delivered; second means for controlling and stabilizing the rotor system under flight conditions above and below Mu-1; and a fuselage coupled to the engine and the first means. 2. The compound aircraft of claim 1 further including: a computer for operating one or more flaps, wherein the one or more flaps are affixed to one or more of the one or more rotor blades, and wherein the computer includes one or more instructions for: stabilizing the tip-jet driven rotor system when the tip-jet driven rotor system encounters variations in free-stream air velocity and compensating for changes in airflow across the tip-jet driven rotor system to facilitate surpassing the mu-1 barrier. 3. The compound aircraft of claim 1 further including: high-rate actuators that are operable in a cyclic fashion to facilitate controlling the tip-jet driven rotor system, including facilitating collective pitch control of the tip-jet driven rotor system. 4. The compound aircraft of claim further including: one or more aeroservoelastic structures coupled to or embedded in one or more of the blades, wherein the one or more aeroservoelastic structures are adapted to facilitate controlling blade twist, blade pitch, and blade vibration. 5. The compound aircraft of claim 1 wherein the one or more aeroservoelastic structures include one or more piezoelectric actuators. 6. The compound aircraft of claim 1 wherein one or more tips of the one or more blades are curved or rounded. 7. The compound aircraft of claim 1 wherein the ducting extends to reaction jets in the wing, wherein the reaction jets are adapted to facilitate controlling roll of the compound aircraft, and wherein the ducting is adapted to provide de-icing capability for the wing and the one or more blades. 8. The compound aircraft of claim 1 further including: a jet exhaust that exits through an exhaust nozzle, wherein the jet exhaust originates from the engine and is selectively diverted to the exhaust nozzle via the ducting and valves, and wherein the exhaust nozzle is directed aft of the compound aircraft to facilitate providing forward propulsion to the compound aircraft. 9. The compound aircraft of claim 1 further including: a manifold within or coupled to a hub of the tip-jet driven rotor system. 10. The compound aircraft of claim 1 further including: one or more leading-edge and trailing-edge flaps affixed to the wing, wherein the one or more leading-edge and trailing-edge flaps are adapted to facilitate transitioning between flight modes. 11. The compound aircraft of claim 1 further including: one or more reaction jets for controlling the attitude of the compound aircraft around pitch and/or roll axes. 12. The compound aircraft of claim 1 wherein cross-sections of the blades are approximately elliptically shaped. 13. The compound aircraft of claim 1 further including a rearward or forward facing propeller for propelling the compound aircraft in forward flight. 14. The compound aircraft of claim 13 wherein the propeller is tip-jet driven. 15. The compound aircraft of claim 1 wherein the rotor system includes one or more rotor blades which do not stop moving during flight.