Aircraft controlled by compressed air

1. An aircraft comprising:

a fuselage having a main wing at opposite sides and elongated along a longitudinal direction of the fuselage;

a first nozzle disposed on a roof of the fuselage and elongated along the longitudinal direction of the fuselage;

a plurality of second nozzles disposed on an upper surface of the main wing along a longitudinal direction of the main wing;

a first tank disposed in the fuselage or the main wing and configured to store first compressed air; a main control valve configured to provide the first compressed air to the first nozzle or the plurality of second nozzles;

a second tank configured to store second compressed air;

a pressure reducing valve configured to reduce a pressure of the second compressed air of the second tank and coupled to the first tank;

a first pitching nozzle disposed on a lower front side of the fuselage and configured to spray the first compressed air in a downward direction;

a second pitching nozzle disposed on a lower rear side of the fuselage and configured to spray the first compressed air in the downward direction;

a first rolling nozzle disposed at a right end of the main wing and configured to spray the first compressed air in the downward direction;

a second rolling nozzle disposed at a left end of the main wing and configured to spray the first compressed air in the downward direction;

a first yaw nozzle disposed at a right end of main wing and configured to spray the first compressed air in a backward direction; and

a second yaw nozzle disposed at a left end of the main wing and configured to spray the first compressed air in the backward direction,

wherein a pressure of the first compressed air is lower by a predetermined amount compared to the pressure of the second compressed air.

2. The aircraft according to claim 1 , wherein the first nozzle is disposed in a plural number along a longitudinal direction of the fuselage.

3. The aircraft according to claim 1 , wherein the first nozzle is disposed to spray the first compressed air in a direction toward the main wing from the fuselage.

4. The aircraft according to claim 1 , wherein the plurality of second nozzles is disposed to spray the first compressed air to a rear side of the main wing.

5. The aircraft according to claim 1 , wherein the main control valve includes:

a first control valve configured to control the first pitching nozzle;

a second control valve configured to control the second pitching nozzle;

a third control valve configured to control the first rolling nozzle;

a fourth control valve configured to control the second rolling nozzle;

a fifth control valve configured to control the first yaw nozzle; and

a sixth control valve configured to control the second yaw nozzle.

6. The aircraft according to claim 1 , wherein the pressure of the first compressed air of the first tank meets a formula: Pb/Pa≥0.528, where Pb denotes an atmospheric pressure, and Pa denotes the pressure of the first compressed air of the first tank.

7. The aircraft according to claim 1 , wherein the first tank is disposed in the main wing.

8. The aircraft according to claim 1 ,

wherein the pressure of the second compressed air of the second tank is 10 bar or less and higher than the pressure of the first compressed air.

9. The aircraft according to claim 8 ,

wherein the pressure of the first compressed air is a threshold pressure according to a formula: Pb/Pa≥0.528.

10. The aircraft according to claim 1 ,

wherein the first pitching nozzle, second pitching nozzle, first rolling nozzle, second rolling nozzle, first yaw nozzle, and second yaw nozzle are configured to control an aircraft posture by spraying the first compressed air stored in the first tank in an emergency where an engine or a battery of the aircraft is incapable of providing energy.

11. The aircraft according to claim 1 ,

wherein the first nozzle is configured to spray the first compressed air from the roof of the fuselage and to allow the first compressed air to flow along a surface of the fuselage.

12. The aircraft according to claim 1 ,

wherein each of the plurality of second nozzles has a predetermined gap with an elongated shape configured to create a jet stream on the upper surface of the main wing.

13. The aircraft of claim 1 ,

wherein the aircraft further comprises an air compressor configured to compress air to store the air as the second compressed air in the second tank, and

wherein the air compressor is configured to be operated by power of an engine or an electric motor.

14. The aircraft of claim 13 ,

wherein the air compressed by the air compressor is dried.

15. The aircraft of claim 1 ,

wherein the aircraft is configured to selectively provide the first compressed air to one or more selected from the first nozzle, the plurality of second nozzles, first pitching nozzle, second pitching nozzle, first rolling nozzle, second rolling nozzle, first yaw nozzle, or second yaw nozzle.

16. The aircraft of claim 15 ,

wherein the aircraft is configured to control an aircraft posture in a transition flight in an emergency by selectively providing the first compressed air to one or more selected from the first pitching nozzle, second pitching nozzle, first rolling nozzle, second rolling nozzle, first yaw nozzle, or second yaw nozzle.

17. The aircraft of claim 1 ,

wherein the aircraft is configured to utilize the first compressed air in a short take-off or landing, vertical take-off or landing, and a transition flight.

18. The aircraft of claim 1 ,

wherein the main control valve is configured to operate in connection with a control stick of the aircraft.