The present disclosure relates to a high performance Vertical Takeoff and Landing (VTOL) aircraft for executing hovering flight, forward flight, and transitioning between the two in a stable and efficient manner. The VTOL aircraft provides a highly stable, controllable and efficient VTOL aircraft. T
The present disclosure relates to a high performance Vertical Takeoff and Landing (VTOL) aircraft for executing hovering flight, forward flight, and transitioning between the two in a stable and efficient manner. The VTOL aircraft provides a highly stable, controllable and efficient VTOL aircraft. The preferred comprises: (1) a pusher propeller configuration with strategic placement which maximizes the effective use of thrust, (2) four propellers which allow for the highly-controllable and mechanically simple control methods used in multirotor aircraft, (3) electric motors which create mechanically simple, lightweight and reliable operation, (4) and a tandem wing configuration which is stable, controllable and efficient in both hovering and forward flight. The VTOL aircraft is capable of full runway, short runway or vertical takeoffs or landings, having unobstructed forward view for camera and sensor placement; and providing a compact, mechanically simple and low-maintenance VTOL aircraft design.
대표청구항▼
1. An aircraft for executing hovering flight, forward flight, and transitioning between the two comprising in combination, a front wing,an aft wing,at least a fuselage,at least a landing gear,at least one flight controller,at least a front propulsion assembly, wherein said front propulsion assembly
1. An aircraft for executing hovering flight, forward flight, and transitioning between the two comprising in combination, a front wing,an aft wing,at least a fuselage,at least a landing gear,at least one flight controller,at least a front propulsion assembly, wherein said front propulsion assembly comprises a front tilting propulsion support including a front propulsion unit in a continuous pusher configuration;at least an aft propulsion assembly, wherein said aft propulsion assembly comprises an aft tilting propulsion support with an aft propulsion unit in a continuous pusher configuration;wherein said front wing and aft wing are in a tandem configuration;wherein said fuselage is at least partially located between said front wing and said aft wing;wherein said front propulsion assembly is attached to said front wing, shifted longitudinally backwards relative to the aerodynamic center of said front wing;wherein said aft propulsion assembly is attached to said aft wing, shifted longitudinally backwards relative to the aerodynamic center of said aft wing;wherein a thrust center determined by the location of said front propulsion unit and said aft propulsion unit is aligned on a vertical axis with the center of gravity of the aircraft during hover flight;wherein an aerodynamic center determined by the location and size of both said front wing and said aft wing is located at or behind the center of gravity of the aircraft on a longitudinal axis during forward flight; andwherein said aft wing is larger relative to said front wing. 2. An aircraft as in claim 1, wherein said front wing comprises a front central section and front outer sections, wherein said front outer sections are mechanically attached to said front central section. 3. An aircraft as in claim 2, wherein said front outer sections are detachable from said front central section. 4. An aircraft as in claim 2, wherein said front propulsion assembly is attached to the front central section. 5. An aircraft as in claim 4, wherein said front wing comprises at least a third propulsion assembly, said third propulsion assembly coupled to said front central section. 6. An aircraft as in claim 1, wherein said aft wing comprises a aft central section and aft outer sections, wherein said aft outer sections are mechanically attached to said aft central section. 7. An aircraft as in claim 6, wherein said aft outer sections are detachable from said aft central section. 8. An aircraft as in claim 6, wherein said aft propulsion unit is attached to the aft central section. 9. An aircraft as in claim 8, wherein said aft wing comprises at least a fourth propulsion assembly, said fourth propulsion assembly is attached to said aft central section. 10. An aircraft as in claim 1, wherein said front wing is vertically shifted a front distance from the aft wing with respect to the fuselage, wherein the propulsion unit comprises a propeller, wherein each propeller comprises a propeller radius. 11. An aircraft as in claim 10, wherein vertically shifted distance between the front wing and the aft wing is at least the propeller radius. 12. An aircraft as in claim 1 comprising sensors, wherein said sensors are electrically coupled to the flight controller; and wherein said front propulsion assembly and said aft propulsion assembly are electrically coupled to said flight controller. 13. An aircraft as in claim 1 wherein the front wing comprises at least a stabilizer. 14. An aircraft as in claim 1 wherein the aft wing comprises at least a stabilizer. 15. An aircraft for executing hovering flight, forward flight, and transitioning between the two comprising in combination, a front wing,a aft wing,at least a fuselage,at least a landing gear,at least one flight controller,at least a front pair of propulsion assemblies, wherein each propulsion assembly of said front pair of propulsion assemblies comprises a front tilting propulsion support including a front propulsion unit in a continuous pusher configuration;at least an aft pair of propulsion assemblies, wherein each propulsion assembly of said aft pair of propulsion assemblies comprises an aft tilting propulsion support with an aft propulsion unit in a continuous pusher configuration;wherein said front wing and aft wing are in a tandem configuration;wherein said fuselage is at least partially located between said front wing and said aft wing;wherein said front pair of propulsion assemblies is attached to said front wing, shifted longitudinally backwards relative to the aerodynamic center of said front wing;wherein said aft pair of propulsion assemblies is attached to said aft wing, shifted longitudinally backwards relative to the aerodynamic center of said aft wing;wherein a thrust center determined by the location of said front propulsion unit and said aft propulsion unit is aligned on a vertical axis with the center of gravity of the aircraft during hover flight;wherein an aerodynamic center determined by the location and size of both said front wing and said aft wing is located at or behind the center of gravity of the aircraft on a longitudinal axis during forward flight, andwherein said aft wing is larger relative to said front wing. 16. An aircraft as in claim 15, wherein the front wing comprises at least a front stabilizer. 17. An aircraft as in claim 15, wherein the aft wing comprises at least a aft stabilizer. 18. An aircraft as in claim 15, wherein said front wing comprises a front central section and front outer sections, wherein said front outer sections are mechanically attached to said front central section. 19. An aircraft as in claim 18, wherein said front outer sections are detachable from said front central section. 20. An aircraft as in claim 18, wherein said front set of propulsion assembly is attached to said front central section.
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