| AMENDED CLAIMS received by the International Bureau on 08 April 2016 (08.04.2016) [Claim 1] An aircraft 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 first propulsion assembly, wherein said first propulsion assembly comprises a first tilting propulsion support including a first propulsion unit in a pusher configuration; at least a second propulsion assembly, wherein said second propulsion assembly comprises a second tilting propulsion support with a second propulsion unit in a pusher configuration; wherein said front wing and aft wing are in a tandem configuration, said front wing being placed higher than the aft wing; wherein said front wing is smaller than said aft wing; wherein said fuselage is at least partially located between said front wing and said aft wing; wherein said first propulsion assembly is attached to said front wing; wherein said second propulsion assembly is attached to said aft wing; and wherein said first propulsion assembly is displaced with respect to said second propulsion assembly. [Claim 2] An aircraft as in claim 1, wherein said front wing comprises a first central section and first outer sections, wherein said first outer sections are mechanically attached to said first central section. [Claim 3] An aircraft as in claim 2, wherein said first outer sections are detachable from said first central section. [Claim 4] An aircraft as in claim 2, wherein said first propulsion assembly is attached to the first central section. [Claim 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 first central section. [Claim 6] An aircraft as in claim 1, wherein said aft wing comprises a second central section and second outer sections, wherein said second outer sections are mechanically attached to said second central section. [Claim 7] An aircraft as in claim 6, wherein said second outer sections are de- tachable from said second central section. [Claim 8] An aircraft as in claim 6, wherein said second propulsion unit is attached to the second central section. [Claim 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 second central section. [Claim 10] An aircraft as in claim 1, wherein said front wing is vertically shifted a first distance from the aft wing with respect to the fuselage, wherein the propulsion unit is a propeller, wherein each propeller comprises a propeller radius. [Claim 11] An aircraft as in claim 10, wherein shifted distance between the front wing and the aft wing is at least the propeller radius. [Claim 12] An aircraft as in claim 1 comprising sensors, wherein said sensors are electrically coupled to the flight controller; and wherein said first propulsion assembly and said second propulsion assembly are electrically coupled to said flight controller. [Claim 13] An aircraft as in claim 1 wherein the front wing comprises at least a stabilizer. [Claim 14] An aircraft as in claim 1 wherein the aft wing comprises at least a stabilizer. [Claim 15] An aircraft 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 first pair of propulsion assemblies, wherein each propulsion assembly of said first pair of propulsion assemblies comprises a first tilting propulsion support including a first propulsion unit in a pusher configuration; at least a second pair of propulsion assemblies, wherein each propulsion assembly of said second pair of propulsion assemblies comprises a second tilting propulsion support with a second propulsion unit in a pusher configuration; wherein said front wing and aft wing are in a tandem configuration, said front wing being placed higher than the aft wing; wherein said front wing is smaller than said aft wing; wherein said fuselage is at least partially located between said front wing and said aft wing; wherein said first pair of propulsion assemblies is attached to said front wing; wherein said second pair of propulsion assemblies is attached to said aft wing; and wherein said first pair of propulsion assemblies is displaced with respect to said second pair of propulsion assemblies. [Claim 16] An aircraft as in claim 15, wherein the front wing comprises at least a first stabilizer; [Claim 17] An aircraft as in claim 15, wherein the aft wing comprises at least a second stabilizer. [Claim 18] An aircraft as in claim 15, wherein said front wing comprises a first central section and first outer sections, wherein said first outer sections are mechanically attached to said first central section. [Claim 19] An aircraft as in claim 18, wherein said first outer sections are detachable from said first central section. [Claim 20] An aircraft as in claim 18, wherein said first set of propulsion assembly is attached to said first central section. |
Title:
High Performance VTOL Aircraft
Document Type and Number:
WIPO Patent Application WO/2016/028358
Kind Code:
A4
Abstract:
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 preffered 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.
Inventors:
JUAN CRUZ AYOROA (US)
Application Number:
PCT/US2015/034069
Publication Date:
May 26, 2016
Filing Date:
June 03, 2015
Export Citation:
Assignee:
JUAN CRUZ AYOROA (US)
International Classes:
B64C29/00
Attorney, Agent or Firm:
TORRES OYOLA, Eugenio (221 Plaza Building5th floo, San Juan ., PR)
Download PDF:
Claims: