Login| Sign Up| Help| Contact|

Patent Searching and Data


Title:
PERSONAL FLIGHT APPARATUS WITH VERTICAL TAKE-OFF AND LANDING
Document Type and Number:
WIPO Patent Application WO/2019/203673
Kind Code:
A4
Abstract:
A personal flight apparatus with vertical take-off and landing conceived as a biplane apparatus constituted by two distinct parts articulated there between, the first distinct part consisting of the cockpit (1), which is hinged to the second part of the latter, which is formed of the wings assembly (6),the cockpit 1 being attached to the wings assembly (6) by two hinges (3) fixed in the upright central vertical supports (7) of the wings, and in this way the cockpit having a limited swing possibility inside of the wings support structure which in turn they are provided with four propellers (9), of ducted type and driven by electric engines (20) disposed two on the top wing and two on the bottom wing, thus forming a kind of quadcopter, the duct (10) of each propeller being provided on the inlet lip with an annular ejection slit (11), and the electrical energy required to operate the apparatus is provided by the batteries (14) placed under the pilot's seat which through the speed regulators transmit the electric energy to the engines, the entire operation of the apparatus being managed by means of a flight computer (17) disposed in the central part of the upper wing of the biplane, and the taking off being made with the wings and the engines vertically oriented, the flight apparatus being laid on the ground by means of a landing gear (15) fixed in the wing extremities, the flight apparatus taking off as a quadcopter, and the transition to the cruise flight is made by reducing the angle of incidence of the wings, this angle decreasing naturally due to the increased resistance to advancement of the wings concurrently with the speed of translation of the flight apparatus, and in the meantime the cockpit (1) remains in a vertical position due to its lower center of gravity and due to the joints (3) which allow it to rotate relative to the wings assembly (6) and the landing is made similarly to a quadcopter, slowing down the speed leading to increasing the incidence angle of the wings until they return to the vertical plane required for landing.

Inventors:
SABIE RAZVAN (RO)
Application Number:
RO2019/000011
Publication Date:
December 19, 2019
Filing Date:
April 11, 2019
Export Citation:
Click for automatic bibliography generation   Help
Assignee:
SABIE RAZVAN (RO)
International Classes:
B64C29/00; B64C9/14; B64C21/04; B64C39/00; B64C39/08; B64C11/00
Attorney, Agent or Firm:
CABINET D. NICOLAESCU (RO)
Download PDF:
Claims:
AMENDED CLAIMS

received by the International Bureau on 18 November 2019 (18.11.2019)

Claim 1. Flight apparatus with vertical take-off and landing characterized in that it is a biplane apparatus constituted by two distinct parts articulated there between, the first distinct part consisting of the cockpit (1 ) and being hinged to the second distinct part which is formed of a wings assembly (6), the cockpit (1 ) being attached to the wings assembly (6) by two hinges (3) fixed in the upright central vertical supports (7) of the wings and, in this way, the cockpit has a limited swing possibility inside of the wings support structure, wings which, in their turn, are provided with four propellers <9), of ducted or non-ducted type and driven by electric engines (20) disposed two on the top wing and two on the bottom wing, thus forming a kind of quadcopter, the duct (10) of each propeller being or not provided on the inlet lip with an annular ejection slit (11 ), and the electrical energy required to operate the apparatus is provided by the batteries (14), placed under the pilot's seat, batteries which, through the speed regulators, transmit the electric energy to the engines, the entire operation of the apparatus being managed by means of a flight computer (17) disposed in the central part of the upper wing of the biplane, and the taking-off being made with the wings and the engines vertically oriented, the flight apparatus being laid on the ground by means of a landing gear (15) fixed in the wing extremities, the flight apparatus taking off as a quadcopter and, the transition to the cruise flight is made by reducing the angle of incidence of the wings, this angle decreasing naturally due to the increased resistance to advancement of the wings, concurrently with the speed of translation of the flight apparatus and, in the meantime, the cockpit (1 ) remains in a vertical position due to its lower center of gravity and due to the joints (3) which allow it to rotate relative to the wings assembly (6) and the landing is made similarly to a quadcopter, slowing down the speed leading to increasing the incidence angle of the wings until they return to the vertical plane required for landing.

Claim 2 Flight apparatus with vertical take-off and landing according to claim 1 , characterized in that the propellers (9) are double ducted and the duct (10) and the duct (35) are provided with ejection slits (11 ) and (37) respectively, thereby forming a double-flow ducted propeller, and the outside of the first duct together with the inner side of the second duct forme an annular Coanda ejector.

Claim 3. Flight apparatus with vertical take-off and landing according to claims 1 and 2, characterized in that the duct (10) and the duct (35) are provided in the rear side with ejection slits (38) and (39) respectively. Claim 4. Flight apparatus according to claims 1 and 2, characterized in that the anterior part of the duct (10) is provided with an annular chamber (24 from which the compressed air is ejected through the slit (11 ) and the shaft of the electric motor (20) drives directly or via a speed multiplier an air compressor 22 which provides compressed air through pipes (23) to annular chamber (24),

Claim 5. Flight apparatus according to 1 and 2, characterized in that the ducted propeller (9) is provided with a second duct (35) and the inner part of the duct (35) together with the exterior part of the duct (10) forms an annular ejector of the Coanda type, and both ducts (10) and (35) have in the rear part ejection slits (38) and (39), respectively,.

Claim 6. Flight apparatus according to claims 1 to 5 characterized in that that the wings are provided with four triple flow jet engines that are made up of a classic double flow turbofan having a duct (10) which is provided with the ejection slit (11 ) and the whole assembly is surrounded by a second duct (35), having an ejection slit (37) and the inner part of the duct (35), together with the outer part of the duct (10), forms an annular Coanda ejector and the compressed air required for the operation of the entire ejection system is supplied through the pipes (23) from a stage of the turbofan's compressor (41 ), said engines being disposed two on the top wing and two on the bottom wing, thus forming a kind of quadcopter, the entire operation of the apparatus being managed by means of a flight computer (17) disposed in the central part of the upper wing of the biplane, and the taking-off being made with the wings and the engines vertically oriented, the flight apparatus being laid on the ground by means of a landing gear (15) fixed in the wing extremities, the flight apparatus taking off as a quadcopter and, the transition to the cruise flight is made by reducing the angle of incidence of the wings, this angle decreasing naturally due to the increased resistance to advancement of the wings, concurrently with the speed of translation of the flight apparatus and, in the meantime, the cockpit (1 ) remains in a vertical position due to its lower center of gravity and due to the joints (3) which allow it to rotate relative to the wings assembly (6) and the landing , is made similarly to a quadcopter, slowing down the speed leading to increasing the incidence angle of the wings until they return to the vertical plane required for landing.