Aerial vehicle

Patent metadata

Field	Value
Publication number	US-2018354613-A1
Application number	US-201815994433-A
Country	US
Kind code	A1
Filing date	May 31, 2018
Priority date	Jun 8, 2017
Publication date	Dec 13, 2018
Grant date	—

Abstract

An aerial vehicle includes a fuselage defining a longitudinal axis, a closed wing structure with a pair of lower wings coupled to the fuselage, an upper wing device, and a pair of connector wings connecting the pair of lower wings and the upper wing device. The aerial vehicle further includes a pair of front propulsion devices coupled to the fuselage, and a pair of rear propulsion devices pivotally coupled to the fuselage, wherein the pair of rear propulsion devices is arranged between the pair of lower wings and the upper wing device, and wherein the pair of rear propulsion devices is pivotal between a take-off position and a cruise position.

First claim

1 . An aerial vehicle, comprising:
a fuselage defining a longitudinal axis of the aerial vehicle; a closed wing structure coupled to the fuselage and comprising a pair of lower wings coupled to the fuselage, an upper wing device spaced to the pair of lower wings with respect to the longitudinal axis and with respect to a vertical direction extending transverse to the longitudinal axis, and a vertical joint structure including first and second connector wings connecting the pair of lower wings and the upper wing device; a pair of front propulsion devices coupled to the fuselage, wherein the pair of front propulsion devices comprises a direction of thrust which is oriented substantially along the vertical direction; and a pair of rear propulsion devices being pivotally coupled to the fuselage, wherein the pair of rear propulsion devices is arranged between the pair of lower wings and the upper wing device with respect to the vertical direction and with respect to the longitudinal axis, and wherein the pair of rear propulsion devices is pivotal between a take-off position, in which a direction of thrust of the pair of rear propulsion devices is oriented substantially along the vertical direction, and a cruise position, in which the direction of thrust of the pair of rear propulsion devices is oriented substantially along the longitudinal axis.

2 . The aerial vehicle according to claim 1 , further comprising a pair of canard wings coupled to the fuselage, wherein the pair of front propulsion devices are arranged adjacent to the pair of canard wings with respect to the longitudinal axis.

3 . The aerial vehicle according to claim 2 , wherein the pair of canard wings is pivotally mounted to the fuselage.

4 . The aerial vehicle according to claim 1 , further comprising a vertical stabilizer which extends substantially along the vertical direction and couples the upper wing device of the closed wing structure to the fuselage.

5 . The aerial vehicle according to claim 4 , wherein the upper wing device comprises a first upper wing and a second upper wing, wherein the first upper wing extends between the vertical stabilizer and the first connector wing, and wherein the second upper wing extends between the vertical stabilizer and the second connector wing.

6 . The aerial vehicle according to claim 1 , further comprising a skid device mounted to a lower side of the fuselage.

7 . The aerial vehicle according to claim 1 , wherein the front propulsion devices are shrouded propellers.

8 . The aerial vehicle according to claim 7 , wherein the shrouded propellers comprise a ring shaped shroud which comprises a cross-sectional shape configured to generate a force comprising a vector component along the longitudinal axis when air is drawn through the ring shaped shroud by the propeller.

9 . The aerial vehicle according claim 7 , wherein the front propulsion devices and/or the rear propulsion devices comprise a first propeller which is configured to rotate in a first rotation direction and a second propeller which is configured to rotate in a second rotation direction contrary to the first rotation direction. 15

10 . The aerial vehicle according to claim 1 , wherein the rear propulsion devices are shrouded propellers.

11 . The aerial vehicle according to claim 10 , wherein the shrouded propellers comprise a ring shaped shroud which comprises a cross-sectional shape configured to generate a force comprising a vector component substantially along the vertical direction in case air is drawn through the ring shaped shroud by the propeller and in case the pair of rear propulsion devices is in its cruise position.

12 . The aerial vehicle according to claim 1 , further comprising an electrical energy storage device, wherein the front propulsion devices and/or the rear propulsion devices comprise an electrically drivable motor, respectively, electrically connected to the electrical energy storage device.

13 . The aerial vehicle according to claim 12 , further comprising a charging system for charging electrical energy storage device, wherein the charging system comprises an internal combustion engine driving an electric generator which is electrically connected to the electrical energy storage device.

14 . The aerial vehicle according to claim 1 , further comprising one or more deployable parachutes.

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Cvrlje Tom

Classifications

• B64D17/80

  in association with aircraft, e.g. for braking thereof · CPC title

• B64C5/02

  Tailplanes · CPC title

• B64C29/0016 Primary

  the lift during taking-off being created by free or ducted propellers or by blowers · CPC title

• B64C25/52

  Skis or runners · CPC title

• B64D27/24

  using steam or spring force (jet aircraft B64D27/16) · CPC title