Aircraft with pusher propeller

Patent metadata

Field	Value
Publication number	US-12591245-B2
Application number	US-202418626202-A
Country	US
Kind code	B2
Filing date	Apr 3, 2024
Priority date	Feb 10, 2020
Publication date	Mar 31, 2026
Grant date	Mar 31, 2026

Abstract

Embodiments provide an electric aircraft with a plurality of lift fan assemblies that are configured to provide vertical lift, and one or more pusher propellers that are configured to provide forward thrust. The lift fan assemblies may be coupled to the wings of the aircraft via one or more support structures, and the wings may be coupled to an upper region of the fuselage. The pusher propeller(s) may be coupled to a tailing end of the fuselage. The lift fan assemblies and the pusher propeller(s) may provide thrust and movement in directions that are orthogonal to one another. A control system coupled to the aircraft may control the lift fan assemblies and the one or more pusher propellers to activate, increase in power, and decrease in power. The lift fan assemblies and the one or more pusher propellers may be operated separately, and may be active at different times.

First claim

What is claimed is:

1 . An aircraft comprising:
a fuselage; a pair of wings coupled to opposite sides of an upper portion of the fuselage; a plurality of lift fan assemblies coupled to the pair of wings, wherein the plurality of lift fan assemblies are configured to create a vertical lift, the plurality of lift fan assemblies including:
a first subset of lift fan assemblies configured to spin in a first direction; and
a second subset of lift fan assemblies configured to spin in a second direction that is opposite the first direction; and
a control system configured to control the plurality of lift fan assemblies to create rotational movement about a vertical axis of the aircraft while maintaining vertical lift by at least one of:
controlling the first subset of lift fan assemblies to decrease a first spin rotational rate of the first subset of lift fan assemblies; and
controlling the second subset of lift fan assemblies to increase a second spin rotational rate of the second subset of lift fan assemblies.

2 . The aircraft of claim 1 , wherein the first subset of lift fan assemblies are configured to create a first angular momentum in the first direction during operation, the second subset of lift fan assemblies are configured to create a second angular momentum in the second direction during operation, and the first angular momentum cancels out the second angular momentum when the first spin rotational rate matches the second spin rotational rate.

3 . The aircraft of claim 1 , wherein the first subset of lift fan assemblies are configured to create a first angular momentum in the first direction during operation, the second subset of lift fan assemblies are configured to create a second angular momentum in the second direction during operation, and the second angular momentum is greater than the first angular momentum when the second spin rotational rate is greater than the second spin rotational rate, thereby causing a net angular momentum in the second direction.

4 . The aircraft of claim 1 , wherein each of the first subset of lift fan assemblies include first rotor blades configured to have a first angle of attack, and each of the second subset of lift fan assemblies include second rotor blades configured to have a second angle of attack that is opposite the first angle of attack.

5 . The aircraft of claim 1 , further comprising:
one or more pusher propellers coupled to a tail end of the fuselage, wherein the one or more pusher propellers are configured to create a forward thrust.

6 . The aircraft of claim 5 , wherein the plurality of lift fan assemblies and the one or more pusher propellers are configured so that the vertical lift is directionally orthogonal to the forward thrust, the one or more pusher propellers are configured to create both forward thrust and reverse thrust.

7 . The aircraft of claim 5 , wherein the control system is further configured to control the plurality of lift fan assemblies and the one or more pusher propellers independently from one another, and to activate or deactivate the plurality of lift fan assemblies or the one or more pusher propellers based on one or more of flight instructions, flight data received from sensors coupled to the aircraft, or a signal received from a remote entity.

8 . The aircraft of claim 1 , wherein the fuselage includes a cabin configured for passengers or cargo, each of the plurality of lift fan assemblies include rotor blades that are each configured to rotate within a rotational plane that is positioned above the cabin without intersecting the cabin.

9 . The aircraft of claim 1 , wherein the fuselage includes a cabin configured for passengers or cargo, and further comprising:
a horizontal stabilizer in a form of a V-tail coupled to a rear end of the fuselage, the V-tail including a first stabilizer surface protruding at a first angle and a second stabilizer surface protruding at a second angle opposite the first angle.

10 . The aircraft of claim 1 , further comprising:
a plurality of support structures coupled to an underside of the pair of wings, each support structure having a forward end extending forward of the pair of wings and an aft end extending aft of the pair of wings, and wherein each of the plurality of support structures are identical and interchangeable between positions on the pair of wings.

11 . The aircraft of claim 10 , wherein a pair lift fan assemblies among the plurality of lift fan assemblies are coupled to opposite ends of at least one of the plurality of support structures.

12 . The aircraft of claim 1 , further comprising:
a plurality of battery units each including a plurality of battery cells configured to power at least the plurality of lift fan assemblies, wherein each of the plurality of lift fan assemblies are coupled to a respective dedicated battery unit of the plurality of battery units.

13 . The aircraft of claim 1 , wherein each of the plurality of lift fan assemblies comprise an electric motor-driven rotor, wherein at least six lift fan assemblies are coupled to each of the pair of wings, and wherein the pair of wings include winglets.

14 . A method, comprising:
receiving, by a control system coupled to an aircraft, a flight instruction to takeoff; activating, by the control system, a plurality of lift fan assemblies coupled to the aircraft, wherein the plurality of lift fan assemblies are configured to create a vertical lift for vertical takeoff and landing; controlling, by the control system, the plurality of lift fan assemblies to create vertical lift so that the aircraft departs vertically from a stationary position on a ground surface; controlling, by the control system, the plurality of lift fan assemblies to create rotational movement about a vertical axis of the aircraft while maintaining vertical lift by at least one of:
decreasing a first spin rotational rate of a first subset of the plurality of lift fan assemblies, the first subset spinning in a first direction; and
increasing a second spin rotational rate of a second subset of the plurality of lift fan assemblies, the second subset spinning in a second direction; and
after a predetermined amount of forward velocity is gained, deactivating or reducing power provided to, by the control system, the plurality of lift fan assemblies.

15 . The method of claim 14 , comprising:
controlling, by the control system, the plurality of lift fan assemblies to stop creating the rotational movement about the vertical axis of the aircraft while maintaining vertical lift by controlling the first spin rotational rate of the first subset of the plurality of lift fan assemblies to be equal the second spin rotational rate of the second subset of the plurality of lift fan assemblies.

16 . The method of claim 14 , wherein the first subset of the plurality of lift fan assemblies create a first angular momentum in the first direction during operation, the second subset of the plurality of lift fan assemblies create a second angular momentum in the second direction during operation, and the second angular momentum is greater than the first angular momentum when the second spin rotational rate is greater than the second spin rotational rate, thereby causing a net angular momentum in the second direction.

17 . The method of claim 14 , wherein each of the first subset of the plurality of lift fan assemblies include first rotor blades configured to have a first angle of attack, and each of the second subset of the plurality of lift fan assemblies include second rotor blades configured to have

Assignees

• Wisk Aero Llc

Inventors

• Tighe James Joseph
• Tzarnotzky Uri
• Long Geoffrey Alan

Classifications

• B64D27/24

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

• B64D31/16

  for electric power plants · CPC title

• G05D1/652

  Take-off (delivering or retrieving payloads G05D1/667) · CPC title

• B60L50/50

  using propulsion power supplied by batteries or fuel cells · CPC title

• B64C11/00

  Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft · CPC title