Hover-capable aircraft

Patent metadata

Field	Value
Publication number	US-12269586-B2
Application number	US-201917252502-A
Country	US
Kind code	B2
Filing date	Jun 14, 2019
Priority date	Jun 15, 2018
Publication date	Apr 8, 2025
Grant date	Apr 8, 2025

Abstract

A hover-capable aircraft includes a body including a tubular strut, a first rotor assembly rotatably coupled to the body and positioned about the strut, wherein the first rotor assembly includes a first plurality of circumferentially-spaced blades, a first actuation assembly including a first plurality of electronically controlled actuators coupled to a first swashplate and configured to control the movement of the first swashplate relative to the body, and a control system coupled to the body and configured to control the first plurality of actuators, wherein the control system includes a cable extending through a passage formed in the tubular strut and in signal communication with the first plurality of actuators.

First claim

What is claimed is:

1. A hover-capable aircraft, comprising:
a body;
a first rotor assembly rotatably coupled to the body, wherein the first rotor assembly includes a first plurality of circumferentially-spaced blades and is configured to rotate about a rotational axis in a first rotational direction; and
a second rotor assembly rotatably coupled to the body, wherein the second rotor assembly includes a second plurality of circumferentially-spaced blades and is configured to rotate about the rotational axis in a second rotational direction opposite the first rotational direction;
wherein each blade of at least one of the first plurality of blades and the second plurality of blades comprises a root, a forward swept section extending directly from the root, and a rearward swept section.

2. The aircraft of claim 1 , wherein:
each blade of the first plurality of blades and the second plurality of blades comprises a location of sweep reversal positioned between the forward swept section and the rearward swept section; and
the forward swept section of each blade of the first plurality of blades and the second plurality of blades has a greater length than the rearward swept section.

3. The aircraft of claim 1 , wherein the forward swept section of each blade of the first plurality of blades and the second plurality of blades has a central axis that is angled from 3 degrees to 7 degrees from a central axis of the blade in a first angular direction, and the rearward swept section of each blade of the first plurality of blades and the second plurality of blades has a central axis that is angled from 18 degrees to 22 degrees from the central axis of the blade in a second angular direction opposite the first angular direction.

4. The aircraft of claim 1 , further comprising a first actuation assembly comprising a first plurality of electronically controlled actuators coupled to an inner swashplate positioned in an outer swashplate, and wherein the first plurality of actuators are configured to control the movement of the inner swashplate relative to the body.

5. The aircraft of claim 4 , wherein:
the inner swashplate and the outer swashplate are coupled to a cylindrical strut of the body;
the outer swashplate comprises a rotating swashplate that is rotationally locked to the first plurality of blades; and
the inner swashplate comprises a nonrotating swashplate configured to rotate relative to the outer swashplate about a central axis of the strut.

6. The aircraft of claim 5 , further comprising a spherical bearing positioned radially between the inner swashplate and the strut.

7. The aircraft of claim 4 , further comprising a control system coupled to the body and configured to independently control the first plurality of actuators.

8. A hover-capable aircraft, comprising:
a body;
a first rotor assembly positioned along a rotational axis and rotatably coupled to the body, wherein the first rotor assembly includes a first plurality of circumferentially-spaced blades and is configured to rotate about the rotational axis; and
a second rotor assembly positioned along the rotational axis at a position spaced from the first rotor assembly and rotatably coupled to the body, wherein the second rotor assembly includes a second plurality of circumferentially-spaced blades and is configured to rotate about the rotational axis;
wherein each blade of at least one of the first plurality of blades and the second plurality of blades comprises a root extending between a radially inner end defining a radially inner end of the blade and a radially outer end, a forward swept section having a radially inner end located directly adjacent the radially outer end of the root, and a rearward swept section.

9. The aircraft of claim 8 , wherein the root of has a root cutout.

10. The aircraft of claim 8 , wherein:
each blade of the first plurality of blades and the second plurality of blades comprises a location of sweep reversal positioned between the forward swept section and the rearward swept section; and
the forward swept section of each blade of the first plurality of blades and the second plurality of blades has a greater length than the rearward swept section.

11. The aircraft of claim 8 , wherein the forward swept section of each blade of the first plurality of blades and the second plurality of blades has a central axis that is angled from 3 degrees to 7 degrees from a central axis of the blade in a first angular direction, and the rearward swept section of each blade of the first plurality of blades and the second plurality of blades has a central axis that is angled from 18 degrees to 22 degrees from the central axis of the blade in a second angular direction opposite the first angular direction.

12. A hover-capable aircraft, comprising:
a body;
a first rotor assembly rotatably coupled to the body, wherein the first rotor assembly includes a first plurality of circumferentially-spaced blades and is configured to rotate about a rotational axis in a first rotational direction; and
a second rotor assembly rotatably coupled to the body, wherein the second rotor assembly includes a second plurality of circumferentially-spaced blades and is configured to rotate about the rotational axis in a second rotational direction opposite the first rotational direction;
wherein each blade of at least one of the first plurality of blades and the second plurality of blades comprises a forward swept section directly extending from a radially inner end of the blade, and a rearward swept section.

13. The aircraft of claim 12 , wherein the forward swept section extends from the radially inner end of the blade to a location of sweep reversal between the forward swept section and the rearward swept section.

14. The aircraft of claim 13 , wherein the rearward swept section extends from the location of sweep reversal to a radially outer end of the blade.

15. The aircraft of claim 13 , wherein the rearward swept section extends from a location of sweep reversal between the forward swept section and the rearward swept section.

16. The aircraft of claim 12 , wherein:
each blade of the first plurality of blades and the second plurality of blades comprises a location of sweep reversal positioned between the forward swept section and the rearward swept section; and
the forward swept section of each blade of the first plurality of blades and the second plurality of blades has a greater length than the rearward swept section.

17. The aircraft of claim 12 , wherein the forward swept section of each blade of the first plurality of blades and the second plurality of blades has a central axis that is angled from 3 degrees to 7 degrees from a central axis of the blade in a first angular direction, and the rearward swept section of each blade of the first plurality of blades and the second plurality of blades has a central axis that is angled from 18 degrees to 22 degrees from the central axis of the blade in a second angular direction opposite the first angular direction.

Assignees

• Texas A & M Univ Sys

Inventors

• BENEDICT Moble
• Coleman David
• Halder Atanu
• Lee Bochan
• Riha Andrew
• Saemi Farid
• Runco Carl
• Subramanian Vishaal
• Greenwood Eric
• Lakshminarayan Vinod

Classifications

• B64D27/34

  All-electric aircraft · CPC title

• B64D31/16

  for electric power plants · CPC title

• B64D27/357

  using batteries · CPC title

• B64C27/68 Primary

  using electrical energy, e.g. having electrical power amplification · CPC title

• B64D17/80 Primary

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