Hover and thrust control assembly for dual-mode aircraft

Patent metadata

Field	Value
Publication number	US-12246821-B2
Application number	US-202217972830-A
Country	US
Kind code	B2
Filing date	Oct 25, 2022
Priority date	Jul 15, 2020
Publication date	Mar 11, 2025
Grant date	Mar 11, 2025

Abstract

A hover and thrust control assembly for dual-mode aircraft including a plurality of flight components mechanically coupled to an aircraft includes a support structure attached to an aircraft frame of an aircraft having a control stick coupled to the support structure. The control stick may include a length and radius and configured to be manipulated along a plurality of axes, wherein the manipulation of the control stick produces an electronic signal, wherein the control stick is further configured to be manipulated rotationally about the length of the control stick. A first interface device disposed on the control stick may be configured to receive an interaction and adjust a lift of the dual-mode aircraft as a function of the interaction. A second interface device may be configured to receive an interaction and adjust the lift of the dual-mode aircraft as a function of the interaction.

First claim

What is claimed is:

1. A three-dimensional control assembly for an electric aircraft, the three-dimensional control assembly comprising:
an aircraft frame;
a support structure coupled to the aircraft frame; and
a control stick coupled to the support structure and having:
a length and a radius, wherein the control stick is configured to be manipulated:
along a first axis to control a pitch of the electric aircraft;
along a second axis perpendicular to the first axis to control a roll of the electric aircraft; and
rotationally about the length of the control stick to control a yaw of the electric aircraft, wherein the control stick is further configured such that rotation about the length of the control stick in a first direction changes a yaw of the electric aircraft in the first direction, and rotation about the length of the control stick in a second direction changes a yaw of the electric aircraft in the second direction; and
a linear thrust control disposed adjacent an end of the control stick and including:
a thumbwheel configured to control at least a forward thrust propulsor of the electric aircraft; and
a resistance mechanism configured to change a resistance against movement of the linear thrust control based on a rotational position of the control stick.

2. The three-dimensional control assembly of claim 1 , wherein the control stick is further configured such that:
a degree of rotation of the control stick about the length of the control stick in a first direction is configured to correspond to a magnitude of change of the yaw of the electric aircraft in the first direction, and
a degree magnitude of rotation of the control stick about the length of the control stick in a second direction is configured to correspond to a magnitude of change of the yaw of the electric aircraft in the second direction.

3. The three-dimensional control assembly of claim 2 , wherein the control stick is further configured such that rotation of the control stick in the first direction corresponds to a greater magnitude of change of the yaw of the electric aircraft compared to when the control stick is rotated in the second direction by an equivalent amount.

4. The three-dimensional control assembly of claim 1 further comprising at least one vertical thrust propulsor.

5. The three-dimensional control assembly of claim 4 further comprising a throttle lever rotatably mounted to the support structure, wherein rotating the throttle lever in a first direction increases power to the at least one vertical thrust propulsor, and rotating the throttle lever in a second direction decreases power to the at least one vertical thrust propulsor.

6. The three-dimensional control assembly of claim 5 further comprising at least one forward thrust propulsor and a thrust control mounted on the throttle lever, wherein movement of the thrust control in a first direction increases forward thrust of the at least a forward thrust propulsor, and movement of the thrust control in a second direction decreases forward thrust of the at least one forward thrust propulsor.

7. The three-dimensional control assembly of claim 6 , wherein the thrust control includes a neutral position wherein forward thrust generated by the at least one forward thrust propulsor is zero.

8. The three-dimensional control assembly of claim 7 , wherein rotating the thrust control in a second direction relative to the neutral position causes the at least one forward thrust propulsor to generate a negative forward thrust.

9. The three-dimensional control assembly of claim 4 , wherein vertical thrust generated by the at least one vertical thrust propulsor is configured to be increased and decrease in response to the manipulation of the control stick.

10. The three-dimensional control assembly of claim 9 , wherein the at least one vertical thrust propulsor includes a plurality of vertical thrust propulsors, wherein pitch, roll, and yaw of the electric aircraft is configured to be controlled by a differential in thrust produced by each of the vertical thrust propulsors.

11. The three-dimensional control assembly of claim 1 further comprising at least one control surface, wherein pitch, roll, and yaw of the electric aircraft is configured to be controlled by the at least one control surface.

12. A three-dimensional control device for an electric aircraft capable of vertical and forward thrust, the three-dimensional control device comprising:
a support structure configured to be coupled to a frame of the electric aircraft; and
a control stick coupled to the support structure and having a length and a radius, wherein the control stick is configured to be manipulated:
along a first axis to control pitch of the electric aircraft;
along a second axis perpendicular to the first axis to control roll of the electric aircraft; and
rotationally about the length of the control stick to control a yaw of the electric aircraft, wherein the control stick is further configured such that rotation about the length of the control stick in a first direction changes the yaw of the electric aircraft in the first direction, and rotation about the length of the control stick in a second direction changes the yaw of the electric aircraft in the second direction; and

a linear thrust control disposed adjacent an end of the control stick and including:
a thumbwheel configured to control at least a forward thrust propulsor of the electric aircraft; and
a resistance mechanism configured to change a resistance against movement of the linear thrust control based on a rotational position of the control stick.

13. The three-dimensional control device of claim 12 , wherein the control stick is further configured such that:
a first degree of rotation of the control stick about the length of the control stick in a first direction is configured to correspond to a first magnitude of change of the yaw of the electric aircraft in the first direction, and
a second degree magnitude of rotation of the control stick about the length of the control stick in a second direction is configured to correspond to a second magnitude of change of the yaw of the electric aircraft in the second direction.

14. The three-dimensional control device of claim 13 , wherein the control stick is further configured such that rotation of the control stick in the first direction corresponds to a greater magnitude of change of the yaw of the electric aircraft compared to when the control stick is rotated in the second direction by an equivalent amount.

15. A three-dimensional control assembly for an electric aircraft capable of vertical and forward thrust, the three-dimensional control assembly comprising:
an aircraft frame;
a plurality of vertical thrust propulsors;
a support structure coupled to the aircraft frame; and
a control stick coupled to the support structure and including a length and a radius and is configured to be manipulated:
along a first axis to control pitch of the electric aircraft;
along a second axis perpendicular to the first axis to control roll of the electric aircraft; and
rotationally about the length of the control stick to control yaw of the electric aircraft, wherein a vertical thrust generated by each vertical thrust propulsor is increased and decreased in response to the manipulation of the control stick; and
wherein the control stick includes a linear thrust control disposed adjacent an end of the control stick and including:
a thumbwheel configured to control at least a forward thrust propulsor of the electric aircraft; and
a resistance mechanism configured to change a resistance agains

Assignees

• Beta Air Llc

Inventors

• Spiegel Cody
• Williams Dale

Classifications

• B64C13/503

  Fly-by-Wire · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C13/505

  having duplication or stand-by provisions · CPC title

• B64C13/0421 Primary

  control sticks for primary flight controls · CPC title