Hover and thrust control assembly for dual-mode aircraft

Patent metadata

Field	Value
Publication number	US-11518497-B2
Application number	US-202017001845-A
Country	US
Kind code	B2
Filing date	Aug 25, 2020
Priority date	Jul 15, 2020
Publication date	Dec 6, 2022
Grant date	Dec 6, 2022

Abstract

A three-dimensional directional control assembly for a dual-mode aircraft, wherein the aircraft is capable of vertical and forward thrust. The assembly comprising a support structure, wherein the support structure is coupled to a dual-mode aircraft. The assembly further comprises a control stick coupled to support structure, wherein the control stick having a length and radius is configured to be manipulated along a plurality of axes, wherein the manipulation of the control stick produces an electronic signal. The assembly further comprises a first interface device disposed on the control stick configured to receive an interaction and enable a thrust element to spin as a function of the interaction. The assembly further comprises a second interface device, wherein the second interface is configured to receive an interaction and disable the thrust element as a function of the interaction.

First claim

What is claimed is:

1. A three-dimensional directional control assembly for a dual-mode aircraft, wherein the aircraft is capable of vertical and forward thrust, the assembly comprising:
a support structure, wherein the support structure is coupled to a dual-mode aircraft;
a control stick coupled to the support structure, the control stick having 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, wherein the rotation is asymmetric;
a first interface device disposed on the control stick configured to:
receive an interaction; and
enable a thrust element as a function of the interaction; and

a second interface device, wherein the second interface is configured to:
receive an interaction; and
disable the thrust element as a function of the interaction.

2. The assembly of claim 1 , wherein the support structure comprises:
an armrest; and
a vibration dampening feature.

3. The assembly of claim 1 , wherein the structure is composed of an additively manufactured polymer material.

4. The assembly of claim 1 , wherein the control stick comprises a palm lever disposed on the control stick.

5. The assembly of claim 1 , wherein the electronic signal is measured by a plurality of sensors.

6. The assembly of claim 5 , wherein the plurality of sensors are configured to send the electronic signal to a processor.

7. The assembly of claim 5 , wherein the plurality of sensors includes a redundant sensor.

8. The assembly of claim 5 , wherein the processor is configured to manipulate the electronic signal, wherein the electronic signal can be used by a controller.

9. The assembly of claim 8 , wherein the controller is configured to:
receive the electronic signal from the processor; and
modify a system of the dual-mode aircraft based on the electronic signal.

10. The assembly of claim 9 , wherein modifying the system of the dual-mode aircraft comprises actuating a control surface of the dual-mode aircraft.

11. The assembly of claim 9 , wherein the at least an aircraft control interface device is reachable while the control stick is being manipulated.

12. The assembly of claim 9 , wherein the aircraft control interface device is configured to:
receive an interaction from the user; and
adjust an aircraft function as a function of the interaction from a user.

13. The assembly of claim 5 , wherein the plurality of sensors comprise a shielding configured to shield at least a portion of the plurality of sensors from electromagnetic interference.

14. The assembly of claim 13 , wherein adjusting the aircraft function further comprises:
adjusting an autopilot function as a function of the interaction from a user.

15. The assembly of claim 13 , wherein adjusting the aircraft function further comprises:
adjusting a radio function as a function of the interaction from a user.

16. The assembly of claim 1 , wherein the control stick further comprises:
at least an aircraft control interface device, wherein the aircraft control interface device is disposed on the control stick.

Assignees

• Beta Air Llc

Inventors

• Spiegel Cody
• Williams Dale

Classifications

• B64C13/503

  Fly-by-Wire · CPC title

• B64C13/0421 Primary

  control sticks for primary flight controls · CPC title

• B64D31/04 Primary

  actuated personally · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title