Self-tightening rotor

Patent metadata

Field	Value
Publication number	US-10196138-B2
Application number	US-201715494251-A
Country	US
Kind code	B2
Filing date	Apr 21, 2017
Priority date	May 31, 2013
Publication date	Feb 5, 2019
Grant date	Feb 5, 2019

Abstract

Systems, methods, and devices for propelling self-propelled movable objects are provided. In one aspect, a rotor assembly for a self-propelled movable object comprises: a hub comprising a first fastening feature; a drive shaft comprising a second fastening feature and directly coupled to the hub by a mating connection of the first and second fastening features, wherein the drive shaft is configured to cause rotation of the hub such that the mating connection of the first and second fastening features is tightened by the rotation; and a plurality of rotor blades coupled to the hub and configured to rotate therewith to generate a propulsive force.

First claim

What is claimed is:

1. A multi-rotor self-propelled aerial vehicle, the aerial vehicle comprising:
(a) a first rotor assembly comprising:
a first hub coupled to a first plurality of blades, wherein the first hub comprises a first fastener disposed within a first cavity of the first hub; and
a first drive shaft comprising a second fastener configured to be coupled to the first hub through a mating connection of the first and second fasteners,
wherein the first drive shaft is configured to cause rotation of the first hub in a first direction via a first rotational force component that is transmitted from the first drive shaft to the first hub via contact between the first and second fasteners, and wherein the first plurality of blades configured to be coupled to the first hub are configured to rotate therewith in the first direction due to the rotation of the first hub to generate a first propulsive force providing lift to the aerial vehicle; and

(b) a second rotor assembly comprising:
a second hub coupled to a second plurality of blades, wherein the second hub comprises a third fastener disposed within a second cavity of the second hub; and
a second drive shaft comprising a fourth fastener and configured to be coupled to the second hub through a mating connection of the third and fourth fasteners,
wherein the second drive shaft is configured to cause rotation of the second hub in a second direction opposite to the first direction via a second rotational force component that is transmitted from the second drive shaft to the second hub via contact between the third and fourth fasteners , and wherein the second plurality of blades configured to be coupled to the second hub are configured to rotate therewith in the second direction due to the rotation of the second hub to generate a second propulsive force providing lift to the aerial vehicle.

2. The aerial vehicle of claim 1 , wherein the first hub comprises a first adapter, and wherein the first adapter comprises the first fastener within a cavity of the first adapter; and wherein the second hub comprises a second adapter, and wherein the second adapter comprises the third fastener in a cavity of the second adapter.

3. The aerial vehicle of claim 2 , wherein the first adapter is fixedly coupled to the first hub, or the second adapter is fixedly coupled to the second hub.

4. The aerial vehicle of claim 2 , wherein the first adapter is releasably coupled to the first hub and the second adapter is releasably coupled to the second hub.

5. The aerial vehicle of claim 1 , wherein the first fastener comprises a first threaded fastening feature, and wherein the third fastener comprises a second threaded fastening feature, the first threaded fastening feature comprising threads in an orientation different from threads of the second threaded fastening feature.

6. The aerial vehicle of claim 5 , wherein the first rotational force component is transmitted from the first drive shaft to the first hub via contact between the first threaded fastening feature and the second fastener, and wherein the second rotational force component is transmitted from the second drive shaft to the second hub via contact between the second threaded fastening feature and the fourth fastener.

7. The aerial vehicle of claim 1 , wherein the mating connection of the first and second fasteners is configured to be tightened by the rotation of the first hub in the first direction, and wherein the mating connection of the third and fourth fasteners is configured to be tightened by the rotation of the second drive shaft in the second direction.

8. The aerial vehicle of claim 1 , wherein contact between the first hub and the first shaft consists of the contact between the first fastener and the second fastener, and wherein contact between the second hub and the second shaft consists of the contact between the third fastener and the fourth fastener.

9. The aerial vehicle of claim 1 , wherein the first plurality of rotor blades is integrally formed with the first hub and the second plurality of rotor blades is integrally formed with the second hub.

10. The aerial vehicle of claim 1 , wherein the self-propelled aerial vehicle is an unmanned aerial vehicle.

11. A multi-rotor self-propelled aerial vehicle, the aerial vehicle comprising:
(a) a first rotor assembly comprising:
a first hub coupled to a first plurality of blades, wherein the first hub comprises a first fastener; and
a first drive shaft comprising a second fastener comprising features symmetrically disposed around a rotational axis of the first drive shaft and configured to be coupled to the first hub through a mating connection of the first and second fasteners,
wherein the first drive shaft is configured to cause rotation of the first hub in a first direction via a rotational force component that is transmitted from the first drive shaft to the first hub via contact between the first and second fasteners, and wherein the first plurality of blades configured to be coupled to the first hub are configured to rotate therewith in the first direction due to the rotation of the first hub to generate a first propulsive force; and

(b) a second rotor assembly comprising:
a second hub coupled to a second plurality of blades, wherein the second hub comprises a third fastener ; and
a second drive shaft comprising a fourth fastener comprising features symmetrically disposed around a rotational axis of the second drive shaft and configured to be coupled to the second hub through a mating connection of the third and fourth fasteners,
wherein the second drive shaft is configured to cause rotation of the second hub in a second direction opposite to the first direction via a rotational force component that is transmitted from the second drive shaft to the second hub via contact between the third and fourth fasteners , and wherein the second plurality of blades configured to be coupled to the second hub are configured to rotate therewith in the second direction due to the rotation of the second hub to generate a second propulsive force.

12. The aerial vehicle of claim 11 , wherein the first hub comprises a first adapter, and wherein the first adapter comprises the first fastener within a cavity of the first adapter, and wherein the second hub comprises a second adapter, and wherein the second adapter comprises the third fastener in a cavity of the second adapter.

13. The aerial vehicle of claim 11 , wherein the first fastener comprises a first pair of guides disposed within a first aperture, wherein each guide of the pair of guides comprises a first end and a second end, and wherein a corresponding first stop is disposed at the first end or the second end, and
wherein the third fastener comprises a second pair of guides disposed within a second aperture, wherein each guide of the second pair of guides comprises a first end and a second end, and wherein a second corresponding stop is disposed at the first end or the second end.

14. The aerial vehicle of claim 13 , wherein each guide of the first pair of guides partially spans a circumference of the first aperture, and wherein each guide of the second pair of guides partially spans a circumference of the second aperture.

15. The aerial vehicle of claim 13 , wherein the corresponding first stop disposed at the first end or the second end of each of the first pair of guides comprises a greater thickness than each of the first pair of guides, and wherein the corresponding second stop disposed at the first end or the second end of each of the second pair of guides comprises a greater thickness than each of the second pai

Assignees

• Sz Dji Technology Co Ltd

Inventors

• Wang Tao
• Zhao Tao
• Ou Zhi Gang

Classifications

• A63H27/02

  Model aircraft · CPC title

• B64C11/02

  Hub construction · CPC title

• A63H27/001

  Making or assembling thereof, e.g. by folding · CPC title

• F01D5/025

  Fixing blade carrying members on shafts (attachment of a member on a shaft in general F16D1/06; for non-positive displacement pumps F04D29/00) · CPC title

• B64C27/32 Primary

  Rotors · CPC title