Aerial system propulsion assembly and method of use

• US 10,435,144 B2
• Filed: 04/24/2017
• Issued: 10/08/2019
• Est. Priority Date: 04/24/2016
• Status: Active Grant

• Current Assignee: Hangzhou Zero Zero Technology Co.Ltd (Shenzhen Zero Zero Infinite Technology Co. Ltd.)
• Original Assignee: Hangzhou Zero Zero Technology Co.Ltd (Shenzhen Zero Zero Infinite Technology Co. Ltd.)
• Inventors: Zhang, Lei, Guo, Hanqing, Wang, Zhaozhe, Zhang, Tong, Wang, Mengqiu
• Primary Examiner(s): Jin, George C
• Application Number:
  US15/495,615
• Publication Number:
  US 20170305542A1
• Time in Patent Office: 897 Days
• CPC Class Codes: B64C 11/02 Hub construction
• CPC Class Codes: B64C 11/04 Blade mountings
• CPC Class Codes: B64C 2027/003 mounted on rotor hub, e.g. a rotary force generator
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 27/14 Direct drive between power plant and rotor hub
• CPC Class Codes: B64C 27/32 Rotors
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/14 with four distinct rotor axes, e.g. quadcopters
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 30/30 Lift-producing means using radial airflow
• CPC Class Codes: B64U 50/19 using electrically powered motors

Abstract

An aerial vehicle including a housing, an outrunner motor including a stator mechanically coupled to the housing and a rotor rotationally coupled to the stator, and a propeller removably coupled to the rotor, the propeller including a hub and a plurality of propeller blades. A rotor, a propeller including a hub and a propeller blade, a radial alignment mechanism, a rotational retention mechanism, and an axial retention mechanism.

Claims

1. A system for an aerial vehicle, the system comprising:

a rotor defining a cylindrical body, the cylindrical body defining a first and second end, a rotor cylinder axis, and a rotor diameter;

a propeller comprising a hub and a propeller blade mechanically coupled to the hub, the hub defining a cylindrical void, the cylindrical void defining a hub cylinder axis and a hub inner diameter greater than the rotor diameter;

a radial alignment mechanism mechanically coupled to the rotor proximal the first end and to the hub, the radial alignment mechanism retaining the hub cylinder axis substantially collinear with the rotor cylinder axis, the radial alignment mechanism comprising;

a first surface defining a hole substantially centered on the rotor cylinder axis; and

a boss retained within the hole;

a rotational retention mechanism mechanically coupled to the rotor proximal the first end and to the hub, the rotational retention mechanism rotationally retaining the hub about the rotor axis with respect to the rotor, the rotational retention mechanism comprising;

a radial member extending radially inward of the cylindrical body; and

a limit member contacting the radial member; and

an axial retention mechanism mechanically coupled to the rotor proximal the second end and to the hub, the axial retention mechanism translationally retaining the hub with respect to the rotor along an axial direction parallel the rotor cylinder axis, the axial retention mechanism comprising;

a second surface defining a circumferential recess; and

a circumferential protrusion defined along a third surface separate from the second surface, the circumferential protrusion retained within the circumferential recess.

2. The system of claim 1, wherein:

the second surface is defined by the hub;

the circumferential protrusion is attached to the rotor more proximal the second end than the first end; and

a protrusion radius from the rotor cylinder axis to the circumferential protrusion is greater than half the hub inner diameter.

3. The system of claim 2, wherein the axial retention mechanism further comprises:

a circumferential retention flange attached to the second surface, the circumferential retention flange arranged proximal the second end relative to the circumferential recess, wherein a flange radius from the hub cylinder axis to the circumferential retention flange is greater than the protrusion radius; and

a lead-in surface attached to the circumferential retention flange, the lead-in surface arranged proximal the second end relative to the circumferential retention flange, the lead-in surface defining a tangent plane at an oblique angle to the second end and to the hub cylinder axis.

4. The system of claim 1, wherein the hub inner diameter exceeds the rotor diameter by more than 1 mm.

5. The system of claim 1, wherein:

the hub comprises a hub end proximal the second end, the hub end defining a hub end plane normal the hub cylinder axis;

the hub end plane and the rotor cylinder axis intersect at an intersection point; and

a distance from the intersection point to a region of the rotor within the hub is greater than half the hub inner diameter.

6. The system of claim 1, wherein the limit member extends substantially parallel the rotor cylinder axis.

7. The system of claim 1, wherein:

the radial member comprises a first side and a second side opposing the first side, the first and second sides substantially parallel the rotor cylinder axis;

the limit member contacts the first side; and

the rotational retention mechanism further comprises a second limit member contacting the second side.

8. The system of claim 1, wherein the radial member is attached to the rotor and the limit member is attached to the hub.

9. The system of claim 8, wherein the boss is attached to the radial member and the first surface is mechanically coupled to the hub.

10. The system of claim 1, further comprising a damper arranged between the rotor and the hub.

11. The system of claim 10, wherein the damper comprises a gasket arranged circumferentially around the rotor.