Aerial system thermal control system and method

• US 10,220,954 B2
• Filed: 04/24/2017
• Issued: 03/05/2019
• Est. Priority Date: 01/04/2015
• Status: Active Grant

• Current Assignee: Hangzhou Zero Zero Technology Co.Ltd (Shenzhen Zero Zero Infinite Technology Co. Ltd.)
• Original Assignee: Zero Zero Robotics Inc.
• Inventors: Sun, Wei, Zhang, Tong, Wang, Mengqiu
• Primary Examiner(s): Dunn, Alex C
• Application Number:
  US15/495,645
• Publication Number:
  US 20170225796A1
• Time in Patent Office: 680 Days
• CPC Class Codes: B64C 15/12 the power plant being tiltable
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 33/08 of power plant cooling systems cooling of internal-combustion engines per se F01P; cooling of gas-turbine plants or jet-propulsion plants per se F02C, F02K
• CPC Class Codes: B64D 47/08 Arrangements of cameras
• 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 20/30 for safety, e.g. with frangible components rotor guards B64U30/299
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2201/00 UAVs characterised by their flight controls
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 30/294 Rotors arranged in the UAV body
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/30 Supply or distribution of electrical power
• CPC Class Codes: B64U 70/30 for capturing UAVs in flight by ground or sea-based arresting gear, e.g. by a cable or a net
• CPC Class Codes: H01L 23/3675 characterised by the shape of the housing
• CPC Class Codes: H01L 23/467 by flowing gases, e.g. air H01L23/473 takes precedence
• CPC Class Codes: H05K 7/20154 Heat dissipaters coupled to components
• CPC Class Codes: H05K 7/20209 Thermal management, e.g. fan control

Abstract

An aerial vehicle including a set of rotors, a processor configured to configured to control the set of rotors for aerial vehicle flight, and a housing defining a plurality of cooling channels, wherein, for each rotor of the set, a projection of the processor and the cooling channels onto the respective rotor plane does not intersect the swept area of the rotor, and a distance from the rotor axis of a first rotor of the set to a cooling channel is less than 75% of a rotor diameter of the first rotor. A method for aerial vehicle operation, including providing an aerial vehicle including a rotor, a processor, and a housing, flying the aerial vehicle, and, while flying the aerial vehicle, actively cooling the processor, including, at the rotor, forcing airflow toward the processor.

Claims

1. An aerial vehicle comprising:

a set of rotors, each rotor of the set defining a respective rotor axis, a respective rotor plane normal to the respective rotor axis, and a respective swept area within the respective rotor plane, wherein the rotor axes are substantially non-collinear;

a processor configured to control the set of rotors for aerial vehicle flight;

a housing defining a housing interior and a plurality of cooling channels, the housing interior fluidly coupled to an ambient environment by the plurality of cooling channels, the processor arranged within the housing interior, each rotor of the set rotationally coupled to the housing about the respective rotor axis; and

a rotor housing mechanically coupled to the housing, the rotor housing enclosing a rotor of the set and defining a plurality of airflow apertures fluidly connecting the rotor to an ambient environment, wherein each aperture is smaller than a threshold size;

wherein;

for each rotor of the set, a projection of the processor and the cooling channels onto the respective rotor plane does not intersect the respective swept area; and

a distance from the rotor axis of a first rotor of the set to a cooling channel of the plurality is less than 75% of a rotor diameter of the first rotor.

2. The aerial vehicle of claim 1, wherein the rotor axes of the set of rotors are substantially parallel.

3. The aerial vehicle of claim 2, wherein the swept areas of the set of rotors are substantially coplanar.

4. The aerial vehicle of claim 3, wherein the aerial vehicle defines a lateral plane intersecting the processor and each rotor of the set.

5. The aerial vehicle of claim 3, wherein:

the set of rotors comprises four rotors; and

for each rotor of the set, a respective rotor diameter is greater than 40% of a longest dimension of a convex hull of a projection of the aerial system onto the respective rotor plane.

6. The aerial vehicle of claim 1, wherein the processor is arranged within a convex hull of the rotor axes of the set of rotors.

7. The aerial vehicle of claim 1, wherein a processor distance from the rotor axis of the first rotor to the processor is less than 75% of a rotor diameter of the first rotor.

8. The aerial vehicle of claim 1, wherein, for each rotor of the set, a sum of the swept areas of the set of rotors is greater than 50% of an area of a convex hull of a projection of the aerial system onto the respective rotor plane.

9. The aerial vehicle of claim 1, further comprising a heatsink thermally coupled to a broad face of the processor, the heatsink arranged within the housing interior.

10. An aerial vehicle comprising:

a set of rotors, each rotor of the set defining a respective rotor axis, a respective rotor plane normal to the respective rotor axis, and a respective swept area within the respective rotor plane, wherein the rotor axes are substantially non-collinear;

a processor configured to control the set of rotors for aerial vehicle flight; and

a housing defining a housing interior and a plurality of cooling channels, the housing interior fluidly coupled to an ambient environment by the plurality of cooling channels, the processor arranged within the housing interior, each rotor of the set rotationally coupled to the housing about the respective rotor axis;

wherein;

for each rotor of the set, a projection of the processor and the cooling channels onto the respective rotor plane does not intersect the respective swept area; and

for each rotor of the set, a sum of the swept areas of the set of rotors is greater than 50% of an area of a convex hull of a projection of the aerial system onto the respective rotor plane.

11. The aerial vehicle of claim 10, wherein the rotor axes of the set of rotors are substantially parallel.

12. The aerial vehicle of claim 11, wherein the swept areas of the set of rotors are substantially coplanar.

13. The aerial vehicle of claim 12, wherein the aerial vehicle defines a lateral plane intersecting the processor and each rotor of the set.

14. The aerial vehicle of claim 13, wherein:

the set of rotors comprises four rotors; and

for each rotor of the set, a respective rotor diameter is greater than 40% of a longest dimension of a convex hull of a projection of the aerial system onto the respective rotor plane.

15. The aerial vehicle of claim 14, wherein the processor is arranged within a convex hull of the rotor axes of the set of rotors.

16. The aerial vehicle of claim 10, wherein a processor distance from the rotor axis of the first rotor to the processor is less than 75% of a rotor diameter of the first rotor.

17. The aerial vehicle of claim 10, further comprising a rotor housing mechanically coupled to the housing, the rotor housing enclosing a rotor of the set and defining a plurality of airflow apertures fluidly connecting the rotor to an ambient environment, wherein each aperture is smaller than a threshold size.

18. The aerial vehicle of claim 10, further comprising a heatsink thermally coupled to a broad face of the processor, the heatsink arranged within the housing interior.

19. The aerial vehicle of claim 10, wherein a distance from the rotor axis of a first rotor of the set to a cooling channel of the plurality is less than 75% of a rotor diameter of the first rotor.