Air scoop solar shield for UAV

Patent metadata

Field	Value
Publication number	US-12110139-B2
Application number	US-202117541944-A
Country	US
Kind code	B2
Filing date	Dec 3, 2021
Priority date	Dec 3, 2021
Publication date	Oct 8, 2024
Grant date	Oct 8, 2024

Abstract

An unmanned aerial vehicle (UAV) includes a fuselage, electronics disposed with the fuselage, a heat sink, and a solar shield. The heat sink is thermally connected to the electronics and includes a cooling plate disposed on or extends through an exterior surface of the fuselage. The cooling plate is exposed to an external environment of the UAV to conduct heat from the electronics to the external environment via convection. The solar shield extends over the cooling plate and defines an air scoop within which the cooling plate is disposed. The air scoop directs airflow from the external environment across the cooling plate. The solar shield shades the cooling plate from solar radiation to prevent or reduce solar heating of the cooling plate.

First claim

What is claimed is:

1. An unmanned aerial vehicle (UAV), comprising:
a fuselage;
electronics disposed with the fuselage;
a heat sink thermally connected to the electronics, the heat sink including a cooling plate disposed on or extending through an exterior surface of the fuselage and exposed to an external environment of the UAV to conduct heat from the electronics to the external environment via convection; and
a solar shield extending over the cooling plate and defining an air scoop within which the cooling plate is disposed to direct airflow from the external environment along an airduct passage that passes over the cooling plate, wherein the solar shield at least partially shades the cooling plate from solar radiation incident from above the UAV,
wherein the solar shield is configured as a removeable mounting bracket that spans the heat sink and removably mounts a tail assembly including one or more stabilizers to the fuselage,
wherein the airduct passage does not include an actuated obstruction that diverts airflow exiting the airduct passage.

2. The UAV of claim 1 , wherein the cooling plate is disposed on or extends through a topside surface of the fuselage.

3. The UAV of claim 2 , wherein the cooling plate and the electronics are disposed in or on an aft section of the fuselage.

4. The UAV of claim 1 , wherein the solar shield is integrated into the tail assembly forming a single contiguous member with the tail assembly.

5. The UAV of claim 1 , further comprising:
a propeller mounted to the fuselage in line with the air scoop defined by the solar shield to blow or draw the airflow through the air scoop across the cooling plate.

6. The UAV of claim 5 , wherein the propeller comprises a tail propeller mounted to a tail of the fuselage immediately behind the solar shield.

7. The UAV of claim 5 , further comprising a controller disposed within the fuselage and including logic that when executed by the controller causes the UAV to perform operations comprising:
spinning the propeller to blow or draw the airflow through the air scoop across the cooling plate while the UAV is landed on a charging pad and charging a battery disposed within the fuselage to cool the electronics,
wherein the propeller is mounted to the UAV to provide horizontal propulsion to the UAV during horizontal cruise flight and a thrust of the propeller is limited during the spinning while the UAV is on the charging pad to prevent movement of the UAV while charging the UAV.

8. The UAV of claim 5 , wherein the UAV comprises a vertical takeoff and landing (VTOL) fixed wing aircraft including a plurality of vertical lift rotors and a plurality of horizontal thrust propellers.

9. The UAV of claim 1 , wherein the cooling plate comprises cooling fins that extend into the air scoop and align with a direction of the airflow.

10. The UAV of claim 1 , wherein the solar shield is shaped to function as a clip-in mount for the tail assembly.

11. A fixed wing unmanned aerial vehicle (UAV), comprising:
a fuselage;
electronics disposed with an aft section of the fuselage;
a heat sink disposed in the aft section of the fuselage and thermally connected to the electronics, the heat sink including a cooling plate exposed from a topside of the fuselage to an external environment of the UAV to conduct heat from the electronics to the external environment via convection; and
a solar shield extending over the cooling plate and defining an air scoop within which the cooling plate is disposed to direct airflow from the external environment along an airduct passage that passes over the cooling plate, wherein the solar shield shades the cooling plate from solar radiation incident from above the fixed wing UAV to reduce solar heating of the cooling plate by the solar radiation,
wherein the solar shield is configured as a removeable mounting bracket that spans the heat sink and removably mounts a tail assembly including one or more stabilizers to the fuselage,
wherein the solar shield is integrated into the tail assembly forming a single contiguous member with the tail assembly,
wherein the airduct passage does not include an actuated obstruction that diverts airflow exiting the airduct passage.

12. The fixed wing UAV of claim 11 , further comprising:
a propeller mounted to the fuselage in line with the air scoop defined by the solar shield to blow or draw the airflow through the air scoop across the cooling plate.

13. The fixed wing UAV of claim 12 , wherein the propeller comprises a tail propeller mounted to a tail of the fuselage immediately behind the solar shield.

14. The fixed wing UAV of claim 12 , further comprising a controller disposed within the fuselage and including logic that when executed by the controller causes the fixed wing UAV to perform operations comprising:
spinning the propeller to blow or draw the airflow through the air scoop across the cooling plate while the fixed wing UAV is landed on a charging pad and charging a battery disposed within the fuselage,
wherein the propeller is mounted to the fixed wing UAV to provide horizontal propulsion to the fixed wing UAV during horizontal cruise flight and a thrust of the propeller is limited during the spinning while the fixed wing UAV is on the charging pad to prevent movement of the fixed wing UAV while charging the fixed wing UAV.

Assignees

• Wing Aviation Llc

Inventors

• Twyford Evan
• Qiu Ivan
• Juma James

Classifications

• B64U30/40

  Empennages, e.g. V-tails (foldable or collapsible UAVs B64U20/50) · CPC title

• B64U20/96

  using air · CPC title

• B64U10/20

  Vertical take-off and landing [VTOL] aircraft (flying platforms B64U10/13; helicopters B64U10/17) · CPC title

• B64C29/0025

  the propellers being fixed relative to the fuselage · CPC title

• B60L2200/10

  Air crafts · CPC title