# US 2017/0283077 A1 · Pneumatic de-icer with sensor for supercooled large droplet icing detection

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- Number: US 2017/0283077 A1
- Document ID: US20170283077A1
- Status: Published application
- Kind: A1
- Application number: 15/088,847
- Filed: 2016-04-01
- Published: 2017-10-05
- Earliest claimed: 2016-04-01
- Assignees: Goodrich Corporation
- Applicants: Goodrich Corporation
- Inventors: James C. Putt
- Web page: https://patentgrep.com/patent/US20170283077A1

## CPC

- B64D 15/166: {using pneumatic boots}
- B64D 15/22: Automatic initiation by icing detector
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT

## Abstract

A de-icing assembly includes an aircraft with an airfoil. A de-icer is disposed on a leading edge of the airfoil. A tab extends from the de-icer in an aft direction from an aft edge of the de-icer. The de-icer and the tab are adhesively attached onto an outer skin of the airfoil. A supercooled large droplet sensor is built into the tab. The supercooled large droplet sensor is positioned in a location aft of the aft edge of the de-icer.

## Claims

### Claim 1

A de-icing assembly comprising:
an aircraft having an airfoil;
a de-icer disposed on a leading edge of the airfoil;
a tab extending from the de-icer in an aft direction from an aft edge of the de-icer,
wherein the de-icer and the tab are adhesively attached onto an outer skin of the airfoil; and
a supercooled large droplet sensor built into the tab, wherein the supercooled large droplet sensor is positioned in a location aft of the aft edge of the de-icer.

### Claim 2 (depends on 1)

The de-icing assembly of claim 1, wherein the airfoil comprises:
a wing, wherein the supercooled large droplet sensor is positioned on an upper surface of the wing.

### Claim 3 (depends on 1)

The de-icing assembly of claim 1, wherein the airfoil comprises:
a horizontal stabilizer, wherein the supercooled large droplet sensor is positioned on a lower surface of the horizontal stabilizer.

### Claim 4 (depends on 1)

The de-icing assembly of claim 1, further comprising:
wires connecting the supercooled large droplet sensor to an electrical system of the aircraft.

### Claim 5 (depends on 4)

The de-icing assembly of claim 4, wherein the wires extend from the supercooled large droplet sensor, through the tab, underneath the de-icer, and through an air supply port in the outer skin of the airfoil, wherein the air supply port is also used for an air supply to the de-icer.

### Claim 6

A method of installing a de-icing assembly, the method comprising:
positioning a supercooled large droplet sensor inside of a tab attached to a de-icer;
adhering the de-icer to a leading edge of an airfoil of an aircraft; and
adhering the tab of the de-icer to the airfoil concurrently with adhesion of the de-icer to the airfoil, wherein adhering the tab further comprises:
positioning the supercooled large droplet sensor in a region aft of an aft edge of the de-icer.

### Claim 7 (depends on 6)

The method of claim 6, further comprising:
feeding wires connected to the supercooled large droplet sensor through an air supply port in a skin of the airfoil, wherein the air supply port includes an air connection for the de-icer.

### Claim 8

A de-icing assembly comprising:
a de-icer configured to be disposed on a leading edge of an airfoil;
a tab extending from the de-icer in an aft direction from an aft edge of the de-icer;
a supercooled large droplet sensor built into the tab, wherein the supercooled large droplet sensor is positioned in a location aft of the aft edge of the de-icer; and
an adhesive applied to the de-icer and the tab.

### Claim 9 (depends on 8)

The de-icing assembly of claim 8, wherein the de-icing assembly is configured to position the supercooled large droplet sensor on an upper surface of a wing of an aircraft.

### Claim 10 (depends on 8)

The de-icing assembly of claim 8, wherein the de-icing assembly is configured to position the supercooled large droplet sensor on a lower surface of a horizontal stabilizer of a wing of an aircraft.

### Claim 11 (depends on 8)

The de-icing assembly of claim 8, further comprising:
wires to connect the supercooled large droplet sensor to an electrical system of an aircraft.