# US 10,369,763 B2 · Segmented acoustic insert

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- Number: US 10,369,763 B2
- Document ID: US10369763B2
- Status: Granted
- Kind: B2
- Application number: 15/490,999
- Filed: 2017-04-19
- Published: 2018-10-25
- Granted: 2019-08-06
- Earliest claimed: 2017-04-19
- Assignees: The Boeing Company
- Applicants: The Boeing Company
- Inventors: Justin Honshune Lan
- Web page: https://patentgrep.com/patent/US10369763B2

## CPC

- B32B 3/12: characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
- B32B 7/08: by mechanical means
- B32B 3/08: characterised by added members at particular parts {(layer formed of separate pieces of material which are juxtaposed side-by-side B32B3/14, B32B3/18)}
- B32B 7/12: using interposed adhesives or interposed materials with bonding properties
- B32B 9/005: {comprising one layer of ceramic material, e.g. porcelain, ceramic tile (layered products with at least two ceramic layers composed mainly of ceramic B32B18/00)}
- B32B 9/045: {of synthetic resin}
- B32B 15/043: {of metal (B32B15/01 takes precedence)}
- B32B 15/08: of synthetic resin
- B32B 15/14: next to a fibrous or filamentary layer
- B32B 15/20: comprising aluminium or copper {(B32B15/016 and B32B15/017 take precedence)}
- B32B 27/08: of synthetic resin
- B32B 27/12: next to a fibrous or filamentary layer
- B32B 2250/03: 3 layers
- B32B 2260/021: Fibrous or filamentary layer
- B32B 2260/046: Synthetic resin
- B32B 2307/10: having particular acoustical properties
- B32B 2307/732: Dimensional properties
- B32B 2419/00: Buildings or parts thereof
- B32B 2605/00: Vehicles
- B32B 2605/12: Ships
- B32B 2605/16: Submarines
- B32B 2605/18: Aircraft
- B64D 2033/0206: {comprising noise reduction means, e.g. acoustic liners}
- B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT

## Abstract

An acoustic insert comprises a sleeve having a first end and a second end. The sleeve comprises segments between the first end and the second end. A first acoustic septum is placed within the sleeve at a first depth. A second acoustic septum placed within the sleeve at a second depth.

## Claims

### Claim 1

An acoustic insert comprising:
a sleeve having a first end and a second end, the sleeve comprising segments between the first end and the second end;
a first acoustic septum placed within the sleeve at a first depth; and
a second acoustic septum placed within the sleeve at a second depth;
wherein a first segment in the segments is joined to a second segment in the segments by at least one of an adhesive, a welding material, ultrasonic welding, laser heating, infrared heating, and friction.

### Claim 2 (depends on 1)

The acoustic insert of claim 1, wherein the first acoustic septum comprises a first structure with a first number of holes such that the acoustic insert absorbs noise at a first range of frequencies.

### Claim 3 (depends on 2)

The acoustic insert of claim 2, wherein the second acoustic septum comprises a second structure with a second number of holes such that the acoustic insert absorbs noise at a second range of frequencies.

### Claim 4 (depends on 3)

The acoustic insert of claim 3, wherein the first acoustic septum is positioned at a first bond line between the first segment and the second segment in the segments.

### Claim 5 (depends on 4)

The acoustic insert of claim 4, wherein the second acoustic septum is positioned at a second bond line between the second segment and a third segment in the segments.

### Claim 6 (depends on 3)

The acoustic insert of claim 3 further comprising:
a third acoustic septum placed within the sleeve at a third depth, the third acoustic septum comprising a third structure with a third number of holes such that the acoustic insert absorbs noise at a third range of frequencies.

### Claim 7 (depends on 1)

The acoustic insert of claim 1 further comprising:
a honeycomb core having a plurality of cells, wherein the sleeve is positioned within a cell in the plurality of cells.

### Claim 8 (depends on 7)

The acoustic insert of claim 7 further comprising:
a gap between an outer surface of the sleeve and a wall of the cell.

### Claim 9 (depends on 1)

The acoustic insert of claim 1 further comprising:
a cutout at the second end of the sleeve configured to provide a liquid drainage path to the sleeve.

### Claim 10

An aircraft structure comprising:
a first facesheet;
a second facesheet opposite the first facesheet;
a honeycomb core having a first edge, a second edge, and a plurality of cells, wherein the first edge of the honeycomb core touches the first facesheet, and the second edge of the honeycomb core touches the second facesheet;
an acoustic insert positioned within a cell in the plurality of cells, the acoustic insert comprising a sleeve having segments between a first end and a second end of the sleeve, a first acoustic septum placed within the sleeve at a first depth, and a second acoustic septum placed within the sleeve at a second depth; and
a gap between an outer surface of the sleeve and a wall of the cell.

### Claim 11 (depends on 10)

The aircraft structure of claim 10 further comprising:
a cutout at the second end of the sleeve configured to provide a liquid drainage path to the sleeve.

### Claim 12 (depends on 10)

The aircraft structure of claim 10, wherein the first acoustic septum is positioned at a first bond line between a first segment and a second segment in the segments, and the first acoustic septum comprises a first structure with a first number of holes such that the acoustic insert is tuned to absorb a first range of frequencies.

### Claim 13 (depends on 12)

The aircraft structure of claim 12, wherein the second acoustic septum is positioned at a second bond line between the second segment and a third segment in the segments, and the second acoustic septum comprises a second structure with a second number of holes such that the acoustic insert is tuned to absorb a second range of frequencies.

### Claim 14 (depends on 10)

The aircraft structure of claim 10, wherein the sleeve is not bonded to the honeycomb core.

### Claim 15

A method for reducing noise in an aircraft, the method comprising:
forming an acoustic insert comprising a sleeve having segments between a first end and a second end of the sleeve, a first acoustic septum, and a second acoustic septum, wherein the acoustic insert is configured to absorb a range of frequencies and wherein forming the acoustic insert comprises bonding a first segment and a second segment in the segments and bonding a third segment and the second segment in the segments; and
positioning the acoustic insert within a cell in a honeycomb core.

### Claim 16 (depends on 15)

The method of claim 15 further comprising:
positioning the first acoustic septum at a first bond line between the first segment and the second segment; and
positioning the second acoustic septum at a second bond line between the second segment and the third segment.

### Claim 17 (depends on 15)

The method of claim 15 further comprising:
bonding a first facesheet to a first edge of the honeycomb core; and
bonding a second facesheet to a second edge of the honeycomb core such that the acoustic insert is positioned within the cell between the first facesheet and the second facesheet, wherein the acoustic insert is not bonded to the honeycomb core.