Method for manufacturing an aircraft radome by assembling small-sized pieces of skin, aircraft radome and aircraft

Patent metadata

Field	Value
Publication number	US-12412978-B2
Application number	US-202318343826-A
Country	US
Kind code	B2
Filing date	Jun 29, 2023
Priority date	Jun 30, 2022
Publication date	Sep 9, 2025
Grant date	Sep 9, 2025

Abstract

A method of assembling an aircraft radome and a radome comprising at least a first skin and a second skin arranged on two opposite faces of the same shell, the first skin and the second skin being formed from a first assembly of skin pieces and from a second assembly of skin pieces, respectively, the assemblies being such that all or some of the skin pieces of the first and second assemblies partially overlap one or more neighboring skin pieces of the assembly that includes them, and such that the ratio between the surface area of a piece of skin overlapping one or more neighboring pieces of skin and the total surface area of that piece of skin does not exceed a predetermined threshold value.

First claim

The invention claimed is:

1. An aircraft radome comprising:
at least one shell,
a first skin, and
a second skin,
said first skin and said second skin being assembled on two opposite faces of each of the at least one shell,
said first skin and said second skin being formed from a first assembly of skin pieces and from a second assembly of skin pieces,

wherein all or some of the skin pieces of said first and second assemblies partially overlap one or more neighboring skin pieces of the assembly that includes them,
wherein a ratio between a surface area of a piece of skin overlapping one or more neighboring pieces of skin and a total surface area of that piece of skin does not exceed 30%, and
wherein one of said first skin and said second skin comprises:
a front portion which includes a tip of the radome with skin pieces arranged to form a central skin layer which forms parallel lines in a central area of the radome, such that the parallel lines are parallel to, and spaced apart from, a plane which passes through the tip of the radome.

2. The aircraft radome according to claim 1 , wherein said first and second assemblies each reproduce a predetermined assembly pattern.

3. The aircraft radome according to claim 1 , wherein each of the skin pieces has a rectangular, trapezoidal or triangular shape.

4. The aircraft radome according to claim 1 , wherein a largest dimension of each skin piece is smaller than one-third of a largest overall dimension of the radome.

5. The aircraft radome according to claim 4 , wherein the largest dimension of each skin piece is smaller than 42 cm.

6. The aircraft radome according to claim 5 , wherein the largest dimension of each skin piece is smaller than 30 cm.

7. The aircraft radome according to claim 1 , wherein said one of said first skin and said second skin further comprises a rear portion which includes skin pieces arranged side-by-side to form at least one circular crown assembled at a bottom end of the front portion of the skin layer.

8. The aircraft radome according to claim 1 , wherein the skin pieces are made of a composite material comprising a fabric reinforcement made of fibers, said fabric being pre-impregnated with a thermosetting or thermoplastic organic or synthetic resin.

9. The aircraft radome according to claim 8 , wherein said fibers comprise flax, hemp, plain polyethylene or polyethylene with a very high molecular weight, glass fabric, quartz fabric, or aramid fabric.

10. The aircraft radome according to claim 1 , wherein the shell is made of foam, paper or resin, and has a cellular structure.

11. An aircraft comprising an aircraft radome according to claim 1 .

12. The aircraft radome according to claim 1 , wherein the front portion further comprises two outer skin layers on opposite sides of the central skin layer which have skin pieces arranged to form lines oriented at a 60° angle relative to the parallel lines.

13. The aircraft radome according to claim 12 , wherein the central skin layer comprises skin pieces with a rectangular shape, such that a long edge of the rectangularly shaped skin pieces is parallel to the parallel lines, and wherein the two outer skin layers comprise skin pieces with a trapezoidal shape.

14. A method for assembling an aircraft radome comprising an assembly of a first skin and of a second skin on two opposite faces of the same shell, respectively, said first skin and said second skin being formed from a first assembly of skin pieces and a second assembly of skin pieces, respectively, the method comprising the steps:
partially overlapping all or some of the skin pieces of said first and second assemblies with one or more neighboring skin pieces of the assembly that includes them, and
maintaining a ratio between a surface area of a piece of skin overlapping one or more neighboring pieces of skin and a total surface area of that piece of skin below a predetermined threshold value,
wherein one of said first skin and said second skin comprises:
a front portion which includes a tip of the radome with skin pieces arranged to form a central skin layer which forms parallel lines in a central area of the radome, such that the parallel lines are parallel to, and spaced apart from, a plane which passes through the tip of the radome.

15. The method according to claim 14 , wherein the predetermined threshold value comprises 30%.

16. The method according to claim 14 , wherein the front portion further comprises two outer skin layers on opposite sides of the central skin layer which have skin pieces arranged to form lines oriented at a 60° angle relative to the parallel lines.

17. The method according to claim 16 , wherein the central skin layer comprises skin pieces with a rectangular shape, such that a long edge of the rectangularly shaped skin pieces is parallel to the parallel lines, and wherein the two outer skin layers comprise skin pieces with a trapezoidal shape.

Assignees

• Airbus Operations Sas

Inventors

• Fournie Jacques
• Bernus Christophe
• Verstraete Olivier
• Berhault Thomas

Classifications

• H01Q1/28

  Adaptation for use in or on aircraft, missiles, satellites, or balloons · CPC title

• B64F5/10 Primary

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• H01Q1/422 Primary

  comprising two or more layers of dielectric material (H01Q1/425 takes precedence) · CPC title

• H01Q1/281

  Nose antennas · CPC title

• B64C1/36

  adapted to receive antennas or radomes · CPC title