Window of an aircraft with an electromagnetic shield

• US 9,598,166 B2
• Filed: 12/13/2012
• Issued: 03/21/2017
• Est. Priority Date: 01/11/2012
• Status: Active Grant

• Current Assignee: Mitsubishi Aircraft Corporation (Mitsubishi Heavy Industries, Ltd.)
• Original Assignee: Mitsubishi Aircraft Corporation (Mitsubishi Heavy Industries, Ltd.)
• Inventors: Yokoi, Takashi
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Giczy, Alexander V
• Application Number:
  US14/361,560
• Publication Number:
  US 20140319277A1
• Time in Patent Office: 1,559 Days
• Field of Search: 522/045.3, 522/045.4, 522/045.5
• US Class Current: 1/1
• CPC Class Codes: B64C 1/1484 Windows B64C1/1492 takes precedence
• CPC Class Codes: B64C 1/1492 Structure and mounting of the transparent elements in the window or windscreen
• CPC Class Codes: H05K 9/0005 Shielded windows
• CPC Class Codes: Y10T 156/10 Methods of surface bonding and/or assembly therefor

Abstract

A window of an aircraft having electromagnetic shielding performance and environment-resistant sealing performance, an aircraft, and an assembly method for a window of an aircraft are provided. A conductive seal member (60) is provided so as to face and surround the peripheral side surface of a window panel and is sandwiched between a conductive film (41) and an outer retainer (22). In the conductive seal member (60), thin wire materials (62) made of a conductive material such as aluminum are embedded in a seal member body (61) made of a material, such as silicone rubber, having an electric insulating property, waterproofness and pliability. An electromagnetic shielding effect, and environment-resistant sealing properties such as an electric insulating property and waterproofness can be both ensured by the conductive seal member (60).

Claims

1. A window of an aircraft with an electromagnetic shield, comprising:

a transparent window panel having an outer surface, an inner surface, and a peripheral side surface connecting the outer surface and the inner surface;

an inner retainer and an outer retainer that are provided on an outer peripheral portion of the window panel so as to sandwich the window panel therebetween;

an electromagnetic shielding film that is made of a conductive material;

a connecting film that is made of a conductive material, one end of the connecting film being connected to the electromagnetic shielding film; and

a conductive seal member that is provided so as to face and surround the peripheral side surface of the window panel, and sandwiched between another end of the connecting film and the outer retainer,

wherein there is a space at an outside of a peripheral side surface of the conductive seal member, and

wherein the conductive seal member includes a seal member body and a conductive member, the seal member body having an electric insulating property and the conductive member electrically connecting the another end of the connecting film and the outer retainer.

2. The window of an aircraft according to claim 1, wherein in the conductive seal member, a wire material is embedded as the conductive member in the seal member body.

3. The window of an aircraft with an electromagnetic shield according to claim 2, wherein in the conductive seal member, a thickness in a non-compressed state is set to be larger than a thickness when the seal member body is compressed between the another end of the connecting film and the outer retainer.

4. The window of an aircraft according to claim 2, wherein the wire material is embedded in the seal member body such that when the seal member body is compressed between the connecting film and the outer retainer, the wire material projects from front and rear sides of the seal member body into the connecting film and the outer retainer.

5. The window of an aircraft according to claim 2, wherein the wire material is deformable when the seal member body is compressed in a direction connecting the another end of the connecting film and the outer retainer.

6. The window of an aircraft with an electromagnetic shield according to claim 5, wherein in the conductive seal member, a thickness in a non-compressed state is set to be larger than a thickness when the seal member body is compressed between the another end of the connecting film and the outer retainer.

7. The window of an aircraft with an electromagnetic shield according to claim 1, wherein in the conductive seal member, a thickness in a non-compressed state is set to be larger than a thickness when the seal member body is compressed between the another end of the connecting film and the outer retainer.

8. The window of an aircraft according to claim 1, wherein the seal member body having the electric insulating property comprises a portion of the conductive seal member that faces the peripheral side surface of the window panel.

9. The window of an aircraft according to claim 1, wherein the conductive seal member comprises a side surface that partially constitutes a peripheral end surface of the window, wherein the conductive member is provided so as not to be exposed on the side surface.

10. The window of an aircraft according to claim 1, wherein the connecting film does not extend beyond the peripheral side surface of the conductive seal member.

11. The window of an aircraft according to claim 1, wherein the conductive seal member is spaced from a fastener that fixes the window panel between the inner retainer and the outer retainer.

12. An aircraft comprising the window of an aircraft according to claim 1.

13. An aircraft comprising the window of an aircraft according to claim 2.

14. An aircraft comprising the window of an aircraft according to claim 5.

15. An aircraft comprising the window of an aircraft according to claim 7.

16. An assembly method for assembling the window of the aircraft according to claim 1, comprising steps of:

laminating the window panel and the electromagnetic shielding film together;

connecting the one end of the connecting film to the electromagnetic shielding film;

sandwiching the conductive seal member between the another end of the connecting film and the outer retainer; and

sandwiching the outer peripheral portions of the window panel and the electromagnetic shielding film laminated together between the inner retainer and the outer retainer.

17. An assembly method for assembling the window of the aircraft according to claim 2, comprising steps of:

laminating the window panel and the electromagnetic shielding film together;

connecting the one end of the connecting film to the electromagnetic shielding film;

sandwiching the conductive seal member between the another end of the connecting film and the outer retainer; and

sandwiching the outer peripheral portions of the window panel and the electromagnetic shielding film laminated together between the inner retainer and the outer retainer.

18. An assembly method for assembling the window of the aircraft according to claim 5, comprising steps of:

laminating the window panel and the electromagnetic shielding film together;

connecting the one end of the connecting film to the electromagnetic shielding film;

sandwiching the conductive seal member between the another end of the connecting film and the outer retainer; and

sandwiching the outer peripheral portions of the window panel and the electromagnetic shielding film laminated together between the inner retainer and the outer retainer.

19. An assembly method for assembling the window of the aircraft according to claim 7, comprising steps of:

laminating the window panel and the electromagnetic shielding film together;

connecting the one end of the connecting film to the electromagnetic shielding film;

sandwiching the conductive seal member between the another end of the connecting film and the outer retainer; and

sandwiching the outer peripheral portions of the window panel and the electromagnetic shielding film laminated together between the inner retainer and the outer retainer.