Aircraft and method for mounting device to be installed outside aircraft onto airframe

Patent metadata

Field	Value
Publication number	US-9617008-B2
Application number	US-201514638020-A
Country	US
Kind code	B2
Filing date	Mar 4, 2015
Priority date	Aug 8, 2014
Publication date	Apr 11, 2017
Grant date	Apr 11, 2017

Abstract

The present invention aims to provide a structure which can reduce the scale of modification of an airframe and allows a device to be installed outside the aircraft to be easily mounted onto the airframe. An aircraft includes, as a structure for mounting a measuring device to be installed outside the aircraft onto the airframe: an arm which penetrates the airframe inwardly and outwardly through a window, and has a portion to be provided with the measuring device and a portion located inside the aircraft; seat rails which support seats disposed inside the aircraft; and a mount which is connected with the arm inside the aircraft and transmits a load input from the arm to the seat rails.

First claim

What is claimed is:

1. An aircraft comprising, as a structure for mounting a device to be installed outside the aircraft onto an airframe:
a penetration member which penetrates the airframe inwardly and outwardly through an opening included in the airframe, and has a portion to be provided with the device and a portion located inside the aircraft;
a seat support member which supports a seat disposed inside the aircraft, the seat support member comprising a first rail member and a second rail member disposed in parallel to each other in a front-rear direction along a floor of the aircraft, wherein the first rail member and the second rail member each comprise a plurality of engaging parts at regular intervals along the front-rear direction; and
a load transmission member which is connected with the penetration member inside the aircraft and transmits a load input from the penetration member to the seat support member.

2. The aircraft according to claim 1 , wherein the opening is formed in a window substituting member which is provided in place of an original window panel in a window frame of a window present in the airframe.

3. The aircraft according to claim 1 , wherein the penetration member has a wing shape in transverse section.

4. The aircraft according to claim 1 , wherein the device measures physical amounts related to water droplets contained in the atmosphere outside the aircraft.

5. The aircraft according to claim 1 , wherein the load transmission member includes: a framework having two first support pillars rising from the first rail member toward the penetration member and two second support pillars rising from the second rail member toward the penetration member; and plate materials constituting side walls provided in the framework.

6. The aircraft according to claim 1 , wherein
the penetration member has a first connection part,
the load transmission member has a second connection part connected with the first connection part,
at least one of the first connection part and the second connection part is composed of a pair of members disposed at a distance in the front-rear direction, and
the pair of members is connected with a mating part, which is either the first connection part or the second connection part, through a pin extending in the front-rear direction.

7. The aircraft according to claim 1 , wherein
the penetration member has a wing shape in transverse section and has a first connection part,
the load transmission member has a second connection part connected with the first connection part, and
the first connection part and the second connection part are connected with each other through a first pin and a second pin both extending in the front-rear direction and disposed side by side in the upper-lower direction.

8. An aircraft comprising, as a structure for mounting a device to be installed outside the aircraft onto an airframe:
a penetration member which penetrates the airframe inwardly and outwardly through an opening included in the airframe, and has a portion to be provided with the device and a portion located inside the aircraft;
a seat support member which supports a seat disposed inside the aircraft;
a load transmission member which is connected with the penetration member inside the aircraft and transmits a load input from the penetration member to the seat support member;
a seal which seals a clearance defined between the penetration member and an opening forming member which forms the opening; and
a retainer which presses the seal against the penetration member and the opening forming member, wherein
the penetration member and the opening forming member each have a receiving part for receiving the seal,
both receiving parts are disposed in a direction connecting one side and the other side of the clearance across the clearance, and
the seal is fixed on only one of the receiving part of the penetration member and the receiving part of the opening forming member.

9. The aircraft according to claim 1 , wherein the load transmission member comprises two first support pillars rising from the first rail member and two second support pillars rising from the second rail member, wherein the first support pillars and the second support pillars each have an L-shaped cross-section.

10. The aircraft according to claim 1 , further comprising the device, wherein the device measures physical amounts related to water droplets using a laser.

11. The aircraft according to claim 1 , wherein the penetration member is connected to the load transmission member with a connecting part and two pins that extend in the front-rear direction through corresponding holes in the connecting part.

12. The aircraft according to claim 1 , wherein the plurality of engaging parts are holes spaced at regular intervals along the first and second rail members in the front-rear direction.

13. The aircraft according to claim 5 , wherein the side walls couple adjacent ones of the two first support pillars and the two second support pillars.

14. The aircraft according to claim 1 , wherein the load transmission member is fixed to the first rail member and the second rail member.

15. The aircraft according to claim 14 , wherein the load transmission member is fixed to a corresponding engaging part of the first rail member and a corresponding engaging part of the second rail member.

16. The aircraft according to claim 1 , wherein the first rail member and the second rail member support the seat disposed inside in the aircraft.

Assignees

• Mitsubishi Aircraft Corp

Inventors

• Goto Shingo
• Sugimura Toshiaki

Classifications

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64C1/1484

  Windows (B64C1/1492 takes precedence) · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title

• B61D49/00

  Other details · CPC title

• B64C1/36

  adapted to receive antennas or radomes · CPC title