Aircraft and fuselage cooling structure

Patent metadata

Field	Value
Publication number	US-2016207606-A1
Application number	US-201514962748-A
Country	US
Kind code	A1
Filing date	Dec 8, 2015
Priority date	Jan 21, 2015
Publication date	Jul 21, 2016
Grant date	—

Abstract

Under constraints on the space and the weight of an aircraft, the present invention aims to protect structural members from a heat generation part. An aircraft includes: a fuselage; an air conditioning pack installed on the outside of a lower part of the fuselage; a fairing covering the air conditioning pack; an outer heat insulation material disposed in a region of the fuselage, which corresponds to the air conditioning pack, from the outside of the fuselage; and an inner heat insulation material disposed around the region on the inside of the fuselage.

First claim

What is claimed is:

1 . An aircraft comprising:
a fuselage; a heat generation part installed on the outside of the fuselage; a fairing covering the heat generation part; an outer heat insulation material disposed in a corresponding region of the fuselage, which corresponds to the heat generation part, from the outside of the fuselage; and an inner heat insulation material disposed around the corresponding region on the inside of the fuselage.

2 . The aircraft according to claim 1 , further comprising an air conditioning system, wherein air conditioned by the air conditioning system is present in a space further on the inside than the corresponding region.

3 . The aircraft according to claim 1 , wherein the corresponding region is exposed toward the inside of the fuselage.

4 . The aircraft according to claim 1 , wherein the inner heat insulation material and the outer heat insulation material are disposed so as to together cover the entire circumference of the fuselage without interruption.

5 . The aircraft according to claim 1 , wherein end edges of the inner heat insulation material and the outer heat insulation material overlap each other.

6 . The aircraft according to claim 1 , wherein the corresponding region is defined over an area substantially equal to an area of the heat generation part projected along the thickness direction of the fuselage.

7 . The aircraft according to claim 1 , wherein the corresponding region is defined over an area larger than an area of the heat generation part projected along the thickness direction of the fuselage.

8 . The aircraft according to claim 1 , wherein end edges of the inner heat insulation material which are adjacent to the corresponding region are rising gently in a thickness direction of the inner heat insulation material.

9 . The aircraft according to claim 8 , wherein the inner heat insulation material has a curvature from each of the end edges to a surface of the inner heat insulation material.

10 . The aircraft according to claim 8 , wherein the inner heat insulation material is formed so that each of the end edges and a surface of the inner heat insulation material form an obtuse angle.

11 . The aircraft according to claim 1 , wherein a flow of air is supplied from the inside of the fuselage toward the corresponding region.

12 . The aircraft according to claim 1 , wherein a flow of air is supplied to a space between the fuselage and the fairing.

13 . The aircraft according to claim 1 , wherein the surface area of the corresponding region in contact with air on the inside of the fuselage is increased by a protrusion formed in the corresponding region.

14 . The aircraft according to claim 1 , wherein the outer heat insulation material is fitted on an outer circumferential part of the fuselage through a hook-and-loop fastener having hooks and loops engaging with each other.

15 . A fuselage cooling structure of the aircraft according to claim 1 comprising:
an outer heat insulation material disposed, from the outside of a fuselage, in a corresponding region of the fuselage which corresponds to a heat generation part installed on the outside of the fuselage and covered with a fairing; and
an inner heat insulation material disposed around the corresponding region on the inside of the fuselage.

Assignees

• Mitsubishi Aircraft Corp

Inventors

• Hara Nobuhide
• Yamada Osamu

Classifications

• B64C1/38 Primary

  Constructions adapted to reduce effects of aerodynamic or other external heating · CPC title

• B64C7/00

  Structures or fairings not otherwise provided for · CPC title

• B64C1/066

  Interior liners · CPC title

• B64D13/00

  Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space · CPC title

• Y02T50/50

  On board measures aiming to increase energy efficiency · CPC title