초록 ▼

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 conditio

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.

대표청구항 ▼

1. An aircraft comprising: a fuselage;a heat generation part installed on an outside circumferential surface of the fuselage, the heat generation part positioned adjacent a corresponding region of the fuselage, the corresponding region having a first shape;a fairing covering the heat generation part

1. An aircraft comprising: a fuselage;a heat generation part installed on an outside circumferential surface of the fuselage, the heat generation part positioned adjacent a corresponding region of the fuselage, the corresponding region having a first shape;a fairing covering the heat generation part;an inner heat insulation material disposed on an internal circumferential surface of the fuselage;an aperture formed in the inner heat insulation material, the aperture being aligned with the corresponding region of the fuselage; andan outer heat insulation material disposed on the outside circumferential surface of the fuselage and adjacent to the corresponding region 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 at least in a space adjacent to the aperture, the space being inside of the fuselage. 3. The aircraft according to claim 1, wherein the corresponding region is exposed toward the inside of the fuselage via the aperture. 4. The aircraft according to claim 1, wherein the inner heat insulation material and the outer heat insulation material are disposed such that the inner and outer heat insulation materials, together, cover an 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 first shape of the corresponding region is defined over a first area, the first area being substantially equal to a second area of the heat generation part projected along the thickness direction of the fuselage. 7. The aircraft according to claim 1, wherein the first shape of the corresponding region is defined over a first area, the first area being larger than a second 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 define the aperture formed in the inner heat insulation material, the end edges 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 a surface area of the corresponding region in contact with air within 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 the outside circumferential surface of the fuselage through a hook-and-loop fastener having hooks and loops engaging with each other. 15. A fuselage cooling structure of an aircraft having a fuselage and a heat generation part disposed adjacent to a corresponding region of the fuselage, the fuselage cooling structure comprising: an inner heat insulation material disposed on an internal circumferential surface of the fuselage;an aperture formed in the inner heat insulation material, the aperture being aligned with the corresponding region of the fuselage; andan outer heat insulation material disposed on an outside circumferential surface of the fuselage and adjacent to the corresponding region, the outer heat insulation material being covered by a fairing. 16. The aircraft according to claim 1, wherein the aperture has a second shape that corresponds to the first shape. 17. The aircraft according to claim 1, wherein the corresponding region, the heat generation part, the aperture, and the outer heat insulation material are all radially aligned with respect to a central axis of the fuselage.