|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/117A ; 244/121 ; 244/124|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 1 인용 특허 : 5|
The invention relates to a system for removing the heat that is incident upon an aircraft, and especially a supersonic aircraft, during flight. The incident heat is generated by the constant heating effect of aerodynamic friction on the outer skin of the fuselage, by compression heating at the ram or stagnation point and stagnation edges of the aircraft fuselage, and by the heating of external air as it is compressed to cabin pressure. In the present system, the used cabin air is exhausted out of the cabin through a space between the cabin interior panel...
[ What is claimed is:] [1.] In an aircraft having a fuselage with an outer skin, at least one cabin interior panel arranged in said fuselage to bound a pressurized cabin in said aircraft, and a wing extending from said fuselage; an improved system for removing from said aircraft heat generated by at least one of aerodynamic friction heating of said fuselage outer skin, compression heating at a stagnation point and a stagnation edge of said fuselage outer skin, compression heating of cabin air that is compressed to a pressure level of said pressurized cab...