|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/053.B; 244/110.0B; 244/129.4|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 6 인용 특허 : 20|
Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following x0) a region just ahead of the lip x1) substantially to said lip. A non-unif...
We claim: 1. A supersonic aircraft jet engine installation having an inlet cowl assembly comprising: a) said cowl assembly having three separate generally tubular sections, b) said sections including a first forward inlet section that is forwardly translatable, a second bypass section that is forwardly translatable with respect to the first section, and a third section fixed to an engine structure, the forward inlet section having a forward position everywhere openly spaced entirely forwardly of the second section. 2. The cowl assembly of claim 1, wh...