|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02K-007/10 F02K-007/00 F02K-009/78 F02K-009/00|
|미국특허분류(USC)||060/204; 060/225; 060/768; 060/769; 102/377|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 1 인용 특허 : 5|
In accordance with a first aspect of the present invention, an aircraft having a scramjet engine is provided. The scramjet engine includes a flowpath which varies in three dimensions. In accordance with a second aspect of the present invention, a method for launching an aircraft having a scramjet engine with a nozzle section and a solid rocket booster positioned within the nozzle section is provided. The method includes the steps of igniting the solid rocket booster to accelerate the aircraft to a speed at which the scramjet engine can operate, clearing ...
What is claimed is: 1. An aircraft having an annular body forming an internal volume and a scramjet engine within said internal volume, said scramjet engine including a semiannular flowpath which varies in three dimensions from an inlet portion to a nozzle section, said flowpath being formed by a curved section of an inner wall of the aircraft body, an internal wall spaced from said inner wall, and two side walls within said internal volume extending between said internal wall and said inner wall, and said flowpath having a concave configuration at an i...