초록 ▼

The flight vehicle includes an elongated central body having a central axis defined therein and a circumference. A plurality of elongated portions are positioned about the central body. A plurality of airbreathing engines are axisymetrically positioned about the central axis of the central body and

The flight vehicle includes an elongated central body having a central axis defined therein and a circumference. A plurality of elongated portions are positioned about the central body. A plurality of airbreathing engines are axisymetrically positioned about the central axis of the central body and between the respective elongated portions. Each flowpath includes a forebody, an inlet, an isolator duct, a combustor, a nozzle, and a mechanism for injecting fuel into the combustor. The forebody externally compresses the air flow. The inlet is downstream of the forebody to capture air flow. The isolator duct is downstream of the inlet to further reduce velocity of the air flow. The combustor is downstream of the isolator duct and finally, the nozzle is downstream of the combustor. The fuel/air mixture is burned in the combustor and expanded in the nozzle for providing thrust. A control mechanism is positioned about the central body for providing control of the flight vehicle. The axisymetric relationship of the engines relative to the central body provides balanced forces in flight and simplifies the integration of the present invention into guns and launch tubes.

대표청구항 ▼

[ What is claimed is:] [1.] An airbreathing propulsion assisted flight vehicle, comprising:a) an elongated central body having a central axis defined therein and a circumference;b) a plurality of elongated portions positioned about said central body and extending substantially the length of said cen

[ What is claimed is:] [1.] An airbreathing propulsion assisted flight vehicle, comprising:a) an elongated central body having a central axis defined therein and a circumference;b) a plurality of elongated portions positioned about said central body and extending substantially the length of said central body;c) a plurality of airbreathing engines axisymetrically positioned about said central axis around the circumference of said central body and between and adjacent to respective elongated portions, said engines sharing a common forebody for externally compressing airflow, each engine comprising:i) an inlet downstream said forebody for the capture of air flow;ii) an isolator duct downstream said inlet to reduce the velocity of said air flow;iii) a combustor downstream said isolator duct;iv) nozzle means downstream said combustor for expanding combustion products; andv) means for injecting fuel into said combustor, wherein the fuel air mixture is burned in said combustor and expanded in said nozzle means for providing thrust; andd) control means positioned about said central body for providing control of said flight vehicle, wherein each engine's flowpath cross-sectional area dimensions at specific positions along the length of each engine are present to define the adjacent elongated portion cross-sectional area dimensions at commensurate positions along the length.