U.S. Patent Specifications

Abstract

In an aircraft, a gas turbine having a truncated tail cone over which turbine effluent flows, the small end of said truncated tail cone being open and directed rearwardly, and a rocket motor within said truncated tail cone and issuing its effluent through the rearward open small end thereof, said rocket motor having selectively operable liquid fuel and liquid oxidizer feed mechanisms driven by said gas turbine and disposed within said tail cone and forward of said rocket motor.

Citation

(1955), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 27 No. 12, pp. 426-426. https://doi.org/10.1108/eb032645