Engineering Design of Engine/Airframe Integration for the SAENGER Fully Reusable Space Transportation System.

摘要

In Germany the Ministry of Research and Technology (BMFT) initiated in 1986 study work at industry focused on 'Determining of the principal features and results as Starting Points for German Industry in the Development of Future Hypersonic Transport-Aircraft with a view to Possible Hypersonic Aircraft Projects. Then, after the start of the newly initiated German Hypersonics Technology Programme in 1987 the Two-Stage-To-Orbit (TSTO) transportation system became the reference concept of the German Hypersonics Technology Program. The new concept adopted the simplified denomination SANGER II. An overview on the concept study work having been done within an international design team will be discussed with specific emphasis on the selection of the combined cycle engine concept, the propulsion operational modes and the results of the engine/airframe integration. Major experimental (EFD) and computational (CFD) results from the detailed intake, combustion chamber and nozzle design will be shown. For the experimental proof of the performance of the operational combined cycle (turbo-ram/scram) engine system under real environmental conditions several flying testbeds had been pursued together with Russian partner companies. The major achievements and 'lessons learned' will be discussed.