Abstract
This paper addresses a detailed preliminary design study of a twin fuselage semi-reusable TSTO launch vehicle. This double fuselage carrier, which would use hydrogen as a fuel, also collects the liquid oxygen (LOX), needed afterwards to propel the all-rocket orbiter. This collection takes place during an extended subsonic cruise phase that precedes the air launch of the orbiter. The concept of this 3 generation semi-reusable launch vehicle will be explained and the results from a detailed preliminary design with the AAA (Advanced Aircraft Analysis) software from Darcorp (USA) will also be given. The results for the aircraft weight distribution will be given as well as performance, aerodynamics and longitudinal stability indications for two reference missions. Besides that, the influence of the collection ratio obtained with the LOX collection plant upon the design of the launch vehicle is also addressed.
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