Investigation of Structure, Thermal Protection System, and Passenger Stage Integration for the Hypersonic Transport System SpaceLiner

Abstract

Suborbital high speed transport is a technology that could significantly impact space transportation, since mass production of rocket propelled aircraft and their engines, as well as operating them on a routinely basis, promises reductions in the manufacturing and launching costs for space launchers. With this vision in mind, the SpaceLiner concept was developed in the Space Launcher Systems Analysis group (SART) of DLR in 2005. Since then, the original design has evolved into several successive configurations. The latest configuration 7-2 is shown in Fig. 1. Currently, the configuration 7-3 is under definition. Various papers have been published about the SpaceLiner or its subsystems, for instance Ref. 1 and Ref. 2 as some of the latest ones. The SpaceLiner is a two staged, rocket propelled and vertical lift off passenger transport aircraft. The reference mission is to carry 50 passengers from Europe to Australia or vice versa within just 90 minutes. The SpaceLiner system is composed of a winged, passenger carrying main stage also denominated orbiter, and a winged booster. Both stages are liquid oxygen (LOX) and liquid hydrogen (LH2) propelled, and fully reusable. After booster separation, the orbiter continues the ascent with its own rocket engines until main engine cut-off (MECO) at an altitude of around 75 km. Subsequently, the range flight is being performed in gliding mode, whereas Mach numbers of up to 24 are reached.