Analysis of Air-Launched and Vertical-Launched Configurations of a Solid Propulsion Hypersonic Demonstrator
Gangnery, F. and Burkhardt, H. (2003) Analysis of Air-Launched and Vertical-Launched Configurations of a Solid Propulsion Hypersonic Demonstrator. Project Report, DLR-Interner Bericht. 647-2003/01, 67 S.
Full text not available from this repository.
A possible next step in the German space program ASTRA is a winged, unmanned experimental vehicle to demonstrate necessary technologies for reusability. The Phoenix 2, a proposal of ASTRIUM/Bremen, is one potential demonstrator vehicle. However the cost of this vehicle is assumed to be considerably high because of the use of liquid propulsion. DLR SART started therefore investigations to identify alternative, more cost efficient solutions using solid propulsion. The main requirements for a solid propulsion experimental vehicle are: o a maximum speed between Mach 4 and Mach 8 o a maximum altitude between 40 km and 90 km, o a gross mass of about 12 tons and an empty masse of about 4 tons, o a horizontal landing in order to use the automated landing techniques demonstraated by Phoenix 1. Concepts for such a future vehicle are investigated in this study. Two launch options are considered: Air-Launch from a carrier aircraft and vertical launch from ground.
|Document Type:||Monograph (Project Report, DLR-Interner Bericht)|
|Title:||Analysis of Air-Launched and Vertical-Launched Configurations of a Solid Propulsion Hypersonic Demonstrator|
|Number of Pages:||67|
|HGF - Research field:||Aeronautics, Space and Transport|
|HGF - Program:||Space|
|HGF - Program Themes:||W RP - Raumtransport|
|DLR - Research area:||Space|
|DLR - Program:||W RP - Raumtransport|
|DLR - Research theme (Project):||E -- no assignement|
|Institutes and Institutions:||Institute of Space Propulsion|
|Deposited By:||Monika Lohmiller|
|Deposited On:||16 Sep 2005|
|Last Modified:||06 Jan 2010 14:02|
Repository Staff Only: item control page