DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Flight Instrumentation for the SHEFEX II Re-Entry Mission

Thiele, Thomas and Siebe, Frank and Gülhan, Ali (2009) Flight Instrumentation for the SHEFEX II Re-Entry Mission. In: Proceedings of the 6th European Workshop Thermal Protection Systems and Hot Structures. 6th European Workshop on Thermal Protection Systems and Hot Structures, 01. - 03.04.2009, Stuttgart, Deutschland.

Full text not available from this repository.


For a low cost access to space with a high level of reliability, the design cycle duration has to be reduced and the service and refurbishment of the space vehicle have to be simplified. A complex geometry of the TPS components of operational space vehicles like the Space Shuttle leads to expensive manufacturing and maintenance processes. TPS structures consisting of flat ceramic panels could be a realistic solution to reduce the costs and improve the aerodynamic performance of space vehicles. Although ground testing still provides the main design data, a complete simulation of the flight conditions is often not possible. Therefore flight experiments are the most effective tool to obtain validation data for the design under real conditions. To test these new sharp edged TPS structures (flat tiles) the DLR successfully performed the SHEFEX I flight experiment and is now preparing a second flight experiment SHEFEX II in 2010 [1]. The SHEFEX II flight configuration includes more than 100 sensors and a new type of Flush Airdata Sensing (FADS) System for the sharp edged configuration, which will be tested during flight and pre-flight qualification tests. Using a two staged sounding rocket system the experiment time is increased up to 60 seconds and the maximum flight Mach number will be about 11. An active steering system using four canards is used for a controlled re-entry varying the roll angle and angle of attack. This paper presents the instrumentation of the ceramic thermal protection system (TPS) consisting of 40 flat ceramic tiles and a massive ceramic nose which form the SHEFEX II forebody. Fig. 1 illustrates the complete configuration including the SHEFEX II payload and the two staged launcher.

Item URL in elib:https://elib.dlr.de/62928/
Document Type:Conference or Workshop Item (Speech)
Title:Flight Instrumentation for the SHEFEX II Re-Entry Mission
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Date:April 2009
Journal or Publication Title:Proceedings of the 6th European Workshop Thermal Protection Systems and Hot Structures
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:Flight Instrumentation, SHEFEX II, Re-Entry, TPS structures
Event Title:6th European Workshop on Thermal Protection Systems and Hot Structures
Event Location:Stuttgart, Deutschland
Event Type:international Conference
Event Dates:01. - 03.04.2009
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:Space
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):W - Grundlagen Raumtransport - Innovativer Thermalschutz (old)
Location: Köln-Porz , Braunschweig , Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Supersonic and Hypersonic Technology
Deposited On:25 Jan 2010 14:31
Last Modified:28 Nov 2012 14:04

Repository Staff Only: item control page

Help & Contact
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.