Key Experiments within the Shefex II Mission
- Paper number
IAC-08.D2.6.4
- Author
Mr. Hendrik Weihs, Deutsches Zentrum für Luft und Raumfahrt e.V. (DLR), Germany
- Coauthor
Dr. José Longo, Germany
- Coauthor
Mr. John Turner, Deutsches Zentrum für Luft und Raumfahrt e.V. (DLR), Germany
- Year
2008
- Abstract
Within the SHEFEX flight test programme, the German Aerospace Center focuses on the development for re-entry and hypersonic technology. Using adapted sounding rocket systems as used for micro gravity research it is possible to perform cost effective flight tests in a short time period. Thus, besides material or structural testing of hardware, the comparison of real flight data with numerical simulations and ground test results is very important to adjust and verify simulation tools and the plausibility of ground test results. After a successful flight of the first sharp edge flight experiment SHEFEX I at October 27th 2005 the next mission is under preparation. During the 20 sec flight at Ma 6 of SHEFEX I a complete set of valuable aerodynamic data could be obtained. Thus, this kind of flight testing and all experience got up to now will be used to answer new scientific questions and to enlarge the flight envelope by doubling the mach number and re-entry duration within the SHEFEX II mission. Launched by a Brazilian two staged sounding rocket system SHEFEX II will be a consequent next step in technology test and demonstration. Considering all experience and collected flight data obtained during the SHEFEX I Mission, the test vehicle will be enlarged and extended by an active control system, which allows active aerodynamic control during the re-entry phase. Thus, besides the facetted ceramic thermal protection system, ceramic based aerodynamic control elements (canards), mechanical actuators and an automatic flight control unit will be implemented as key technology experiments. In addition, supporting subcomponents like different inertial platforms and a star tracker sensor are part of the GNC system of SHEFEX II to provide accurate data related to position and orientation of the vehicle. In addition, some other experiments including an actively cooled thermal protection element, advanced sensor equipment for temperature, heat flux and pressure, high temperature antenna inserts etc. are intended to fly with SHEFEX II. From national and international companies and universities some passenger experiments will be integrated to investigate and demonstrate advanced metallic and ceramic based thermal protection elements, new fiber optic sensors and a sensor system package, which was developed for ESA’s EXPERT mission. Using a special arrangement of the forward pressure sensors a hypersonic Flush air data system will be integrated at the payload tip as a passive experiment. This is to evaluate such a system and advanced algorithms for active control during hypersonic flight within future missions. Shefex II is one more step forward within DLR’s roadmap for the development of hypersonic and re-entry technology. A first application is planned within the Returnable Experiment REX. Such a system shall provide a free flying platform with a high micro g quality for a few days. The return capability, active aerodynamic control during re-entry and the special container technique derived from sounding rocket experiment set up shall provide a cost effective and easy access for experimenters.
- Abstract document
- Manuscript document
IAC-08.D2.6.4.pdf (🔒 authorized access only).
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