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pro vyhledávání: '"SHEFEX II"'
Akademický článek
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Publikováno v:
Journal of Spacecraft and Rockets. 53:153-177
The aerothermal instrumentation of the Sharp Edge Hypersonic Flight Experiment SHEFEX-II, which was launched from Andoya Rocket Range on top of a two-stage rocket configuration, provided very useful flight data. Complementary to the pressure data, he
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::19a4c7aa66b1b978997711886a10b738
https://doi.org/10.2514/1.a33275
https://doi.org/10.2514/1.a33275
Autor:
Hannah Böhrk
Publikováno v:
Journal of Spacecraft and Rockets. 52:674-683
The present paper presents the in-flight measurement of the transpiration cooling experiment Aktive Kuhlung durch Transpiration im Versuch (often referred to as AKTiV) flown on the suborbital reentry configuration Sharp Edge Flight Experiment II (oft
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::01be40ee6dbf4306ffd2b294cd1631a4
https://doi.org/10.2514/1.a33144
https://doi.org/10.2514/1.a33144
Autor:
Markus Kuhn, Thomas Reimer
A ceramic matrix composite thermal protection system test article was subjected to a dynamic load environment to determine its lifetime. The test article consisted of one panel made from the ceramic matrix composite and the corresponding structural i
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::dff1d44484e721f3e91984b8e1d0a7f8
https://elib.dlr.de/99180/
https://elib.dlr.de/99180/
Autor:
Sven Lorenz, Andreas Bierig
Publikováno v:
AIAA Guidance, Navigation, and Control (GNC) Conference.
This paper presents the simulation based robustness analysis w.r.t. parameters and initial conditions, related to the hypersonic flight experiment called SHEFEX-II. The robustness criteria and the parameter limits are obtained from the nominal missio
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::b09f8f3dc61fbaecc96f3e453f30fc41
https://doi.org/10.2514/6.2013-4857
https://doi.org/10.2514/6.2013-4857
The mission architecture of SHEFEX II features a two-stage solid propellant sounding rocket vehicle on a suppressed trajectory, which is induced by a cold gas pointing maneuver of the vehicle before second stage ignition. The impact point is subject
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=od______1640::edc8c79dd3d39b53ac84e26ad1d90d97
https://elib.dlr.de/82127/
https://elib.dlr.de/82127/