The Combined Sensor System COMPARE for SHEFEX II

Preci, Arianit; Herdrich, Georg; Auweter‐Kurtz, Monika

doi:10.2514/6.2009-7264

Cited by 3 publications

(2 citation statements)

References 4 publications

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“…SHEFEX II consists of 40 flat TPS panels in segments B through E, made from identical raw material plates. The set-up has the advantage of being able to integrate experiments from potential clients with one single interface specification [34][35][36][37].…”

Section: International Journal Of Aerospace Engineeringmentioning

confidence: 99%

Hot Structure Flight Data of a Faceted Atmospheric Reentry Thermal Protection System

Boehrk

Weihs

Elsäßer

2019

International Journal of Aerospace Engineering

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The second sharp-edged flight experiment is a faceted suborbital reentry body that enables low-cost in-flight reentry research. Its faceted thermal protection system consisting of only flat radiation-cooled thermal protection panels is cost-efficient since it saves dies, manpower, and storage. The ceramic sharp leading edge has a 1 mm nose radius in order to achieve good aerodynamic behaviour of the vehicle. The maximum temperature measured during flight was 867°C just before transmission ended and was predicted with an accuracy of the order of 10%. The acreage thermal protection system is set up by 3 mm fiber-reinforced ceramic panels isolated by a 27 mm alumina felt from the substructure. The panel gaps are sealed by a ceramic seal. Part of the thermal protection system is an additional transpiration-cooling experiment in which nitrogen is exhausted through a permeable ceramic matrix composite to form a coolant film on the panel. The efficiencies at the maximum heat flux are 58% on the porous sample and 42% and 30% downstream of the sample in the wake. The transient load at each panel location is derived from the trajectory by oblique shock equations and subsequent use of a heat balance for both cooled and uncooled structures. The comparison to the heat balance HEATS reveals heat sinks in the attachment system while the concurrence with the measurement is good with only 8% deviation for the acreage thermal protection system. Aerodynamic control surfaces, i.e., canards, have been designed and made from a hybrid titanium and ceramic matrix composite structure.

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Section: International Journal Of Aerospace Engineeringmentioning

confidence: 99%

Hot Structure Flight Data of a Faceted Atmospheric Reentry Thermal Protection System

Boehrk

Weihs

Elsäßer

2019

International Journal of Aerospace Engineering

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“…In 2012, SHEFEX II has been established, it focuses on hypersonic flight control using steerable canard fins and new TPS concepts. By comparing the results of these two experiments and the results of computer simulations, a lot of researches of sharp-edge re-entry vehicles have been made in aero thermo-dynamics [1][2][3][4], aerodynamics, flight dynamics [5][6][7], flight control, structure design [8,9], subsystem design [10][11][12][13].…”

Section: Introductionmentioning

confidence: 99%

Design, Modeling and Analysis of a Sharp-edge Hypersonic Stealthy Re-entry Vehicle

Liu¹,

Li²,

Xiang³

et al. 2015

Procedia Engineering

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In 2005 and in 2012, the SHarp Edge Flight EXperiment SHEFEX I and SHEFEX II of DLR have been established. Low lift-todrag ratio of them limits active control ability. This paper studies on a sharp-edge stealthy re-entry vehicle with high lift-to-drag ratio. The focus will be laid upon designing and modeling of a sharp-edge stealthy re-entry vehicle by analyzing of lift-to-drag ratio and center of gravity, and also upon stealth performance researches. All aerodynamic performance analysis are based on Modified Newtonian Theory, it's proved to be more precise for a sharp-edge hypersonic re-entry vehicle relative to the Piston Theory and Shock-Expansion Method. A procedure based on physical optics and method of equivalent currents for radar cross section calculation. As result, the configuration and the center of gravity are determined, and a good stealth performance is demonstrated.

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