Numerical Investigation of the Re-entry Flight of Hayabusa and Comparison to Flight Data

Loehle, Stefan; Brandis, Aaron M.; Hermann, Tobias; Peter, Johannes M. F.

doi:10.2514/6.2012-3102

Cited by 33 publications

(14 citation statements)

References 14 publications

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“…All experimental results presented here have been measured in a flow condition corresponding to a Hayabusa reentry trajectory point at 78.8 km altitude with a velocity of 11.7 km∕s [32]. This ground testing flow condition was set according to the concept of the local heat transfer simulation, which related a subsonic boundary layer to a hypersonic real flight condition [33].…”

Section: Facility Overviewmentioning

confidence: 99%

Characterization of a Reentry Plasma Wind-Tunnel Flow with Vacuum-Ultraviolet to Near-Infrared Spectroscopy

Hermann

Löhle

Zander

et al. 2016

Journal of Thermophysics and Heat Transfer

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This paper presents the analysis of optical emission spectroscopic measurements from vacuum ultraviolet (120 nm) to near infrared (960 nm) in a high-enthalpy air plasma flow corresponding to superorbital reentry conditions. The vacuum ultraviolet measurements have been realized with a new experimental setup allowing measurements through a bore hole in the sample. Using the commonly applied optical emission spectroscopy from the side, the radiation transport along the line of sight of the vacuum ultraviolet measurements has been assessed. This allowed the determination of the local ground state densities of atomic oxygen and atomic nitrogen from a branching ratio analysis and the blackbody limiting correction of the vacuum ultraviolet radiation. Through the analysis of the absorption in the borehole, the spectra have been corrected, resulting in a stagnation point radiative heat flux in the vacuum ultraviolet of 235 kW∕m 2 .= local mass-specific enthalpy, MJ∕kg I = arc current, A K = proportionality constant for air, W∕MJ∕kg·Pa 0.5 ·m 1.5 k = Boltzmann constant, J∕K k cal = calibration factor, W∕m 2 · nm · sr∕counts∕s L λ = spectral radiance, W∕m 2 · nm · sr L λ;Limit = blackbody limit spectral radiance, W∕m 2 · nm · sr M = magnification _ m = mass flow, g∕s n = number density, m −3 n i = excited state population density, m −3 n 0 = ground state population density, m −3 P = electric power, kW P k = spectral line shape, nm −1 p = pressure, hPa _ q = heat flux, kW∕m 2 R eff = effective nose radius, mm r = radial distance, mm S = raw signal, counts/s s = distance from the probe surface, mm s 0 = distance between object and focusing element, mm= vibrational quantum number x = axial distance from the nozzle, mm y = horizontal distance from the nozzle, mm z = vertical distance from the nozzle, mm α λ = absorption coefficient, m −1 δ = full width at half-maximum of line broadening, nm ε λ = emission coefficient, W∕m 3 · nm · sr ε = spectrally integrated emission coefficient, W∕m 3 · sr λ = wavelength, nm σ λ = absorption cross section, m 2 Subscripts BB = blackbody DL = deuterium lamp exc = electronic excitation IS = integrating sphere l = lower state rot = rotational tot = total trans = translational u = upper state vib = vibrational

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Section: Facility Overviewmentioning

confidence: 99%

Characterization of a Reentry Plasma Wind-Tunnel Flow with Vacuum-Ultraviolet to Near-Infrared Spectroscopy

Hermann

Löhle

Zander

et al. 2016

Journal of Thermophysics and Heat Transfer

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“…[3][4][5][6][7] The testing logic is to reproduce the stagnation line boundary layer aerothermochemistry of the flight in the ground based facility. 8,9 Therefore, local physical parameters of the flow need to be assessed, such as local mass-specific enthalpy and spatially resolved boundary layer temperatures and number densities. Furthermore, the material behavior under this heat load needs to be investigated.…”

Section: Introductionmentioning

confidence: 99%

Review of Heat Flux Measurements for High Enthalpy Flows

Löhle

2016

32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference

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This article reviews heat flux measurement devices for high enthalpy flows as used in plasma wind tunnel facilities. Only heat flux gages measuring heat flux on cold copper surfaces are considered. The steady state water-cooled calorimeter, the Gardon gage sensor, slug calorimetry and swept nullpoint calorimetry are described. Based on published data and sensor heritage the various designs in Europe and the US are reviewed and analyzed. The paper ends with some remarks on comparability testing in different facilities.

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“…Several mission-oriented velocity gradient scaling approaches, all for spherical-nosed axisymmetric vehicles, as the one presented in [23] for the Hayabusa capsule or the one used in [24] in the full-scale testing approach of the small capsule SPRITE for supersonic arcjet testing, were used in the past. However, these approaches always apply to spherical-nosed axisymmetric vehicles.…”

Section: B Velocity Gradient Determination and Considerationsmentioning

confidence: 99%

Hypersonic Aerothermochemistry Duplication in Ground Plasma Facilities: A Flight-to-Ground Approach

Sakraker

Turchi

Chazot

2015

Journal of Spacecraft and Rockets

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High conservative safety margins, applied to the design of spacecraft thermal protection systems for planetary entry, need to be reduced for higher efficiency of future space missions. Ground testing of such protection systems is of great importance during the design phase. This study covers a methodology for simulating the complex hypersonic entry aerothermochemistry in a plasma wind tunnel for a given spacecraft geometry without any assumption on axisymmetry or bluntness. A demonstration of this proposed methodology is made on the Qubesat for Aerothermodynamic Research and Measurements on AblatioN, QARMAN mission, which is a rectangular reentry CubeSat with a cork-based ablative thermal protection system in the front unit. The reacting boundary-layer profiles of the hypersonic entry probe compare well with the ones developing at the stagnation region of the plasma test model, defined with the proposed flight-to-ground duplication method.

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Numerical Investigation of the Re-entry Flight of Hayabusa and Comparison to Flight Data

Cited by 33 publications

References 14 publications

Characterization of a Reentry Plasma Wind-Tunnel Flow with Vacuum-Ultraviolet to Near-Infrared Spectroscopy

Characterization of a Reentry Plasma Wind-Tunnel Flow with Vacuum-Ultraviolet to Near-Infrared Spectroscopy

Review of Heat Flux Measurements for High Enthalpy Flows

Hypersonic Aerothermochemistry Duplication in Ground Plasma Facilities: A Flight-to-Ground Approach

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