Nonstop Mars Sample Return System Using Aerocapture Technologies

Fujita, Kazuhisa; Tachibana, Shogo; Sugita, Seiji; Miyamoto, Hirdy; Mikouchi, T.; Suzuki, Toshiyuki; Takayanagi, Hideaki; Ozawa, Takashi; Kawaguchi, Jun; Woo, Hanwool

doi:10.2514/6.2009-5614

Cited by 30 publications

(13 citation statements)

References 3 publications

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“…Fujita et al [6] and Ozawa et al [7] investigated the feasibility of a Mars nonstop dust sample-return mission. They used several heattransfer models in order to examine the temperature elevation of dust particles flying in the shock layer.…”

Section: Introductionmentioning

confidence: 99%

“…Sampling such dust particles and bringing them back to Earth will be scientifically valuable because such dust particles are expected to contain global geological information of the Martian surface. In the aeroflyby sample-return mission [2][3][4][5][6], the flyby velocity of the capsule will be hypersonic at an altitude of 35 to 45 km. Therefore, strong shock waves will be formed around the vehicle, and dust particles can be melted or their chemical composition altered due to the high temperature in the shock layer.…”

Section: Introductionmentioning

confidence: 99%

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Study of Capsule Geometry for Dust Sample Acquisition During Mars Atmospheric Entry

Ogino

Terata

Nakajima

et al. 2015

Journal of Spacecraft and Rockets

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This paper explores an appropriate position for the dust-capturing device on the surface of an aeroflyby capsule traveling at a velocity of 4.4 km∕s in the Martian atmosphere at an altitude of 36 km. The equation of motion and the heat-transfer equation for dust particles are solved for particle sizes of 0.5 and 0.1 μm. A thermochemical nonequilibrium flowfield over the vehicle is computed using a prismatic unstructured mesh method. Analysis indicates that placing a dust-capturing device on the leeward frustum edge results in less aerodynamic drag and lower surface heat flux than placing the same device on the windward frustum edge. The lower heat flux exerted on the surface of the dust-capturing device is preferable because the aerogel on the surface of the device is less damaged. The temperature of dust particles of 0.5 μm diameter is elevated to almost the phase-change temperature when the dustcapturing device is on the leeward frustum edge, due to longer flight time in the high-temperature shock layer. The temperature of dust particles reaching the device on the windward frustum edge is well below the phase-change temperature. However, this study could not find any position to capture dust particles of 0.1 μm diameter before reaching the phase-change temperature, regardless of the position of the dust-capturing device. Nomenclature= pitching moment coefficient c = specific heat capacity, J∕kg · K F g = gas force exerted on dust particle, N M = Mach number m = mass, kg Nu = Nusselt number Pr = Prandtl number p = pressure, Pa Q = transferred energy, J Re = Reynolds number r d = radius of dust particle, m T = temperature, K u R = fluid velocity relative to dust particle, m∕s V d = volume of dust particle, m 3 v = particle velocity, m∕s γ = specific heat ratio λ = thermal conductivity, W∕m · K ν = kinematic viscosity, m 2 ∕s ρ = density, kg∕m 3Subscripts ad = adiabatic d = dust g = gas inc = incompressible R = relative Superscript cont = continuum

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Study of Capsule Geometry for Dust Sample Acquisition During Mars Atmospheric Entry

Ogino

Terata

Nakajima

et al. 2015

Journal of Spacecraft and Rockets

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“…[1][2][3] In these missions, spacecraft are exposed to severe heat loads by aerodynamic heating. Arc-heated wind tunnels have been widely used to simulate these entry environments on the ground because of their high heat flux density as well as its high particle speed, high temperature and large flow area.…”

Section: Introductionmentioning

confidence: 99%

Application of Two-Photon Absorption Laser-Induced Fluorescence to Atomic Species in the JAXA 750 kW Arc-Heated Wind Tunnel

Takayanagi

Mizuno

Fujii

et al. 2014

Trans. Japan Soc. Aero. S Sci.

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Two-photon absorption laser induced fluorescence (TALIF) is applied to atomic oxygen and nitrogen generated in the JAXA 750 kW arc-heated wind tunnel in order to obtain velocity, translational temperature and atomic number density distributions. Free stream velocity is estimated by Doppler shift and the translational temperature distributions are deduced from spectral broadening. The absolute center excitation wavelength and laser line width are estimated with the TALIF profiles from a static reference cell which is called as a flow reactor. In this flow reactor, atomic species are generated by microwave discharge. The spatial distributions of atomic number density are deduced from the integrated TALIF profiles. The absolute atomic number densities inside the flow reactor are estimated with a titration method. From the mass fraction estimation, it is found that the number densities of atomic oxygen are overestimated owing to the saturation effect. When oxygen is assumed to be totally dissociated, the fractional enthalpies are estimated.

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“…1) In Japan, a feasibility study of a Martian aerocapture demonstrator of small dimension was conducted for the purpose of opening a new frontier of space transportation in planetary explorations, 2) and now a Mars Exploration for Live Organisms Search (MELOS) by use of an atmospheric entry-descent-landing system and a rover is currently entertained for launch in 2018. 3) In addition, a nonstop Mars sample return mission using the aerocapture technique, which is called as Mars Aero-flyby Sample Collection (MASC), 4) has been also investigated. In these missions, mass of Thermal Protection Systems (TPS) for the protection of the aeroshell from the aerodynamic heating should be minimized.…”

Section: Introductionmentioning

confidence: 99%

VUV and IR Radiation Measurement in Mars Simulant Gas with Hyper Velocity Shock Tube

Takayanagi

Fujita

2014

AEROSPACE TECHNOLOGY JAPAN

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Ultraviolet and mid-infrared radiations behind shock wave in Mars simulant gases are detected in order to expect the radiative heating for future Mars missions. According to the CFD calculation coupled with the radiation analysis code, SPRADIAN2, for a small-sized Martian aerocapture demonstrator, the radiation intensity from VUV wavelength region is dominant in the forebody region, while that from mid-IR wavelength region is dominant in the aftbody region. In VUV region, the absolute spectral radiances from CO 4 th positive band are evaluated by the absolute intensity calibration with a Deuterium lamp from 6.0 to 7.5 km/s. By fitting these profiles with Planck curves, equilibrium temperatures are estimated.The experimental values are less than 5% lower than the simulated ones. In mid-IR wavelength region, time histories of the radiation intensity from CO 2 ro-vibrational modes are measured by an InSb photovoltaic detector from 2.5 to 7.5 km/s. From the comparison of the relative values in equilibrium region, the IR radiation is highest at around 3.5 km/s and lowest at around 6 km/s.

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Nonstop Mars Sample Return System Using Aerocapture Technologies

Cited by 30 publications

References 3 publications

Study of Capsule Geometry for Dust Sample Acquisition During Mars Atmospheric Entry

Study of Capsule Geometry for Dust Sample Acquisition During Mars Atmospheric Entry

Application of Two-Photon Absorption Laser-Induced Fluorescence to Atomic Species in the JAXA 750 kW Arc-Heated Wind Tunnel

VUV and IR Radiation Measurement in Mars Simulant Gas with Hyper Velocity Shock Tube

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