Proposal on application of Russian technical facilities for International Mars Research Program for 2009–2015

Polishchuk, G. M.; Pichkhadze, K. M.; Vorontsov, Victor; Pavel, Kazmerchuk

doi:10.1016/j.actaastro.2006.02.055

Cited by 9 publications

(6 citation statements)

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“…To this end, fully three-dimensional CFD Analyses, both Euler and Navier-Stokes, have been performed in order to address the aerodynamic performance of an Apollo-like capsule for mission exploration to Mars, considering an entry approach scenario to red planet compliant with the spacecraft released from circular orbit [2], [3]. Today the need for research activities on Mars entry are ever more apparent, and among the available technologies, capsule option is still the safest and cheapest way to get exploration vehicle on Mars [4], [5].…”

Section: Figure 1 Typical Fast-transit Interplanetary Trajectory [1]mentioning

confidence: 99%

Aerodynamic Analysis of a Capsule Vehicle for a Manned Exploration Mission to Mars

Viviani

Pezzella²

2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

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The paper deals with the aerodynamic analysis of a manned braking system entering the Mars atmosphere, with the aim to support planetary entry system design studies. The capsule configuration is an axisymmetric blunt body close to the Apollo capsule. Several fully three-dimensional Computational Fluid Dynamics analyses have been performed to assess the flowfield environment around the vehicle to address the aerodynamic performance of the entry capsule within mission exploration to Mars. To this end, a wide range of flow conditions including reacting and non-reacting flow, different angles of attack, and Mach numbers have been investigated and compared. Moreover, non-equilibrium effects on the flowfield around the capsule have been also investigated. Results show that real-gas effects, for all the angles of attach considered, increase both the aerodynamic drag and pitching moment, whereas the lift is only slighted affected. Finally, results comparisons highlight that experimental and CFD aerodynamic findings available for the Apollo capsule in air adequately represent the static coefficients of the capsule in the Mars atmosphere. Nomenclatureforce, N L = Aerodynamic Lift, N M = Mach number / Aerodynamic Moment, Nm P = Pressure, Pa q = Dynamic Pressure, Pa R = Radius of curvature, m Re = Reynolds number S = Reference Area, m 2 Greek symbols α = Angle of attack, deg ρ = Density, kg/m 3 γ = Specific heats ratio Subscripts b = base ref = reference t2 = stagnation point downstream a normal shock w = wall 1 Professor, Chair of Fluid Dynamics, Dipartimento di Ingegneria Aerospaziale e Meccanica (DIAM), antonio.viviani@unina2.it, AIAA Senior Member.

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Section: Figure 1 Typical Fast-transit Interplanetary Trajectory [1]mentioning

confidence: 99%

Aerodynamic Analysis of a Capsule Vehicle for a Manned Exploration Mission to Mars

Viviani

Pezzella²

2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

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“…The results herein provided have been obtained for a Mars entry scenario compliant with an approach to the red planet both by a direct planetary entry and an entry after aerobraking [1]. These results may be used to provide numerical data for understanding the requirements for the human exploration of Mars [2].…”

Section: Introductionmentioning

confidence: 97%

Nonequilibrium computational flowfield analysis for the design of mars manned entry vehicles

Viviani

Pezzella

2013

Progress in Flight Physics

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This paper deals with the aerodynamic exploration analysis of innovative unusual vehicle concepts, suitable for a manned Mars entry, aiming to support design studies of planetary entry systems. In this framework, two lifting body (LB) con¦gurations have been analyzed so far. Several fully three-dimensional (3D) computational §uid dynamics (CFD) analyses, both for a perfect gas model and for a nonequilibrium reacting gas mixture model, have been performed. The §ow¦eld environment past the exploration vehicle for an assigned Mars entry scenario has been addressed. To this end, a wide range of §ow conditions, including di¨erent angles of attack (AoA), various Mach numbers, and Reynolds numbers, have been investigated. Results reported in the paper are useful for providing numerical data for further understanding the §uid dynamics processes, as those of high enthalpy §ow and vehicle shape e¨ects, involved in the design analysis of LB vehicles for the exploration of Mars.

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“…The forthcoming Phobos-Grunt mission to Mars will probably carry a set of semi-hard landing systems for meteorological research that will impact on the Martian surface (MetNet). The MetNet is being developed in collaboration between the Finnish Meteorological Institute (FMI), the Babakin Space Centre (BSC) and the Russian Space Research Institute (IKI) (Harri et al, 1998(Harri et al, , 2003Polishchuk et al, 2006). The United States also intended to investigate the Martian poles with a set of two impacting probes named Deep-Space-2 (Gavit and Powell, 1995).…”

Section: Introductionmentioning

confidence: 99%

Thermal drill sampling system onboard high-velocity impactors for exploring the subsurface of Europa

Weiß

Yung

Kömle

et al. 2011

Advances in Space Research

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Proposal on application of Russian technical facilities for International Mars Research Program for 2009–2015

Cited by 9 publications

References 0 publications

Aerodynamic Analysis of a Capsule Vehicle for a Manned Exploration Mission to Mars

Aerodynamic Analysis of a Capsule Vehicle for a Manned Exploration Mission to Mars

Nonequilibrium computational flowfield analysis for the design of mars manned entry vehicles

Thermal drill sampling system onboard high-velocity impactors for exploring the subsurface of Europa

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