Thermochemical nonequilibrium phenomena are key factors affecting the numerical simulation results of flow fields of Mars rover. In order to make clear the flow field properties of the Mars Pathfinder, a multi-physics numerical model including the Navier–Stokes equations, 11 species and 59 chemical reactions of CO2 plasma, and a four-temperature thermodynamic nonequilibrium model is established in this study. Numerical simulations on the thermal-chemical nonequilibrium flow fields of the Mars Pathfinder spacecraft are performed. The distributions of flow-field parameters such as temperature, pressure, Mach number, molar fractions of CO and CO2 around the Mars Pathfinder at different altitudes are obtained. It is found that there is a subsonic backflow at the rear of the Mars Pathfinder, resulting in slightly higher temperatures than other areas; after the shoulder, the pressure decreases rapidly; as the altitude decreases, the intensity of chemical reactions decreases, and the thermal-chemical nonequilibrium effects gradually weaken. Based on the chemical kinetic model of CO2 we proposed, the numerical simulation of the nonequilibrium flow field of the Mars Pathfinder spacecraft showed good predictive accuracy and application potential, providing reference value for subsequent studies on the thermal-chemical nonequilibrium effects of the Mars Pathfinder spacecraft.
REFERENCES
1.
M.-C.
Druguet
, “
Prediction of the flow field over an orbiter entering the Mars atmosphere
,” Shock Waves
20
, 251
(2010
).2.
B.
Hollis
,
D.
Liechty
,
M.
Wright
,
M.
Holden
,
T.
Wadhams
,
M.
MacLean
, and
A.
Dyakonov
, “
Transition onset and turbulent heating measurements for the mars science laboratory entry vehicle
,” AIAA Paper No. AIAA 2005-1437, 2005
.3.
Y.
Yang
,
V. R.
Petha Sethuraman
, and
J. G.
Kim
, “
Effect of equilibrium constant for carbon dioxide recombination in hypersonic flow analysis
,” Case Stud. Therm. Eng.
45
, 102947
(2023
).4.
X.
Yang
,
W.
Tang
, and
Y.-W.
Gui
, “
Hypersonic flow field prediction and aerodynamics analysis for MSL entry capsule
,” J. Astronaut.
36
, 383
(2015
).5.
A.
Viviani
and
G.
Pezzella
, “
Aerodynamic analysis of a capsule vehicle for a manned exploration mission to Mars
,” AIAA Paper No. AIAA 2009-7386, 2009
.6.
W. H.
Willcockson
, “
Mars Pathfinder heatshield design and flight experience
,” J. Spacecr. Rockets
36
(3
), 374
(1999
).7.
L.
Dongjun
et al, “
Measurement and numerical simulation of flow field parameters of free flight spheres with flight velocity from 5 to 7 km/s in CO2
,” J. Exp. Fluid Mech.
34
, 29
(2020
).8.
M.
Wright
,
K.
Edquist
,
C.
Tang
,
B.
Hollis
,
P.
Krasa
, and
C.
Campbell
, “
A review of aerothermal modeling for Mars entry missions
,” AIAA Paper No. AIAA 2010-443, 2010
.9.
M.
Sharma
,
A. B.
Swantek
,
W.
Flaherty
,
J. M.
Austin
,
S.
Doraiswamy
, and
G. V.
Candler
, “
Experimental and numerical investigation of hypervelocity carbon dioxide flow over blunt bodies
,” J. Thermophys. Heat Transfer
24
, 673
(2010
).10.
R. A.
Mitcheltree
and
P. A.
Gnoffo
, “
Wake flow about the Mars Pathfinder entry vehicle
,” J. Spacecr. Rockets
32
, 771
(1995
).11.
M. G.
Dunn
and
S.-W.
Kang
, “
Theoretical and experimental studies of reentry plasmas
,” Technical Report No. NASA-CR-2232
(
NASA
, 1973
).12.
C.
Park
,
R. L.
Jaffe
, and
H.
Partridge
, “
Chemical-kinetic parameters of hyperbolic earth entry
,” J. Thermophys. Heat Transfer
15
, 76
(2001
).13.
W. C.
Gardiner
, Jr., Gas-Phase Combustion Chemistry
(
Springer Science & Business Media
, 2012
).14.
R. N.
Gupta
,
J. M.
Yos
,
R. A.
Thompson
, and
K.-P.
Lee
, “
A review of reaction rates and thermodynamic and transport properties for an 11-species air model for chemical and thermal nonequilibrium calculations to 30000 K
,” Technical Report No. NASA-RP-1232
(
NASA
, 1990
).15.
X.
Jing
, “
Numerical simulation of aerodynamic heat for mars entry capsule
,” M.S. thesis (
Beijing Jiaotong University
, 2016
).16.
C.
Yunpeng
, “
Catalytic and non-equilibrium effects of the aerodynamic heat for the mars entry capsule
,” M.S. thesis (
Beijing Jiaotong University
, 2016
).17.
J.
Lü
, “
Flow field prediction of an orbiter entering the mars atmosphere
,” Chin. J. Space Sci.
33
, 129
(2013
).18.
F. S.
Milos
,
Y.-K.
Chen
,
W. M.
Congdon
, and
J. M.
Thornton
, “
Mars Pathfinder entry temperature data, aerothermal heating, and heatshield material response
,” J. Spacecr. Rockets
36
, 380
(1999
).19.
C. F.
Curtiss
and
J. O.
Hirschfelder
, “
Transport properties of multicomponent gas mixtures
,” J. Chem. Phys.
17
, 550
(1949
).20.
J. M.
Yos
, “
Transport properties of nitrogen, hydrogen, oxygen, and air to 30,000 K
,” Technical Report No. TRAD-TM-63-7
(
National Aeronautics and Space Administration
, 1963
).21.
M.
Yu
,
H.
Kihara
,
K.-I.
Abe
, and
Y.
Takahashi
, “
Computation and analysis of the electron transport properties for nitrogen and air inductively-coupled plasmas
,” J. Korean Phys. Soc.
66
, 1833
(2015
).22.
S.
Ghorui
and
A. K.
Das
, “
Collision integrals for charged-charged interaction in two-temperature non-equilibrium plasma
,” Phys. Plasmas
20
, 093504
(2013
).23.
R. S.
Devoto
, “
Simplified expressions for the transport properties of ionized monatomic gases
,” Phys. Fluids
10
, 2105
(1967
).24.
C.
Park
,
J. T.
Howe
,
R. L.
Jaffe
, and
G. V.
Candler
, “
Review of chemical-kinetic problems of future NASA mission, II: Mars entries
,” J. Thermophys. Heat Transfer
8
, 9
(1994
).25.
C.
Park
, “
Review of chemical-kinetic problems of future NASA missions. I: Earth entries
,” J. Thermophys. Heat Transfer
7
, 385
(1993
).26.
F. G.
Blottner
, “
Prediction of electron density in the boundary layer on entry vehicles with ablation
,” Report Nol. NASA SP-252
(
NASA
, 1971
).27.
M.-H.
Yu
, “
Numerical investigation on interaction mechanisms between flow field and electromagnetic field for nonequilibrium inductively coupled plasma
,” Acta Phys. Sin.
68
, 185202
(2019
).28.
C.
Park
, “
Rotational relaxation of N2 behind a strong shock wave
,” J. Thermophys. Heat Transfer
18
, 527
(2004
).29.
R. C.
Millikan
and
D. R.
White
, “
Systematics of vibrational relaxation
,” J. Chem. Phys.
39
, 3209
(1963
).30.
Š. S.
Lazdinis
and
S. L.
Petrie
, “
Free electron and vibrational temperature nonequilibrium in high temperature nitrogen
,” Phys. Fluids
17
, 1539
(1974
).31.
W. G.
Vincenti
,
C. H.
Kruger
, Jr., and
T.
Teichmann
, “
Introduction to physical gas dynamics
,” Phys. Today
19
(10
), 95
(1966
).32.
J. P.
Appleton
and
K. N. C.
Bray
, “
The conservation equations for a non-equilibrium plasma
,” J. Fluid Mech.
20
, 659
(1964
).33.
P. A.
Gnoffo
,
R. N.
Gupta
, and
J. L.
Shinn
, “
Conservation equations and physical models for hypersonic air flows in thermal and chemical nonequilibrium
,” Technical Report No. NASA-TP-2867
(
National Aeronautics and Space Administration
, 1989
).34.
J. G.
Parker
, “
Rotational and vibrational relaxation in diatomic gases
,” Phys. Fluids
2
, 449
(1959
).35.
J. P.
Appleton
, “
Electrical precursors of ionizing shock waves
,” Phys. Fluids
9
, 336
(1966
).36.
37.
M.
Nishida
and
M.
Matsumoto
, “
Thermochemical nonequilibrium in rapidly expanding flows of high-temperature air
,” Z. Naturforsch., A
52
, 358
(1997
).38.
J. H.
Lee
, “
Electron-impact vibrational relaxation in high-temperature nitrogen
,” J. Thermophys. Heat Transfer
7
, 399
(1993
).39.
C.
Park
and
S.
Lee
, “
Validation of multitemperature nozzle flow code
,” J. Thermophys. Heat Transfer
9
, 9
(1995
).40.
M.
Yu
,
Z.
Qiu
,
B.
Lv
, and
Z.
Wang
, “
Numerical simulation of the thermal non-equilibrium flow-field characteristics of a hypersonic Apollo-like vehicle
,” Chin. Phys. B.
31
, 94702
(2022
).41.
M.
MacLean
and
M.
Holden
, “
Catalytic effects on heat transfer measurements for aerothermal studies with CO2
,” AIAA Paper No. AIAA 2006-182, 2006
.42.
M. J.
Wright
,
T.
White
, and
N.
Mangini
, “
Data Parallel Line Relaxation (DPLR) Code User Manual: Acadia-Version 4.01. 1
,” Technical Report No. NASA/TM-2009-215388
(
NASA
, 2009
).© 2024 Author(s). Published under an exclusive license by AIP Publishing.
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