analysis of temperature-constrained ballute aerocapture for high-mass mars payloads
DESCRIPTION
Analysis of Temperature-Constrained Ballute Aerocapture for High-Mass Mars Payloads. Kristin Gates Medlock (1) Alina A. Alexeenko (2) James M. Longuski (3). 6 th International Planetary Probe Workshop Atlanta, Georgia June 23-27, 2008. (1) Graduate Student, Purdue University - PowerPoint PPT PresentationTRANSCRIPT
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Analysis of Temperature-Constrained Ballute Aerocapture for High-Mass Mars Payloads
Kristin Gates Medlock(1)
Alina A. Alexeenko(2)
James M. Longuski(3)
(1) Graduate Student, Purdue University(2) Assistant Professor, Purdue University(3) Professor, Purdue University
6th International Planetary Probe WorkshopAtlanta, GeorgiaJune 23-27, 2008
Funded in part by NASA GSRP Fellowship through MSFC
MSFC Technical Advisor: Bonnie F. James
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2June 25, 2008 Medlock, Alexeenko, Longuski
Can towed ballutes be used to capture high mass systems at Mars?
High-fidelity aerothermodynamic analysis must be achieved
ballute release
orbiter trajectory
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3June 25, 2008 Medlock, Alexeenko, Longuski
Temperature-Constrained Trajectories for Towed Toroidal Ballute Aerocapture at Mars
Hypersonic Planetary Aeroassist Simulation System
(HyperPASS)
3DOF trajectory simulations
point-mass vehicle representation
variable CD model
rotating atmosphere (with planet)
Exponentially interpolated atmosphere (Mars COSPAR90)
Ballute Surface Temperature ≤ 500ºC(equivalent to Qs= 2.01 W/cm2)
Simulation Parameters
Vehicle Mass: 0.1, 1, 10, and 100 tons (sans ballute)
Entry Speed = 6.0 km/s (at 150km)
Target: 4-day Mars parking orbit
CD,ball = 2.00 (varies with Kn) CD,s/c = 0.93 (constant)
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4June 25, 2008 Medlock, Alexeenko, Longuski
Ballute Sizing Results for Temperature-Constrained Ballute Aerocapture at Mars
R 4ballr R
Parameter 0.1 ton case 1 ton case 10 ton case 100 ton case
s/c ballute s/c ballute s/c ballute s/c ballute
m [kg] 100 3.20 1000 20.9 10,000 98.2 100,000 453
A [m2] 2.00 103 5.64 669 26.1 3140 121 14500
r [m] 0.80 1.43 1.34 3.66 2.88 7.91 6.20 17.0
R [m] --- 5.73 --- 14.59 --- 31.63 --- 67.94
Initial β [kg/m2] 0.50 0.76 1.60 3.45
, , / / /, , , , ,D ball D s c s c s cR C C A m
/
, / / ,
s c ball
D s c s c D ballute ball
m m
C A C A
Ballistic Coefficient
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5June 25, 2008 Medlock, Alexeenko, Longuski
Altitude vs. Knudsen Number
KnL
Kn > 100: free molecular flow Kn < 10-3 : continuum flow
in between is rarefied and transitional flow
0
50
100
150
200
250
300
350
1.E-05 1.E-03 1.E-01 1.E+01 1.E+03 1.E+05
Free-Stream Knudsen Number
Alti
tude
(km
)
0.1 ton case
100 ton case
10 ton case
1 ton case
continuum flow free molecular flowrarefied flow
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6June 25, 2008 Medlock, Alexeenko, Longuski
Flow Conditions
CASEBallisticCoeff.
[kg/m2]
Char. Length
[m]
Altitude @ max heating
[km]
Knudsen Number
Reynolds Number
0.1 ton case 0.50 2.86 90.99 2.63x10-2 878
1 ton case 0.76 7.31 87.15 6.20x10-3 3745
10 ton case 1.60 15.82 81.40 1.30x10-3 17497
100 ton case 3.45 33.98 75.64 3.00x10-4 81398
at Point of Maximum Heat Flux
rarefied, laminar flow
continuum, turbulent flow
Indicates rarefied vs. continuum flow regime
Indicates laminar vs. turbulent flow
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7June 25, 2008 Medlock, Alexeenko, Longuski
Aerothermodynamic ToolsCFD Langley Aerothermodynamic Upwind Relaxation Algorithm
(LAURA)
3D/2D/axisymmetric code
grid resolution, ~27500 cells
radiative equilibrium wall temperature
super-catalytic wall boundary
governing equations: Full Navier-Stokes
laminar flow assumed
DSMC Statistical Modeling In Low-density
Environment (SMILE)
3D/2D/axisymmetric code
3 million simulated molecules
constant wall temperature assumed
gas-surface interactions assumed to be diffuse, with full energy accommodation
variable-hard-sphere molecular model
Martian Atmosphere Model: eight species gas model with chemical reactions and exchange between translational, rotational, and vibrational modes.
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8June 25, 2008 Medlock, Alexeenko, Longuski
9 blocks, 27500 cellsgrid not fully convergedcell Reynolds number
minimum cell Re = 0.03maximum cell Re = 13.06
Convergence residualminimum residual = 10-5
maximum residual = 10-3
CFD Numerical Issues
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9June 25, 2008 Medlock, Alexeenko, Longuski
Mach Number
Complex hypersonic flow, combining normal and oblique shock waves around the spacecraft and ballute.
M∞ = 27.2
0.1 ton payload, β = 0.50 (DSMC results) Kn = 2.63E-2, V∞= 5.38 km/s
1 ton payload, β = 0.76 (CFD results) Kn = 6.20E-3, V∞= 5.39 km/s
M∞ = 27.9
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10June 25, 2008 Medlock, Alexeenko, Longuski
0.1 ton Pressure & CD (DSMC)
2
2D
DC
V A
Based on Moss’ DSMC calculations for air:
CD = 1.32
DSMC results for
Mars: CD = 1.48
Sum of surface pressure and friction forces in the x-direction
p∞ = 0.03 Pa
(12% higher)
0.1 ton payload, β = 0.50 (DSMC results) Kn = 2.63E-2, V∞= 5.38 km/s
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11June 25, 2008 Medlock, Alexeenko, Longuski
0.1 ton Surface Heating (DSMC)
Sutton-Graves model :
assuming C = 2.62x10-8 kg1/2/m
Qs = 2.47 W/cm2 ballute
Qs = 3.31 W/cm2 orbiter
DSMC results:
Qs = 1.63 W/cm2 ballute (34% lower)
Qs = 3.09 W/cm2 orbiter (6% lower)
3stag
n
Q CVR
0.0
0.5
1.0
1.5
2.0
2.5
3.0
3.5
0 45 90 135 180 225 270 315 360
θ [deg]
Hea
t F
lux
[W/c
m2]
V ∞ θ
s/c
ballute
0.1 ton payload, β = 0.50 (DSMC results) Kn = 2.63E-2, V∞= 5.38 km/s
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12June 25, 2008 Medlock, Alexeenko, Longuski
1 ton Pressure & CD (CFD)
Based on Moss’ DSMC calculations for air:
CD = 1.32
Preliminary CFD results for Mars:
CD = 1.52(expected to be lower when fully converged)
p∞ = 0.023 Pa
1 ton payload, β = 0.76 (CFD results) Kn = 6.20E-3, V∞= 5.39 km/s
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13June 25, 2008 Medlock, Alexeenko, Longuski
1 ton Surface Heating (CFD)
Sutton-Graves model :
assuming C = 2.62E-8 kg1/2/m
Qs = 2.01 W/cm2 ballute
Qs = 3.32 W/cm2 orbiter
Preliminary CFD results:
Qs = 1.18 W/cm2 ballute (41% lower)
Qs = 2.08 W/cm2 orbiter (37% lower)
3stag
n
Q CVR
0.0
0.5
1.0
1.5
2.0
2.5
0 45 90 135 180 225 270 315 360
θ [deg]
Hea
t F
lux
[W/c
m^2
]
s/c
ballute
V ∞ θ
1 ton payload, β = 0.76 (CFD results) Kn = 6.20E-3, V∞= 5.39 km/s
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14June 25, 2008 Medlock, Alexeenko, Longuski
Aerothermodynamic analysis indicates that CD for Mars is higher than the CD calculated for air at the same Knudsen number (as expected).
Aerothermodynamic analysis (both DSMC and preliminary CFD) predict a lower ballute heat flux than estimated by Sutton-Graves model (34 % lower for the 0.1 ton case and 41% lower for the 1 ton case).
Heating results suggest that ballute-spacecraft systems with larger ballistic coefficients (than predicted by the Sutton-Graves model) are feasible for Mars aerocapture.
Conclusions
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15June 25, 2008 Medlock, Alexeenko, Longuski
Back-up Slides
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16June 25, 2008 Medlock, Alexeenko, Longuski
21
2 DD V AC
DSMC Predictions for CD vs. Kn (Earth)
Mean free path, λ, is a function of altitude
Moss, “DSMC Simulations of Ballute Aerothermodynamics Under Hypersonic Rarefied Conditions”, AIAA 2005-4949.
function of Kn
0
0.5
1
1.5
2
2.5
0.001 0.01 0.1 1 10 100
Knudsen Number = λ/L
Cd
Air (Moss)
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17June 25, 2008 Medlock, Alexeenko, Longuski
Stagnation Point Heating Rate0.5 3
s
n
C VQ
R
Larger ballute = lower heating rate at a given altitude
(based on Sutton-Graves heating approximation)
2,max ,maxfor Kapton: 500 2.01 w sT C Q W cm
0.0
0.5
1.0
1.5
2.0
2.5
3.0
0 200 400 600 800
time (s)
Sta
gn
atio
n-P
oin
t H
eati
ng
Rat
e (W
/cm
2 )
0.1 ton case
100 ton case
10 ton case
1 ton case
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18June 25, 2008 Medlock, Alexeenko, Longuski
Stagnation Point Heating Rate
4 1
2w sT Q
Stefan-Boltzmann constant (σ = 5.67x10-8 kg/s3/K4)
-300
-200
-100
0
100
200
300
400
500
600
0 200 400 600 800
time (s)
Bal
lute
Wal
l Tem
per
atu
re (
deg
C)
0.1 ton case
100 ton case10 ton case
1 ton case
2,max ,maxfor Kapton: 500 2.01 w sT C Q W cm
0.1 ton: β = 0.50
1 ton: β = 0.76
10 ton: β = 1.60
100 ton: β = 3.45
emissivity (ε = 0.5)
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19June 25, 2008 Medlock, Alexeenko, Longuski
Temperature
T∞ = 139 KHigh temperature leads to CO2
dissociation, which causes chemical reactions.
0.1 ton payload, β = 0.50 (DSMC results) Kn = 2.63E-2, V∞= 5.38 km/s 1 ton payload, β = 0.76 (CFD results)
Kn = 6.20E-3, V∞= 5.39 km/s
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20June 25, 2008 Medlock, Alexeenko, Longuski
Surface Pressure (1 ton, CFD)
0
5
10
15
20
25
0 45 90 135 180 225 270 315 360θ [deg]
surf
ace
pre
ssu
re [
N/m
2 ]
V ∞ θ
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21June 25, 2008 Medlock, Alexeenko, Longuski
Surface Pressure (0.1 ton, DSMC)
0.0
2.0
4.0
6.0
8.0
10.0
12.0
14.0
16.0
18.0
0 45 90 135 180 225 270 315 360
θ [deg]
Pre
ssu
re [
N/m
2 ]
V ∞ θ
s/c
ballute
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22June 25, 2008 Medlock, Alexeenko, Longuski
Surface Temperature (0.1 ton, DSMC)
-100
0
100
200
300
400
500
600
0 100 200 300 400θ [deg]
surf
ace
tem
per
atu
re [
ºC]
V ∞ θ