Aerodynamics of the RANGE Nanosatellites from
Direct Flowfield Simulation
Kenneth A. Hart,
*
Brian C. Gunter,
†
and Robert D. Braun
‡
Georgia Institute of Technology, Atlanta, GA, 30332-0150, USA
One of the objectives of the RANGE mission is to perform relative navigation using
differential aerodynamics. The aerodynamic force coefficients, moment coefficients, and
heating can be computed numerically, though this process is too computationally expen-
sive to integrate directly into an orbit propagator. A surrogate model is developed to
improve the modeling fidelity beyond a simple sphere or plate model without significantly
increasing computational cost. The training points for this model come from an industry
standard code for Direct Simulation Monte Carlo analysis. Detailed discussions of model
development, validation, and results are included.
Nomenclature
C Coefficient, see subscripts
CFD Computational fluid dynamics
DAC DSMC Analysis Code
DSMC Direct Simulation Monte Carlo
H Heaviside function
LEO Low-Earth orbit
MFE Model fit error
ˆ n Surface normal, oriented outward
˙
Q Total convective heat rate
r
0
RBF tuning parameter
RANGE Ranging and Nanosatellite Guidance Experiment
RBF Radial basis function
ˆ
t Surface tangent vector
ˆ
V
∞
Freestream velocity direction
Subscripts
A Axial
D Drag
L Lift
N Normal
p Pressure
S Side
T Tangential
τ Shear
Symbols
α Angle of attack
β Sideslip angle
θ Angle of incidence
σ Accommodation coefficient, see subscripts
*
Graduate Research Assistant, Daniel Guggenheim School of Aerospace Engineering, AIAA Student Member.
†
Assistant Professor, Daniel Guggenheim School of Aerospace Engineering, AIAA Senior Member.
‡
David & Andrew Lewis Professor of Space Technology, Daniel Guggenheim School of Aerospace Engineering, AIAA Fellow.
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American Institute of Aeronautics and Astronautics
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AIAA SPACE 2016
13 - 16 September 2016, Long Beach, California
AIAA 2016-5520
Copyright © 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
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