Path: CubeSat/Simulation
% Aerodynamic model for a CubeSat.
Contains a built-in demo for a 1U CubeSat in a 6500 km orbit.
Also contains an option to retrieve the default data structure.
Note that it is most efficient to combine the areas into one per face
for simple CubeSat models - i.e. 6 areas.
The attitude model in CubeSatAttitude will be used if p.q is empty.
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Form:
[force, torque] = CubeSatAero( p, d )
d = CubeSatAero % data structure
CubeSatAero % demo for LEO orbit with LVLH alignment
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Inputs
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p (.) Profile data structure
.r (3,1) ECI position
.v (3,1) ECI velocity
.q (4,1) ECI to body quaternion
.vRel (3,1) ECI velocity relative to the earth (km/s)
.rho (1,1) Atmospheric density (kg/m^3)
d (.) Aero data structure
.cD (1,1) Drag coefficient
.nFace (3,:) Face outward unit normals
.rFace (3,:) Face vectors with respect to the origin
.cM (3,1) Center of mass with respect to the orgin
.area (1,:) Area of each face (m^2)
.att (.) Attitude data structure
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Outputs
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force (3,1) ECI force (N)
torque (3,1) Body fixed torque (Nm)
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See also CubeSatFaces, CubeSatAttitude
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Common: Graphics/Plot2D Common: Graphics/TimeLabl Common: Quaternion/QForm Common: Quaternion/QTForm CubeSat: Utilities/CubeSatAttitude CubeSat: Utilities/CubeSatFaces Math: Linear/Cross Math: Linear/Dot Math: Linear/Mag SC: BasicOrbit/RVFromKepler
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