Path: CubeSat/AttitudeControl
% CubeSat disturbance analysis from batch data using RHSCubeSat.
Compute the drag, magnetic, gravity gradient, and optical disturbances. The
environment is computed using AtmJ70, BDipole, and SunV1. AtmDens2
can be used instead by supplying an empty matrix for d.atm.
The built-in demo computes the disturbances on a 3U satellite for one day.
The center of mass is assumed to be offset from the geometric center of the
spacecraft by a few cm. Note the growth in momentum. the gravity gradient
torque is zero in the demo because the attitude entered is perfect LVLH and
the inertia is symmetric.
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Form:
[tT, fECI, h, hECI, f, t, powers] = CubeSatDisturbanceAnalysis( d, q, r, v, jD )
CubeSatDisturbanceAnalysis % demo
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Inputs
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d (.) Data structure from RHSCubeSat
q (4,:) Quaternion, ECI to body
r (3,:) Position vector
v (3,:) Velocity vector
jD (1,:) Julian dates
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Outputs
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tT (3,:) Torque in body (Nms)
fECI (3,:) Force in ECI (N)
h (3,:) Body momentum (Nms)
hECI (3,:) ECI momentum (Nms)
torque (.) Torque structure
.total (3,:) Torque in body frame
.aero (3,:) Aerodynamic torque
.mag (3,:) Magnetic torque
.optical (3,:) Optical torque
.gg (3,:) Gravity gradient torque
force (.) Force structure
.total (3,:) Force in ECI frame
.aero (3,:) Aerodynamic force
.optical (3,:) Optical force
powers (1,:) Total power from the solar cells (W)
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See also CubeSatAero, CubeSatRadiationPressure, GravityGradientFromR,
RHSCubeSat
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AerospaceUtils: Coord/QLVLH CubeSat: Simulation/RHSCubeSat SC: BasicOrbit/Period SC: BasicOrbit/RVFromKepler SC: Disturbances/OpticalSurfaceProperties SC: Visualization/PlotPlanet Common: GUIs/Figui Common: Graphics/AxesCart Common: Graphics/Plot2D Common: Graphics/Plot3D Common: Graphics/TimeLabl Common: Quaternion/AU2Q Common: Quaternion/QMult Common: Quaternion/QTForm Common: Time/Date2JD Math: Linear/Mag
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