Path: SpacecraftEstimation/Demos/AttitudeEstimation

% Test attitude determination with sun, earth and magnetometer. 

 dT is the time step for the attitude determination system. You can 
 numerically integrate with a smaller time step by setting
 nInt > 1. The initial attitude is unknown. This demo uses the sun
 earth and magnetic field as attitude sources. The earth provides roll and 
 pitch while the sun provides yaw. The magnetic field provide orientation
 with respect to the local field lines.

 When using the UKF it is important to pick an appropriate plant noise
 matrix. If it is too high the filter may go unstable and produce 
 large errors. With a gyro it is generally small. The terms for the
 delta quaternion and the bias are not the same (although they are in 
 this demo). The choice of the UKF alpha parameter is also important.
 You will notice that it takes a few sun measurements for the filter
 to properly estimate the bias. 
  See also SunMagAttDet, RVFromKepler, SunV1, FPSensors, RIGOut, BDipole
   Copyright (c) 2017 Princeton Satellite Systems, Inc.
   All rights reserved.


AerospaceUtils: Coord/QLVLH
AerospaceUtils: Coord/U2AzEl
Common: Graphics/Plot2D
Common: Graphics/TimeLabl
Common: Quaternion/QForm
Common: Quaternion/QMult
Common: Quaternion/QPose
Common: Quaternion/QUnit
Common: Time/Date2JD
Math: Integration/RK4
Math: Linear/Unit
SC: BasicOrbit/RVFromKepler
SC: Environs/BDipole
SC: Ephem/SunV1
SC: Sensor/FPSensors
SC: Sensor/RIGOut
SpacecraftEstimation: AttitudeEstimation/SunEarthMagAttDet
SpacecraftEstimation: StellarModels/FRBwRIG

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