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Path: SpacecraftEstimation/Demos/AttitudeEstimation
% Test a sun and earth sensor attitude determination system. 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 and the earth as attitude sources. The earth provides roll and pitch while the sun provides yaw. The simulation starts with valid measurements from both sun and earth sensors. The attitude and rate errors rapidly go to zero. The spacecraft has a small z rate so eventually the sun sensor measurement is no longer valid. The covariance then grows rapidly. Note that the plant noise covariances are larger than the measurement covariances. This determines the rate of growth. When the sun is visible again, the covariance drops. Eclipses are not modeled which would cause additional sun sensor outages. -------------------------------------------------------------------------- See also QLVLH, QMult, QPose, QUnit, Plot2D, TimeGUI, RK4, Unit, Date2JD, SunEarthAttDet, TOrbit, RVFromKepler, SunV1, FPSensors, RIGOut TimeLabl -------------------------------------------------------------------------- % -------------------------------------------------------------------------- Copyright (c) 1994-2000, 2017 Princeton Satellite Systems, Inc. All rights reserved. -------------------------------------------------------------------------- 2017.1 Changed the simulation duration and initial conditions --------------------------------------------------------------------------
AerospaceUtils: Coord/QLVLH Common: Graphics/Plot2D Common: Graphics/TimeLabl Common: Quaternion/QMult Common: Quaternion/QPose Common: Quaternion/QUnit Common: Time/Date2JD Math: Integration/RK4 Math: Linear/Unit SC: BasicOrbit/RVFromKepler SC: Ephem/SunV1 SC: Sensor/FPSensors SC: Sensor/RIGOut SpacecraftEstimation: AttitudeEstimation/SunEarthAttDet SpacecraftEstimation: StellarModels/FRBwRIG
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