Path: Interplanetary/Landers
% 3D lander simulation using the bilinear tangent law. The spacecraft has 3-axis thruster control. Ideal attitude pointing is assumed. An altimeter gives the altitude. The planet is assumed to be a perfect sphere. The dynamics model accounts for the changing mass of the vehicle as fuel is consumed. This demo demonstrates the bilinear tangent law for descent from a circular equatorial orbit. Choose between the moon, Mars, and Enceladus, or add your own body. Things to explore: 1. For the bilinear control, vary the control acceleration (nAccel). 2. Try different starting altitudes. 3. Try different planets: moon, Mars, Enceladus -------------------------------------------------------------------------- See also: LandingControlBilinear, Inertias, RHSPointMass, RK4, Plot2D -------------------------------------------------------------------------- % -------------------------------------------------------------------------- Copyright (c) 2013-2014 Princeton Satellite Systems, Inc. All rights reserved. -------------------------------------------------------------------------- Since version 2014.1 --------------------------------------------------------------------------
Interplanetary: Landers/LandingControlBilinear SCPro: DynamicalModels/RHSPointMass Common: Database/Constant Common: Graphics/Plot2D Common: Graphics/TimeLabl Common: MassProperties/Inertias Math: Integration/RK4 Math: Linear/Dot Math: Linear/Mag Math: Linear/Unit
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