Path: SCPro/ProControl
% Altitude hold for a lander
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[u,thrust,angle] = AltitudeHold(x,kH,tauH,g,mass,xSet)
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Inputs
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x (:,1) State vector [r;v]
d (.) Data structure
.tauH (1,1) Damping time constant (s)
.kH (1,1) Forward gain (N/km^3)
.g (1,1) Acceleration of gravity (N/km^2)
.mass (1,1) Mass (kg)
.xSet (6,1) State vector set point [r;v]
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Outputs
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u (3,1) Thrust unit vector
thrust (1,1) Thrust (N)
angle (1,1) Thrust angle (rad)
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Copyright (c) 2022 Princeton Satellite Systems, Inc.
All rights reserved.
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Since version 2022.1
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Common: Quaternion/QTForm Common: Quaternion/U2Q Math: Linear/Mag
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