Simulink:Aerospace 6 DoF Model Singularity with High Altitudes
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I am using the "Simple Variable Mass 6DoF ECEF (Quaternion)" for a rocket model and everything is working great and as expected, except when the altitude (h) exceeds a certain value (around 180,000 meters). I end up getting an error:
"Derivative input 1 of 'LV01/Simple Variable Mass 6DoF ECEF (Quaternion)/Calculate Velocity in Body Axes/ub,vb,wb' at time 0 is Inf or NaN. Stopping simulation. There may be a singularity in the solution. If not, try reducing the step size (either by reducing the fixed step size or by tightening the error tolerances)."
Any ideas? I'm kind of stuck since I need to get up to around 500 km. I couldn't find anything that discussed limitations on with the model. Maybe there is another more appropriate model to use?
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Guy Rouleau
el 28 de Ag. de 2013
I do not think it is because of high altitude. Based on the subsystem where the error happens shown in the screenshot, it looks like your body starts spinning infinitely fast.
Try logging data and analyzing how the states in your model evolve. Maybe Simulink debugger can help analyzing in finer details what happen just before the end.
For this kind of situation, there is typically no other solution than looking at all the details in your model to get better understanding of the system you are trying to model.
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