Aerospace and Electronic Systems Magazine June 2017 - 43

Macˇ iulis and Buzas

Figure 13.

Simulated time response of LituanicaSAT-2 with 30 cm fins deployed at 20°, proportional B-dot gain 6000, initial tumble rate 50 °/s, altitude 380 km.

Figure 14.

Simulated time response of LituanicaSAT-2 with 30 cm fins deployed at 20°, bang-bang B-dot control law, initial tumble rate 50 °/s, altitude 380 km.

scenario for 380 km initial orbit altitude based on NASA DAS
(Debris Assesment Software) simulations. However, in case of
LituanicaSAT-2, the launcher was changed late in the project from
initially planned 400 km to 500 km initial orbit altitude. Thus 20
degrees fin angle was chosen for final configuration to increase
stability at higher orbits while still maintaining good performance
at lower altitudes.
For rate damping control a B-dot algorithm is proposed with
actuation capability of not less than 0.05 A/m magnetic dipole moment. Both proportional and bang-bang B-dot modes were considered and found to be equally capable to detumble the satellite from
the initial 50 deg/s rate within 3 days at nominal conditions. The
bang-bang method seems to be more attractive due to the shorter
JUNE 2017

time required to achieve steady state conditions and higher pointing accuracy, but with additional cost of power consumption. The
suggested design complies with requirements even at off-nominal
conditions of 90 deg/s tip- off rates as was demonstrated by simulations.
For future work, it would be interesting to compare the accuracy of different gas surface interaction models, as only a simplified Schamberg's model was implemented in this work. Also a
more accurate shadowing estimation algorithm would be desired
for more detailed analysis. In terms of practical mission constrains,
it is also of great interest to model the scenario that would occur if
magnetic torquers could not be used for active rate damping due
to e.g. power limitations or hardware faults. In that case only the

IEEE A&E SYSTEMS MAGAZINE

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