Aerospace and Electronic Systems - October 2018 - 12
Analysis and Design of a Stacked Power Subsystem to Picosatellite
Figure 13.
Experimental result of controller output of boost converter.
Figure 11.
Currents and voltages in the converters at point (x) of Figure 15 with (a)
and (b) for the boost converter; (c) and (d) for the buck-boost converter.
by asterisks. In this case, the power used by CubeSat subsystems
is minimal (1.125 W). The power not used by CubeSat subsystems
is redirected to the battery charge, that results in raising the battery
charge current to approximately 1.9 A and reducing the charging
time by approximately 20 minutes. Figure 11 from (a)-(d) shows
the DC bus voltage for the subsystems, the load current of the
CubeSat subsystems, the battery voltage, and the battery charge
current, respectively, when the system is operating at point (x),
pointed out in Figure 15.
Figure 12 shows that the system is searching for the maximum
power point of the photovoltaic arrangement and that it remains
operating close to it during the battery charge intervals, for both
maximum and minimum charge conditions. The current variation
of the buck-boost converter (control of the battery charge current) depends exclusively on the maximum power point search
algorithm. However, it is possible to verify the operation of the
MPPT algorithm by verifying that the output power values are always close to 9 W, considering the power sum of each converter.
Furthermore, considering the electrical efficiency close to 0.8, it
is possible to see that the photovoltaic array is operating at the
maximum power, 11.25 W, as shown in Figure 12. Figure 13 and
Figure 14 show the compensators operation against a load variation of 50%. In Figure 13 the undershoot was approximately 0.3 V
due to charge variation from (50% to 100%), which is comprised
within the 2% error range in permanent basis. So, accommodation
time may be disregarded.
In Figure 14 the undershoot was approximately 0.2 A and the
accommodation time was approximately 0.7 seconds due to charge
variation of (50% to 100%). The results are in accordance with the
design requirements of the controllers.
Finally, Figure 15, shows the EPS electrical efficiency graph
for various configurations of the CubeSat load, where 50 Ω is the
maximum load for boost converter and 200 Ω is the minimum load
for the satellite.
CONCLUSIONS
Figure 12.
Photovoltaic array power for CubeSat maximum and minimum loads.
12
In this article, a stacked EPS architecture was proposed. The suggested configuration allows EPS to drain the highest available en-
IEEE A&E SYSTEMS MAGAZINE
OCTOBER 2018
Aerospace and Electronic Systems - October 2018
Table of Contents for the Digital Edition of Aerospace and Electronic Systems - October 2018
Contents
Aerospace and Electronic Systems - October 2018 - Cover1
Aerospace and Electronic Systems - October 2018 - Cover2
Aerospace and Electronic Systems - October 2018 - Contents
Aerospace and Electronic Systems - October 2018 - 2
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