Aerospace and Electronic Systems - October 2018 - 11

Mattos et al.

EXPERIMENTAL RESULTS

Figure 9.

Boost and buck-boost converters control.

G(Vbus , D ) ( s ) =

−0,002382 s + 1,36·106
0,002s 2 + 0,0001s + 7,929·104

C( D ,Vbus ) ( z ) = 0.3609

( z − 0.9943)( z − 0.9852 )
( z − 1)( z − 0.5366 )

(18)

This section shows the experimental
results that prove the operation of the
proposed architecture designs. A laboratory prototype was developed using the
components described in Table 1. Current
and voltage data were obtained using the
Tektronix MDO4054-3 oscilloscope. The
controllers were implemented in Texas
Instruments TMS320F28335 DSP. The
electrical efficiency was obtained using
Yokogawa WT3000E.
Figure 10 shows the charging battery
process for two situations: first with satellites operating at nominal load and second with satellites operating at minimum
load. Samples of the battery current and
voltage were drawn at regularly spaced
intervals of 10 minutes, hence finding the
maximum charge plot (50%), in which
the circles represent the samples obtained.
Figure 10 also shows the battery charge
current variation on the initial minutes,
where the search for the maximum power
point occurs, translated as the search for
the battery maximum charge current.
During the maximum load condition,
the buck-boost converter delivers approximately 1.2 A to the battery. In this
situation, the available power for both the
boost and the buck-boost converter is 4.5
W. The P&O algorithm is active; however, the battery charge current is not the
maximum considering the CubeSat as full
load or operating with all subsystems.
For the charging process, where the current is set at 1.9 A, the
sampling was performed every 3 minutes. Samples are represented

(19)

For the buck-boost converter, the transfer function is given by
(20) and the compensator equation is shown in (21). The method
used to tune the compensators was developed according to [10].
G(ibat , D ) ( s ) =

−2,3·10−5 s + 6,8
5,6·10−8 s 2 + 4,7·10−5 s + 0,7

C( D ,ibat ) ( z ) = 0.9411

( z − 0.9937 )( z − 0.9822 )
( z − 1)( z − 0.7436 )

(20)

(21)

Figure 10.

Battery current and voltage with minimum and maximum CubeSat load.

OCTOBER 2018

IEEE A&E SYSTEMS MAGAZINE

11



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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