Aerospace and Electronic Systems Magazine July 2017 - 37

Pasand, Hassani, and Ghorbani
Figure 5.
Continued.

(m)

(n)

the results can be interpreted as follows. In the control system design
procedure, closed-loop controller gains are designed in an ideal form,
without considering the PWPF modulator and control allocation algorithm; then, the PWPF and control allocation algorithm are integrated
into the closed loop. If they are set to be on the pseudolinear range,
the outcome will be near the ideal form, although they are both hard
nonlinear components. Therefore, it can be interpreted that changing
controller gains do not alter the general effects of thruster configurations on the considered performance indices.

One question may arise here: Are presented outcomes valid for
different controller coefficients? Regarding the question, Table 8 is
presented to illustrate the effect of controller gains on the performance
indices. It is easy to see that decreasing the proportional and derivative
gains improves fuel consumption and an average number of pulses per
thruster at the expense of degrading three-axis tracking performance,
the mean value of pulse widths, and the three-axis linear displacement.
Table 8 clearly shows that changing controller gains have the similar effects on the considered performance indices. The reason behind

Table 8.

Effect of Changing Controller Gains on Performance Indices
Three-Axis
Tracking Error

Average No.
Pulses per
Thruster

Mean PW (ms)

Three-Axis Linear
Displacement (m)

Fuel Cons. (kg)

For Kp = 120 and Kd = 200
Conf. 10

0.051

158

115

1.8

0.9

Conf. 11

0.077

221

133

2.8

1.41

Conf. 12

0.076

224

130

12.2

1.37

For Kp = 72 and Kd = 100
Conf. 10

0.109

101

111

1.9

0.56

Conf. 11

0.088

177

116

3

0.99

Conf. 12

0.087

177

116

13.8

0.97

Conf., configuration; PW, pulse width; Cons., consumption.

JULY 2017

IEEE A&E SYSTEMS MAGAZINE

37



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