Background
The proposed cascade attitude control strategy
The QPDLQR and LPC approaches
The PWPF realization
The CA scheme realization
The dynamics and kinematics of the space systems
The simulation results
The parameters | The values | |
---|---|---|
1 | Space system moments of inertia |
\( \left\{ {\begin{array}{*{20}c} {I_{x} = 15.95} \\ {I_{y} = 72.19} \\ {I_{z} = 72.19} \\ \end{array} } \right. \)
|
2 | Thruster’s level |
\( T = 15.0 \)
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3 | The LPC coefficients in the inner loop |
\( \left\{ {\begin{array}{*{20}c} {k_{px} = 15.0} \\ {k_{py} = 15.0} \\ {k_{pz} = 15.0} \\ \end{array} } \right. \)
|
4 | The QPDLQR coefficients in the outer loop |
\( \left\{ {\begin{array}{*{20}c} {k_{px} = 72.0} \\ {k_{py} = 72.0} \\ {k_{pz} = 72.0} \\ \end{array} } \right. \)
\( \left\{ {\begin{array}{*{20}c} {k_{dx} = 200.0} \\ {k_{dy} = 200.0} \\ {k_{dz} = 200.0} \\ \end{array} } \right. \)
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5 | Thruster’s configurations |
\( \left\{ {\begin{array}{*{20}c} {L = 0.22} \\ {R = 0.45} \\ \end{array} } \right. \)
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6 | Relay hysteresis |
\( \varepsilon = 0.1 \)
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The outer loop results
The inner loop results
The verification of the results
The approach titles | Maximum three-axis rotational angles errors in steady state (deg) | Maximum three-axis angular rates errors in steady state (deg/s) | Trajectory convergence time (s) | |
---|---|---|---|---|
1 | The proposed approach | Less than 3 | Less than 4 | Less than 10 |
2 | The Wu approach [15] | Less than 5 | Less than 6 | Less than 25 |
3 | The Butyrin approach [16] | Less than 4 | Less than 3 | Less than 15 |