Table 3 Chaser spacecraft specifications.
From: Coupled position and attitude control of a servicer spacecraft in rendezvous with an orbiting target
Chaser spacecraft specification | ||
|---|---|---|
Physical specifications | ||
 Mass \(\left({M}_{c}\right)\) | \(100 \left[\mathrm{kg}\right]\) | |
 Size | \(0.90\times 0.85\times 0.72 \left[\mathrm{m}\right]\) | |
 Inertia \(\left({I}_{c}\right)\) | \(diag\left(11.5, 11.5, 11.5\right) \left[\mathrm{kg}.{\mathrm{m}}^{2}\right]\) | |
Actuators specification | ||
 Position control actuators: | 6 thrusters | |
 Each thruster mass \(\left({m}_{thr}\right)\) | 0.38 [kg] | |
 Fuel mass \(\left({m}_{f}\right)\) | 15.7 [kg] (Hydrazine) | |
 Specific impulse (\({I}_{sp}\)) | 227 [s] | |
 Thrusters force \(\left({f}_{thr}\right)\) | 1 [N] | |
 Thrusters misalignment | \(\left[{\alpha}_{{Th}_{1}}, {\alpha}_{{Th}_{2}}, {\alpha}_{{Th}_{3}}\right]\) | \(\left[0.1, 0.1, 0.1\right] [\mathrm{deg}]\) |
\(\left[{\beta}_{{Th}_{1}}, {\beta}_{{Th}_{2}}, {\beta}_{{Th}_{3}}\right]\) | \(\left[0.2, 0.2, 0.2\right][\mathrm{deg}]\) | |
 Attitude control actuators: | 3 orthogonal RWs | |
 RWs mass | 0.8 [kg] | |
 Moment of inertia \(\left({I}_{Rw}\right)\) | \(6.52\times {10}^{-4}\mathrm{ kg}{\mathrm{m}}^{2}\) | |
 Max Torque \(\left({T}_{Rw}\right)\) | 0.02 [Nm] | |
 Max Angular momentum \(\left({h}_{Rw}\right)\) | 0.41 [Nms] | |
 Max Angular velocity \(\left({\omega}_{Rw}\right)\) | 6000 [RPM] | |
 Delay | 2 [ms] | |
 Wheels misalignment | \(\left[{\alpha}_{{RW}_{1}}, {\alpha}_{{RW}_{2}}, {\alpha}_{{RW}_{3}}\right]\) | \(\left[0.1, 0.1, 0.1\right] [\mathrm{deg}]\) |
\(\left[{\beta}_{{RW}_{1}}, {\beta}_{{RW}_{2}}, {\beta}_{{RW}_{3}}\right]\) | \(\left[0.2, 0.2, 0.2\right][\mathrm{deg}]\) | |
