Table 1 Initial values of spacecraft attitude and orbit.
Parameter | Symbol | Numerical Value | Unit |
|---|---|---|---|
Tensor of inertia | \(J_{1} ,J_{2} ,J_{3}\) | 110.4,580.5,649.5 | kg m2 |
Tensor of inertia error | \(\left[ {\begin{array}{*{20}l} {\delta J_{11} } & {\delta J_{12} } & {\delta J_{13} } \\ {\delta J_{21} } & {\delta J_{22} } & {\delta J_{23} } \\ {\delta J_{31} } & {\delta J_{32} } & {\delta J_{33} } \\ \end{array} } \right]\) | \(\left[ {\begin{array}{*{20}l} 7 & {0.02} & {0.05} \\ {0.02} & {5.79} & {0.09} \\ {0.05} & {0.09} & 5 \\ \end{array} } \right]\) | kg m2 |
Sensitizer noise | \(\delta \alpha\) | diag(52, 52, 402) | arcses2 |
Fiber optic gyro noise | \(\delta \dot{\alpha }\) | diag(52, 52, 52) | (arcses/s)2 |
Orbit radius | \(R\) | 6821 | km |
Orbital period | \(T\) | 94 | min |
Double satellite distance | \(\Delta r\) | 100 | km |
Orbit inclination | \(i\) | 89 | deg |
Right ascension of ascending node | \(\Omega\) | 78 | deg |
Geomagnetic inclination | \(\gamma_{m}\) | 11.44 | deg |
Earth angular velocity | \(\omega_{e}\) | 7.292 × \({10}^{-5}\) | rad/s |
Outline dimension | a/b/h/l | 0.9/1.8/0.78/3.35 | m |
