Operation | Description |
---|---|

Normalize time (t) from reference epoch time (t) and known validity interval (Δt)_{oe} | |

Obtain satellite position in MI frame | |

Obtain satellite velocity in MI frame | |

Calculate Euler angles at t for frame transformation | |

ψ rotation matrix | |

θ rotation matrix | |

ϕ rotation matrix | |

Rotation matrix from MI frame to ME frame | |

Satellite position in ME frame | |

Satellite velocity in ME frame |