The Orbit page of a satellite's Basic properties provides a complete interface for defining satellite orbits and editing the properties of previously defined orbits, including those created with the STK Orbit Wizard. Satellite orbit properties include:

For most propagators, the Orbit page includes fields that let you specify some or all of the following time parameters:

Parameter | Description |
---|---|

Start and Stop Times | Define the satellite's time period. |

Step Size | The interval between calculated ephemeris output points. |

Orbit Epoch | The time at which the established orbital elements are true. |

Coordinate Epoch | The epoch of the coordinate system (disabled for coordinate systems with pre-established epochs (e.g. J2000, B1950) |

STK offers a variety of analytic and numerical orbit propagators, some of which are available only with specific licenses. Follow one of the links below to learn how to configure a specific propagator and any applicable force models:

Two Body | J2 Perturbation | J4 Perturbation | HPOP |

SGP4 | GPS | LOP | StkExternal |

SP3 | 11-Parameter | SPICE | Astrogator |

Real-time |

STK supports several different coordinate types (sets of orbital elements). Follow one of the links below to learn about a specific coordinate type.

Classical (Keplerian) | Cartesian | Equinoctial | Delaunay Variables |

Mixed Spherical | Spherical | Geodetic | |

Target Vector Incoming Asymptote | Target Vector Outgoing Asymptote |

STK makes available a number of coordinate systems to which orbital elements can be referenced.

Note: Some coordinate systems require special licenses.

The Initial State tool, available with most propagators, lets you change the initial state of a satellite by reading an ephemeris from a file, or move the epoch of the initial state using a satellite's propagated ephemeris.