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:
|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|
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|
|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.