Obtaining a state vector from orbital elements is easy.
conics
Abstract
Determine the state (position, velocity) of an orbiting body from a set of elliptic, hyperbolic, or parabolic orbital elements.
conics input variables:
| What | Type | |
|---|---|---|
| Elts | SConicElements | Orbital Elements |
| Et | SEphemerisTime | Epoch, Ephemeris Time |
conics output variables:
| What | Type | |
|---|---|---|
| State | SStateVector | State Vector |
The conics action computes a state vector
Copy Hyakutake Conics to Clipboard
The definition of SConicElements:
| Name | Type | |
|---|---|---|
| PerifocalDistance | q | SDistanceVector |
| Eccentricity | e | Double |
| Inclination | i | SAngle |
| LongitudeOfAscendingNode | node | SAngle |
| ArgumentOfPeriapse | peri | SAngle |
| MeanAnomalyAtEpoch | M | SAngle |
| Epoch | epoch | SEphemerisTime |
| GravitationalParameter | GM | SMassConstant |
