The Long-term orbit predictor (LOP) allows accurate prediction of the motion of a satellite's orbit over many months or years. The LOP propagator uses the same orbital elements as the Two-Body, J2 and J4 propagators.
The LOP propagator does not propagate its position; therefore, Access, Graphics, some reports, and some Vector Geometry, Time, and Calculation components may not be defined for a Satellite using the LOP propagator.
- Get a new initial vector with the Initial State Tool (optional).
- Set the satellite's Start Time, Stop Time, and Step Size.
- Choose a Coordinate System.
- Choose a Coordinate Type and enter values for the orbital parameters.
- Define the Force Model.
The LOP propagator works in the Mean of Epoch reference frame where the epoch of the reference frame is the epoch of the initial conditions. For the purposes of central body gravity effects, the movement of the Earth's equator due to precession and nutation are ignored (the Earth Fixed equator is assumed to be in alignment with the Mean of Epoch equator). It is therefore often desirable to view the evolution of the orbit plane (inclination and right ascension of the ascending node) in Mean of Epoch coordinates.
While LOP accepts inputs in osculating elements, STK converts those inputs to mean elements before propagating an orbit. This is an iterative process that ends based on internal convergence criteria. After the mean elements are integrated, they are transformed back to osculating elements for output. Since the conversion to mean elements is not exact, it is possible for the initial state output by LOP to be slightly different from the original initial state.
The Force Models... button on the Orbit page allows you to set advanced options for the LOP propagator.
|Maximum Degree||The maximum degree of geopotential coefficients to be included for Earth gravity computations. Valid range is from 2 to 70.|
|Maximum Order||The maximum order of Geopotential coefficients to be included for Earth gravity computations. Valid range is from 0 to the Maximum Degree.|
|Use Solar Gravity||If ON, the effects of solar gravity on the satellite are modeled.|
|Use Lunar Gravity||If ON, the effects of lunar gravity on the satellite are modeled.|
|Use||If ON, the drag parameters set here are modeled.|
|Cd||The atmospheric drag coefficient.|
|Advanced Settings...||Click Advanced Settings... to define further the drag model to be used during LOP calculations.|
|Use||If ON, solar radiation pressure values entered here are modeled.|
|Cr||The solar radiation pressure coefficient.|
|Atmosphere Height||Height of atmosphere blockage used when calculating shadow entry and exit in solar radiation computations.|
Use the Advanced Settings... button in the LOP Force Model window to define further the drag model to be used for calculations.
If the Atmospheric Density Model is Exponential Density, define the following parameters:
|Reference Density||O in the above equation.|
|Reference Height||hO in the above equation.|
|Scale Height||H in the above equation.|