The High-Precision Orbit Propagator (HPOP) uses numerical integration of the differential equations of motions to generate ephemeris. Several different force modeling effects can be included in the analysis, including a full gravitational field model (based upon spherical harmonics), third-body gravity, atmospheric drag and solar radiation pressure. Several different numerical integration techniques and formulations of the equations of motion are available. The different formulations aid in computational efficiency while preserving accuracy. Because of the many parameter settings available for the user, a precise model of the force model environment for almost any satellite can be specified, and thus a highly precise orbit ephemeris can be generated.
High precision is not without costs: (1) the user is responsible for choosing force model settings appropriate to the situation being modeled; and (2) ephemeris generation takes more computational time and effort than analytical propagation (which simply evaluates a formula).
HPOP can handle circular, elliptical, parabolic and hyperbolic orbits around any central body and at distance ranges from the lower atmosphere of the Earth, to the Moon and beyond.
After choosing the HPOP propagator, define its parameters:
- Get a new initial vector with the Initial State Tool (optional).
- Set the vehicle's Start Time, Stop Time, and Step Size.
- Choose a Coordinate System.
- Choose a Coordinate Type and enter values for the orbital parameters.
- Define any propagator specific force models.
- Define parameters for the HPOP Integrator.
Follow these links to information on:
Also, refer to the HPOP technical Notes for computational data.
If HPOP appears dimmed in the propagator drop-down list box then the HPOP license is required. Find out more on the licensing help page.
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