The orbit module provides functions for orbit dynamics analysis and simulation, orbit maneuver planning and includes a high-fidelity orbit propagator.
Downloads
Applications
- Mission analysis.
- Orbit propagation.
- Proximity operations and rendezvous.
- Fuel budgets.
Key Features
- Impulsive transfer analysis.
- Low-thrust spirals and simulations.
- Lambert law solver for large orbit changes.
- Circumnavigation using impulsive maneuvers and glideslopes.
- Stationkeeping analysis.
- Bielliptic and Hohmann transfers.
- User selectable gravity models. GEM-T1, JGM-2, JGM-3 and WGS-84 are supported.
- Ballistic propagation of the covariance matrix for the state vector.
- Keplerian and Equinoctial orbital elements, cartesian, cylindrical, and spherical frames.
- Gauss' variational equations
- Propagate NORAD elements, ex. SGP, SGP4, SGP8.
The Orbit Propagator GUI provides an interface to the high-fidelity propagator. The propagator uses a singularity-free spherical-harmonic gravity model. This tool allows users to:
- Propagate in ECI, ECR (earth-fixed) or ECIR (ECI referenced to a fixed earth).
- Have complete control over the speed and accuracy of numerical integration using the MathWorks state-of-the-art ode113 propagator.
- Select the time step.
- Specify any one of over thirty stopping conditions.
- Compute flight path angle, altitude, geodetic latitude and longitude are automatically.
- Save output to a mat-file for further analysis.
- Add Sun/moon/earth perturbations you are propagating in an earth-centered or moon-centered frame.
- Include solar pressure, earth albedo, earth radiation and drag models.
- Choose between exponential, Jacchia and Standard Atmosphere atmospheric density models.
- Plug in an orbit control function to turn on thrusters during propagation.
