The codes collected here are meant to propagate and present the orbit of a spacecraft/particle in the Earth-Moon-Sun Planar Bicircular Restricted 4-Body Problem. The masses are organised as follows:
- Primary = Earth
- Secondary = Moon
- Tertiary = Sun
- Quaternary = Spacecraft
The codes allora to:
- PBR4BP_data.m = Produces the parameters used in the PBR4BP
- PBR4BP.m = Propagator in this astrodynamical model
- Syn2ECI = Transformation from PBR4BP Synodic r.f. (rotating frame) to Earth Centred Inertial r.f. (ECI), both in dimensionless forms.
- Syn2MCI = Transformation from PBR4BP Synodic r.f. (rotating frame) to Moon Centred Inertial r.f. (MCI), both in dimensionless forms.
引用格式
Luigi De Maria (2024). Planar Bicircular Restricted 4-Body Problem (PBR4BP) (https://www.mathworks.com/matlabcentral/fileexchange/119373-planar-bicircular-restricted-4-body-problem-pbr4bp), MATLAB Central File Exchange. 检索来源 .
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