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Luni-solar dynamics on resident space on objects (Link1), (Link2):
The effects and dynamics of luni-solar gravity attraction on the near-Earth orbital environment has been captured utilizing Kustaanheimo-Stiefel (KS) framework. The underlying dynamical mechanisms of the solar perturbation on HEOs can be understood better through the relation between the relative Sun azimuth angle and perigee altitude oscillation.
The animations show the RAAN vs day of the year heat maps for change in perigee altitude in km (top) and the Sun azimuth angle (bottom), cycled through inclination and argument of perigee.
Few applications:
Characterization of space debris evolution in HEO;
Mission analysis with natural phasing to Lunar transfer orbits;
Solar apsidal resonance studies and space debris re-entry predictions;
Space traffic management and collision studies;
Re-entry predictions from HEOs (Link):
Re-entry predictions of space debris from HEO using response surface methodology with genetic algorithm on TLE data is carried out using KSROP - KS regularized elements orbit propagator for resident space objects, the software is collectively named as OREM (Optimal Regularized re-entry Estimation Method). It predicts re-entry from up to three years in advance and driven towards high accuracy and performance.
The traces of the apogee altitude in black color in the above figures are from observed data of chosen space objects which were in highly elliptical orbits. The colored traces are predictions with OREM.
The zone selection for generating the response surfaces in order to find the optimal initial conditions is done in view of the physical evolution of the orbital parameters. It was identified that, when the initial conditions for propagation are obtained from the epochs during the solar apsidal resonance, the convergence for optimality is better. The mean prediction error (MPE) with OREM (< 5%).
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