Abstract
Abstract In this paper, the evolution of space debris for spacecraft in the Sun-Synchronous orbit has been investigated. The impact motion, the evolution of debris from the Sun-Synchronous orbit, as well as the evolution of debris clouds from the quasi-Sun-Synchronous orbit have been studied. The formulas to calculate the evolution of debris objects have been derived. The relative relationships of the velocity error and the rate of change of the right ascension of the ascending node have been presented. Three debris objects with different orbital parameters have been selected to investigate the evolution of space debris caused by the Sun-Synchronous orbit. The debris objects may stay in quasi-Sun-Synchronous orbits or non-Sun-Synchronous orbits, which depend on the initial velocity errors of these objects.
Highlights
The increasing of population of the space debris poses a hazard to human spacecraft (Liou and Johnson 2006; ESA Space Debris O ce 2017)
The debris objects may stay in quasi-Sun-Synchronous orbits or non-Sun-Synchronous orbits, which depend on the initial velocity errors of these objects
This paper investigates the evolution of space debris caused by the impact between debris object and a spacecraft in the Sun-Synchronous orbit
Summary
The increasing of population of the space debris poses a hazard to human spacecraft (Liou and Johnson 2006; ESA Space Debris O ce 2017). Previous literature investigates the orbit determination, collision probability, and removal of the space debris, as well as the impact and evolution of the debris cloud. Y. Jiang et al, Evolution of space debris for spacecraft in the Sun-synchronous orbit tional torque acting on the debris is considered. The relative relationship of the objects’ velocity errors and the rate of change of the right ascension of the ascending node has been calculated, the results showed the deviation of the orbital characteristic of the sun-synchronous. Where Ω represents the right ascension of the ascending node, a represents the semi-major axis, e represents the orbital eccentricity, i represents the inclination, J2 represents the second-order zonal harmonic, n represents the mean angular velocity, Re represents the reference radius of Earth, ns represents the Earth’s mean motion around the sun. Considering the semi-major axis and the inclination have perturbations with the change of time, let
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