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Abstract
The need for debris mitigation is illustrated in the context of historic launch activates and operational practices. This has led to the existing space debris environment, with consequent collision flux levels that are based on detailed population and evolution models. Therefore mitigation of space debris has become a major concern for us humans lately. National space agencies have proposed many space debris mitigation measures to reduce and stabilize the predicted long term growth of space object population. Through this article we take a closer look at the mathematical analysis of three main strategies adapted to reduce and stabilize the growth of space debris.
Highlights
The aim of this study is to calculate the minimum delta-v required to remove multiple target objects that lie within the lower earth orbit altitudes
The spacecraft will move to the selected object from the current orbit and it will engage in a similar mechanism as the latter; which is to attach another iron engine that will direct the second debris object back to the disposal region
This is a mechanism whereby the spacecraft will initially go up to an altitude of 382 km2. and that will be allocated as a collecting orbit which is illustrated in Figures 3 and 4; this orbit will consist of all the debris along with the space-craft prior to the pacing maneuver mechanism
Summary
The aim of this study is to calculate the minimum delta-v required to remove multiple target objects that lie within the lower earth orbit altitudes. Three such strategies have been analyzed below showing their pros and cons to find the optimum solution that gives the best out puts of delta-v, time, specific-impulse and the fuel mass of the missions
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