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Message: <blockquote data-quote="rajitha_ks" data-source="post: 19747993" data-attributes="member: 162025">Research Topic: Mathematical optimization of space debris mitigation and Strategy analysis Group:Dr. JK Wijeratne, <a href="http://science.cmb.ac.lk/contact-us/contacts/?contact_id=224" target="_blank">Mr. C.R Rajapaksa.</a><a href="http://science.cmb.ac.lk/contact-us/contacts/?contact_id=224" target="_blank"></a><a href="http://science.cmb.ac.lk/contact-us/contacts/?contact_id=224" target="_blank"></a> Introduction: Space activities conducted by humans on  Earth orbit began with the first launch of the artificial satellite  Sputnik1 in 1957.  Since then, orbital debris has increased with time  and approximately 19,000 objects larger than 10cm and approximately  500,000 particles between 1 and 10 cm’s exist in space and probably tens  of millions of particles smaller than 1cm roams in orbit today. U.S.  Space Surveillance Network tracks larger orbital objects (> 10cm) and  approximately 15,000 objects were in their catalogue as of 1st May  2010. Fifty percent of all orbital debris is vulnerable to collisions,  which result in fragmentation of debris and that leads to a rise in the  debris populations in the future even in the absence of future space  launches.     Mechanisms for Removing or reducing space debris 1)      Minimizing the break up potential during operational phases 2)      Limiting the accidental collision in orbit 3)      Avoiding intentional destructive and harmful operations (deliberate collisions) in orbit 4)      Limiting debris released during normal operations 5)      Limiting long-term presence of launch vehicle and the  spacecraft in low earth orbit (LEO) region and geosynchronous (GEO)  region after end of their missions 6)      Taking active measures to deorbit or move debris to alternative orbits From the above mechanisms, the active  measures to deorbit the debris object have been chosen for the  suggesting study. The international space community has focused on  debris mitigation measures that lasted a decade, and they have  introduced policies and guidelines to address these issues.  In 2007,  the United Nations adopted space debris mitigation guidelines. However,  adopting these guidelines was not sufficient to stabilize the LEO debris  environment, nevertheless active debris removal methods may help to  control the situation. Moreover, active debris removal methods will  enhance the reliability of future space systems. These methods need to  address technological, financial and political constraints when being  implemented. Furthermore, these systems should identify effective  mitigation and removal strategies based on reliability, robust criteria  and appropriate performance metrics. Previous studies used  high-definition models of space debris environment to select these  criteria and metrics on a relatively ad-hoc basis. Therefore, there is  still a current requirement to identify a potentially optimal solution  for space debris removal. This field of research commenced more than twenty-five years ago and numerous methods were proposed to remove large debris. Objectives of the research It is suggested that when a single vehicle attempts to carry  severaldeorbiting packages within different inclinations, even at same  altitudes it requires a very high fuel mass and delta-v due to the plane  changes that should be attended by the spacecraft. Equipped iron  engines with satellites could also be used to direct debris back to the  earth’s atmosphere. However, due to the high-energy requirements, this  was also not worth being operational in the past. In addition, it  requires a long-term power source and attitude control sub systems. This  implies a practical approach to orbital debris removal process that  needs to be developed more thoroughly to adopt a feasible system. This  leads the main objective of the this research to find the best optimum  solution to deorbit the debris to a position approximately below 100km  of altitude to completely decay the debris object in the earth’s  atmosphere. The optimum solution will be future analyzed to give out the  best mission options in order to identify the most effective sequence  of debris that needs to be de-orbited with priority. Technical  communities have focused to obtain precise information about debris via  the SGP4 model as it helps to predict these orbital debris objects more  effectively. Consequently, the author of this study decides to use the  SGP4(Simplified General Perturbation) modelමුගෙ research project එකhttp://science.cmb.ac.lk/departments/mathematics/research/postgraduate-research-projects/</blockquote>

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