Abdikul E. Ashurov

@enu.kz

Department of Space Engineering and Technology
L.N. Gumilyov Eurasian National University



           

https://researchid.co/abdikul

EDUCATION

Saint Petersburg State University

RESEARCH INTERESTS

Astrodynamics of spacecrafts

FUTURE PROJECTS

Developing an effective method for detecting satellite orbital maneuvers and its application to LEO and GEO satellites

It is planned to continue the work begun in the paper An effective method for detecting satellite orbital maneuvers and its application to LEO satellites, published in Advances in Aircraft and Spacecrfaft Science. An International Journal, Vol. 9, No. 4, July 2022, pages 279-300. https://www.techno-press.org/content/?page=article&journal=aas&volume=9&num=4&ordernum=1 https://doi.org/10.12989/aas.2022.9.4.279 In addition, it is assumed that on the basis of this method, a service for monitoring satellite maneuvers to be created


Applications Invited
Looking for colleagues for cooperation
5

Scopus Publications

Scopus Publications

  • DEVISING A DEORBITATION STRATEGY FOR KAZAKHSTANI’S KazEOSat-1 SPACECRAFT
    Berik Zhumazhanov, Aigul Kulakayeva, Abdikul Ashurov, Kazbek Baktybekov, Ainur Zhetpisbayeva, Daniyar Uskenbaev, Bexultan Zhumazhanov, Aigerim Zylgara, and Aliya Kargulova
    Private Company Technology Center
    The object of this study is the process of deorbiting the KazEOSat-1 spacecraft, which has completed its active service life in low Earth orbit. The main problem is the lack of an effective technique to deorbit KazEOSat-1, taking into account its technical characteristics, orbital parameters, and the need to minimize risks to the environment and other objects in orbit. As part of the work, a software model was built that takes into account the initial orbital parameters of the device, which are essential for planning and performing deorbiting maneuvers. The model is designed to accurately calculate the descent trajectory, taking into account the laws of celestial mechanics and the influence of atmospheric conditions. The optimal deorbiting strategy was selected based on an analysis of various methods for calculating orbital maneuvers aimed at reducing fuel consumption and minimizing environmental risks. This included a comparative analysis of existing approaches and the selection of the most suitable ones under the given mission parameters. The results of the simulation using precise modeling methods in the MATLAB software environment allowed us to determine the main deorbiting parameters, such as the altitude at which the maneuvers begin, the required velocity impulses, the total fuel consumption, and the expected time before entering the dense layers of the atmosphere. Based on the obtained data, practical recommendations were formulated for the KazEOSat-1 deorbit. The first stage, the active controlled deorbit, is carried out by operating the low-thrust engine and braking by the Earth’s atmosphere, allowing the spacecraft to descend from 758 km to 444 km in 2.5 days. The second stage, the passive uncontrolled deorbit, continues the descent to 103 km in 969 days, using only atmospheric braking. The third stage, the uncontrolled drop, begins after reaching 103 km and ends with a drop to the Earth in 834 seconds


  • Creation of a service for monitoring satellite maneuvers



  • On the probability of stellar encounters in globular clusters
    A. E. Ashurov
    American Astronomical Society
    The number of stellar encounters in a globular cluster per unit time, with given changes in energy and direction of motion relative to the cluster center, has been determined assuming an anisotropic field star distribution function. An exact expression for the integrated probability of such encounters is derived for the case of equal-mass stars, and ranges of physical variables are analyzed. The distributions of the probability and number of encounters in a globular cluster with and without a black hole in the Plummer and King models are also studied. It is shown that the influence of the black hole on the probability distribution almost vanishes at the distance r0 ≈ 1.55rc, where rc is the core radius of the cluster. Moreover, in the area of radius (2–3)r0 strong encounters are significant and the Fokker-Planck approximation cannot be used for modeling the dynamical evolution of globular clusters. The method is developed for determining the probability of distant (weak), as well as close, encounters and for studying the dynamical evolution of globular clusters in the space of the energy integral (E) and angular momentum per unit mass (J) under close encounters.

Publications

An effective method for detecting satellite orbital maneuvers and its application to LEO satellites, published in Advances in Aircraft and Spacecrfaft Science. An International Journal, Vol. 9, No. 4, July 2022, pages 279-300.