Build-Up Schemes and Optimization of the Design Parameters and Orbital Motion Modes of a Combined System for the Space Debris Removing from the Low Near-Earth Orbit

Аuthors

Kul'kov V. M.^*, Yegorov Y. G.^**, Firsyuk S. O.^***

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: vmk_1@mail.ru
**e-mail: yuyeg@mail.ru
***e-mail: iskramai@gmail.com

Abstract

This article addresses the pressing issue of the near-Earth space (NES) contamination by the technogenic space objects (SO), including defunct spacecraft. Various methods for removing the SO from protected areas of the NES (including the low Earth orbit region, a spherical region of the NES with an altitude of no more than 2,000 km from the Earth surface) were analyzed. The options for disposing of space debris by quick removing and towing it into the dense layers of the Earth atmosphere are considered.
The article presents a combined method for the large space debris removing from low Earth orbits with an electric propulsion system (EPS) and aerodynamic braking device (ABD) that allows increasing operational efficiency of the space debris utilization, reducing fuel and energy consumption, and expanding application area of these devices.
The authors elaborated a technique for the design parameters selecting for space objects deorbit system based on the assessment of the deorbit system design options by several indicators with account for the imposed constrictions. The authors considered the composition and operating scheme of the spacecraft deorbiting system option selected as the result of its efficiency evaluation, and disclosed operation principles of the basic system components.
A project model of the orbital motion at the stage of the space object towing by the active spacecraft in the Earth atmosphere while the combined deorbit with account for the dynamically changing solar activity. The article adduced analytical dependencies for both electric propulsion system and aerodynamic system  project parameters computing, so as to  assess combined deorbit efficiency at the rocket-dynamic and aerodynamic flight stages in the wide range of the initial orbit altitude and solar activity level.
A design-ballistic analysis based on the numerical simulation of a spacecraft deorbit allows determining optimal parameters for a low-thrust interorbital transfer from an orbit with an 500–2300 km altitude up to the seizure by the atmosphere. he subject matter of the combined deorbit scheme optimization is a transfer orbit height that determines transfer from the rocket-dynamic to the aerodynamic state  and allows revealing the areas of the electric propulsion system and aerodynamic braking device rational application.
Parametric analysis over a wide range of design-and-ballistic parameters and flight conditions allows determining the design concepts and optimal design parameters and orbital motion modes for the combined deorbit system, with account for dynamically changing solar activity, as well as assessing the ballistic aspects impact on the combined deorbit method effectiveness.
The obtained results represent practical interest for the of modern systems design tasks concerning large space objects removal from low Earth orbits.

Keywords:

space debris, space object, combined deorbiting, electric propulsion system, aerodynamic braking unit

References

1. Space technology items. General requirements for space vehicles for near-earth space debris mitigation. State Standard R 52925-2018. Moscow: Standartinform; 2018. 9 p. (In Russ.).
2.  ESA Space Debris Mitigation Requirements. ESSB-ST-U-007 Issue 1. 2023. 83 p.
3.  Process for Limiting Orbital Debris. NASA Technical Standard NASA-STD-8719.14C. 2021. 77 p.
4.  Earth's upper atmosphere. Density model for design ballistic computation of artificial Earth satellites. State Standard R 25645.101-83. Moscow: Izdatel’stvo standartov; 1984. 168 p. (In Russ.).
5. Earth's upper atmosphere. Density model for ballistic support of artificial Earth satellites flights. State Standard R 25645.166-2004. Moscow: Izdatel’stvo standartov; 2004. 24 p. (In Russ.).
6.  Пикалов Р.С., Юдинцев В.В. Обзор и выбор средств увода крупногабаритного космического мусора. // Труды МАИ. 2018. № 100. DOI: 10.34759/trd-2019-109-1
7. Pikalov RS, Yudintsev VV. Review and selection of large-size space debris removal means. Trudy MAI. 2018(100). (In Russ.).
8.  Trushlyakov VI, Yudintsev VV, Urbansky VA, et al. The analysis of the state of development of devices for cleaning orbits in near-Earth space from large-sized space debris objects. Omsk Scientific Bulletin. Series “Aviation, Rocket and Power Engineering”. 2022;6(4):42-52. (In Russ.).
9.  Trushlyakov VI, Yutkin EA. Overview of means for de-orbiting of large-scale space debris objects as the service operation of spacecraft in orbit. Omskii nauchnyi vestnik. 2015(3):50-56. (In Russ.).
10.  Golubek AV. Optimal Costs for Combined Deorbiting Outsized Orbital Debris Using an Electric Propulsion Engine. BMSTU Journal of Mechanical Engineering. 2022(7):101-111. (In Russ.).
11. Pichkhadze KM, Sysoev VK, Firsyuk SO, et al. Analysis of the design of the drag braking device for CubeSat satellites for withdrawal from low near-Earth orbits. Engineering Journal: Science and Innovations. 2020(5). (In Russ.).
12. Krestina AV, Tkachenko IS, Volgin SS, et al. An aerodynamic de-orbiting system device for small satellites. Engineering Journal: Science and Innovations. 2022(1). (In Russ.).
13.  Roddy M, Huang A. Development of a Solid-State Inflation Balloon Deorbiter. ASME 2016 International Mechanical Engineering Congress and Exposition (November 11-17, 2016; Phoenix, USA). DOI: 10.1115/IMECE2016-67467
14. Finchenko VS, Firsyuk SO, Kulkov VM, et al. To the questionof designing an innovative descent vehicle with a deployable inflatable braking device. Materialy nauchno-tekhnicheskoi konferentsii “Aktual'nye voprosy proektirovaniya avtomaticheskikh kosmicheskikh apparatov dlya fundamental'nykh i prikladnykh nauchnykh issledovanii” (September 04–09, 2017; Anapa). Khimki: NPO im. S.A. Lavochkina; 2017. p. 44-51. (In Russ.).
15. Kul'kov VM, Yoon SW, Firsyuk SO. A small spacecraft motion control method employing inflatable braking units for deceleration while orbital flight prior to the atmospheric entry. Aerospace MAI Journal. 2020;27(3):23-36. (In Russ.).
16.  Koryanov VV, Alifanov OM, Nedogarok AA, et al. Review of the technologies for development the inflatable brake device for deorbiting the space objects. AIP Conference Proceedings. XLIV Academic Space Conference (January 28–31, 2020; Moscow, Russia). 2021;2318(1):110014. DOI: 10.1063/5.0036055
17.  Yoon SW, Kulkov VM, Firsyuk SO, et al. Problems of controlling the motion of small satellite using inflatable thin-film shells for removal space objects from orbit. AIP Conference Proceedings. XLIV Academic Space Conference (January 28–31, 2020; Moscow, Russia). 2021;2318(1):110002. DOI: 10.1063/5.0035800
18. Firsyuk SO, Kulkov VM, Egorov YuG, et al. Spacecraft with aerodynamic braking device for removing space objects from orbit into earth's atmosphere and method for controlling its flight. Patent RU 2748483 C1. Bull. 15, 26.05.2021. (In Russ.).
19. Anshakov GP, Krestina AV, Tkachenko IS. Analysis of the effectiveness of the de-orbiting devices for small satellite. Spacecraft & Technologies. 2020;4(2):72-84. (In Russ.).
20. Marakhtanov MK, Pil'nikov AV. On solar electric propulsion system application possibility for low-orbit small spacecraft. Aerospace MAI Journal. 2017;24(4):26-39. (In Russ.).
21. Popov GA, Kul’kov VM, Petukhov VG, et al. A space platform with an electric rocket propulsion system in combination with an air launch vehicle. In: Rezul’taty fundamental’nykh issledovanii v prikladnykh zadachakh aviastroeniya: Sbornik statei. Moscow: Nauka; 2016. 175-186. (In Russ.).
22. Petukhov VG. Optimization of multi-orbit transfers between noncoplanar elliptic orbits. Cosmic Research. 2004;42(3):250-268