DEVELOPMENT OF R&D FRAMEWORK FOR THE MODERNIZATION OF THE AERODYNAMIC DEORBIT SYSTEM FOR THE USE IN THE UPPER STAGE OF CYCLONE-1M LAUNCH VEHICLE
DOI:
https://doi.org/10.15407/scine18.06.060Keywords:
upper stage of launch vehicle, aerodynamic deorbit system, design parametersAbstract
Introduction. Growing interest in space exploration and new satellite navigation and communication technologies has led to an increase in the number of spacecraft in Earth orbits and the formation of orbital groups. Today,
spacecraft are launched into Earth orbits mainly by launch vehicles, the defunct upper stages of which, after the
spacecraft launch, remain in Earth orbits and become the one of the sources of space debris (SD).
Problem Statement. The problem of increasing the number of SD is one of the key issues in modern cosmonautics. A significant accumulation of SD fragments on some clusters of orbits may cause significant obstacles to operating spacecraft and lead to global problems (the Kessler effect). One of the sources of SD growth is defunct
upper stages of launch vehicles (LV). Means for deorbiting LV upper stages from near-Earth orbits needs to be
designed urgently. In turn, the light class LV Cyclone-1M created by the Yangel Pivdenne Design Office is one of
the promising developments.
Purpose. Development of R&D framework for the modernization of aerodynamic deorbit system for its use
in the upper stage of the Cyclone-1M launch vehicle.
Material and Methods. Methods of applied mechanics, mathematical and computer modeling of spacecraft motion.
Results. The R&D framework for the creation of a new aerodynamic deorbit system (ADS) of the Cyclone1M upper stage has been developed. A new design of the aerodynamic element of the ADS in the form of three
orthogonally placed round disks, which allows raising the ADS efficiency, has been created. The design scheme and manufacturing technology of the container for the ADS storage on the upper stage of the Cyclone-1M launch vehicle with the use of honeycomb technologies, which allows minimizing the weight of the system, have been proposed.
Conclusions. The proposed development has enabled raising the ADS efficiency in the case of non-oriented angular motion during the deorbit of launch vehicles and reducing the weight of the storage system.
References
Raws, M. L., Thiemann, H. B., Chemin, V., Walcowicz, L., Peel, M. W., Grange, Y. G. (2020). Satellite Constellation Internet Affordability and Need. Typeset using LATEX RNAAS style in AASTeX63. URL: https://arxiv.org/pdf/2011.05168.pdf (Last accessed: 30.10.2021).
The Orbital Debris Quarterly News. (2021). NASA JSC Houston, 25(1), 10-12.
The presentation of the promising rocket-space complex of the light class "Cyclone-1M" was reviewed. Aerokosmichny portal Space.com.ua. URL: https://space.com.ua/2019/04/22/vidbulasya-prezentatsiya-perspektivnogo-raketno-kosmichnogokompleksu-legkogo-klasu-tsiklon-1m/ (Last accessed: 30.10.2021).
Lovell, T. A., Tragesser, S. (2004). Guidance for Relative Motion of Low Earth Orbit Spacecraft Based on Relative Orbit Elements. AIAA Paper 2004-4988, presented at the AAS/AIAA Astrodynamics Specialist Conference. Providence, RI. https://doi.org/10.2514/6.2004-4988
Paliy, A. S. (2012). Methods and means of spacecraft deorbiting from operating orbits (state of the problem). Technical mechanics. 1, 94-102 [іn Russian].
Alpatov, A. P. (2018). Space debris: the aspects of the problem. Techical mechanics, 1, 30-47. [іn Russian]. https://doi.org/10.15407/itm2018.01.030
Pikalov, R. S., Yudintsev, V. V. (2018). Review and selection of means for removing large-sized space debris. Proceedings of the MAI. 100. URL: http://trudymai.ru/upload/iblock/239/Pikalov_YUdintsev_rus.pdf?lang=ru&issue=100 (Last accessed: 30.10.2021) [іn Russian].
Lapkhanov, Е. О. (2019). Features of the development of means for spacecraft removal from near-Earth operational orbits. Technical mechanics, 2, 16-30. [іn Ukrainian]. https://doi.org/10.15407/itm2019.02.016
Golubek, A., Dron, M., Dubovik, L., Dreus, A., Kulyk, O., Khorolskiy, P. (2020). Development of the combined method to de-orbit space objects using an electric rocket propulsion system. Eastern-European Journal of Enterprise Technologies, 4(5(106)), 78-87. https://doi.org/10.15587/1729-4061.2020.210378
Dron, M., Golubek, O., Dubovik, L., Dreus, A., Heti, K. (2019). Analysis of the Ballistic Aspects of the Combined Method of Deorbiting Space Objects From the Near-Earth Orbits. Eastern-European Journal of Enterprise Technologies, 2(5(98)), 49-54. https://doi.org/10.15587/1729-4061.2019.161778
Lapkhanov, E., Khoroshylov, S. (2019). Development of the aeromagnetic space debris deorbiting system. Eastern-European Journal of Enterprise Technologies, 5(5(101)), 30-37.
https://doi.org/10.15587/1729-4061.2019.179382
Anderson, J. L. NASA's Nanosail-D 'Sails' Home - Mission Complete. NASA.gov. URL: https://www.nasa.gov/mission_ pages/smallsats/11-148.html (Last accessed: 30.10.2021).
MMA Design. Drag NET De-orbit system. URL: https://mmadesignllc.com/product/dragnet-de-orbit-system/ (Last accessed: 30.10.2021).
Bonin, G., Hiemstra, J., Sears, T., Zee, R. E. (2013). The CanX-7 Drag Sail Demonstration Mission: Enabling Environmental Stewarship for Nano- and Microsatellites. 27th Annual AIAA/USU Conference on Small Satellites (12-15 August, 2013, Logan, USA). URL: https://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=2993&context=smallsat (Last accessed: 30.10.2021).
Underwood, C., Viquerat, A., Schenk, M., Taylor, B., Massimiani, C., …, Denis, A. (2019). Inflatesail de-orbit flight demonstration results and follow-on drag-sail applications. Acta Astronautica, 162, 344-358. https://doi.org/10.1016/j.actaastro.2019.05.054
Aglietti, G. S., Taylor, B., Fellowes, S., Salmon, T., Retat, I., …, Steyn, W. H. (2020). The active space debris removal mission Remove Debris. Part 2: in orbit operations. Acta Astronautica, 168, 310-322. URL: https://hal.inria.fr/hal-02286751/ document (Last accessed: 30.10.2021).
https://doi.org/10.1016/j.actaastro.2019.09.001
Yost, B., Weston, S. (2020). Small Spacecraft Technology. State-of-the-Art. National Aeronautics and Space Administration (NASA) Center for AeroSpace Information. URL: https://www.nasa.gov/sites/default/files/atoms/files/soa2020_ final3.pdf (Last accessed: 30.10.2021).
Alpatov, A. P., Paliy, O. S., Skorik, О. D. (2017). The Development of Structural Design and the Selection of Design Parameters of Aerodynamic Systems for De-orbiting Upper-stage Rocket Launcher. Nauka innov., 13(4), 33-45. https://doi.org/10.15407/scin13.03.033
Fortescue, P., Stark, J., Swinerd, G. (2011). Spacecraft systems engineering. John Wiley & Sons Ltd. Chichester. https://doi.org/10.1002/9781119971009
Bordovitsina, T. V. (1984). Modern numerical methods in problems of celestial mechanics. Moscow: Nauka.
Mirer, S. A. (2007). Space flight mechanics. Orbital motion. Moscow: Resolite.
ECSS-E-ST-10-04C. Space engineering, Space environment. (2008). Noordwijk: ECSS Secretariat, ESA-ESTEC, Requirements & Standards Division, 198.
Alpatov, A. P., Astapenko, V. N., Antonenko, M. E. et al. (2007, May) Use of honeycomb structures in space vehicles. The effectiveness of honeycomb structures in products of aerospace technology: collection of articles. materials of the II int. scientific-practical conf., (23-25 May, 2007, Dnipropetrovsk, Ukraine). Dnepropetrovsk, 27-28 [іn Russian].
Gaidachuk, A. V., Karpikova, A. V., Kondratev, A. V., Slivinsky, M. V. (2012). Cell fillers and honeycomb structures for space purposes: monograph. Technological imperfections of honeycomb fillers and structures (Еd. Gaidachuk A. V.). Kharkіv: National aerospace univwrsity. "Khark. Aviation Institute" [іn Russian].
Album Developed by LTD Research and Production Enterprise "NIKE" on honeycomb fillers and honeycomb structures for aviation, rocket and space technology and conversion. URL: http://www225.dts.dp.ua/administrator/pdf/temp/album_ honeycomb_rus.pdf. (Last accessed: 30.10.2021).
ASTMD 7249/D 7249M-06. (2006). Standard test method for facing properties of sandwich constructions by long beam flexure. American Society for Testing and Materials. Philadelphia West Conshohocken, PA : ASTM, 9.
Downloads
Published
How to Cite
Issue
Section
License
Copyright (c) 2022 Copyright Notice Authors published in the journal “Science and Innovation” agree to the following conditions: Authors retain copyright and grant the journal the right of first publication. Authors may enter into separate, additional contractual agreements for non-exclusive distribution of the version of their work (article) published in the journal “Science and Innovation” (for example, place it in an institutional repository or publish in their book), while confirming its initial publication in the journal “Science and innovation.” Authors are allowed to place their work on the Internet (for example, in institutional repositories or on their website).
This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.
