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
Keywords:upper stage of launch vehicle, aerodynamic deorbit system, design parameters
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.
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