Assessing the possibility of using a variable-length launch vehicle with a polymer body for orbiting payload

Authors

DOI:

https://doi.org/10.15587/1729-4061.2024.306225

Keywords:

launch vehicle, variable length, polymer body, aerodynamic characteristics, suborbital trajectory

Abstract

The object of this study was the motion of an ultralight class variable-length launch vehicle made of a polymer body along the active phase of the trajectory. The work considers the solution to the problem of designing low-cost means of delivery to orbit, namely to the assessment of the possibility of removing the payload by a carrier rocket with a polymer body of variable length beyond the dense atmosphere of the Earth. For this purpose, ballistic projection of the trajectory of the launch vehicle was carried out taking into account overloading; its aerodynamic characteristics and peculiarities of aerothermodynamic processes occurring during flight in the atmospheric phase of the trajectory were determined. The closeness (up to 10 %) of the obtained results with known experimental data is shown. The influence of the aerodynamic force on the parameters of the launch vehicle motion was studied. A flight simulation was conducted, the results of which showed the fundamental possibility of launching a CubeSat 24U class payload using a launch vehicle with a polymer body of variable length to a suborbital trajectory with an altitude of about 300 km. At the same time, the effective longitudinal overload on the body of the launch vehicle does not exceed 4 units, and the temperature on the surface of the body does not exceed 300 K. A feature of the research is the use of a multidisciplinary approach, which implies taking into account the interrelationship of aerodynamic, thermodynamic, and ballistic processes. The established motion parameters, aerodynamic characteristics, and the surface heating temperature of the launch vehicle body are key values for further research on the design and analysis of a launch vehicle with a polymer body of variable length. These data could be used to calculate the mechanical and thermal loads acting on the structure of the launch vehicle during flight

Author Biographies

Aleksandr Golubek, Oles Honchar Dnipro National University

Doctor of Technical Sciences, Professor

Department of Cyber Security and Computer-Integrated Technologies

Serhii Aleksieienko, Dnipro University of Technology

Doctor of Technical Sciences, Professor

Department of Mechanical Engineering Technology and Materials Science

Mykola Dron, Oles Honchar Dnipro National University

Doctor of Technical Sciences, Professor

Department of Rocket and Space and Innovative Technologies

Andrii Dreus, Oles Honchar Dnipro National University

Doctor of Technical Sciences, Professor

Department of Fluid Mechanics and Energy and Mass Transfer

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Assessing the possibility of using a variable-length launch vehicle with a polymer body for orbiting payload

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Published

2024-06-28

How to Cite

Golubek, A., Aleksieienko, S., Dron, M., & Dreus, A. (2024). Assessing the possibility of using a variable-length launch vehicle with a polymer body for orbiting payload. Eastern-European Journal of Enterprise Technologies, 3(7 (129), 63–72. https://doi.org/10.15587/1729-4061.2024.306225

Issue

Vol. 3 No. 7 (129) (2024): Applied mechanics

Section

Applied mechanics

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Copyright (c) 2024 Aleksandr Golubek, Serhii Aleksieienko, Mykola Dron, Andrii Dreus

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