I am a member of the research group led by Prof. Vladimir S. Aslanov.
My research interests are:
space flight mechanics,
spacecraft attitude dynamics,
spacecraft aerodynamics (especially small satellites) in low orbits,
re-entry ballistics,
space tethered systems,
active space debris removal.
I am also a Reviewer for several Q1/Q2 journals in the field (Aerospace, Mathematics, Energies, Applied Sciences).
V. S. Aslanov, D. A. Sizov VLEO CubeSat attitude dynamics during and after flexible panels deployment
using torsion springs (Acta Astronautica 210 (2023), pp. 117–128)
This paper deals with the attitude motion of VLEO CubeSats during and after the deployment of flexible
stabilizing panels driven by torsion springs. Unlike in higher orbits, in VLEO, the attitude motion of the satellite
is primarily influenced by the interaction with the atmosphere. Therefore, in order to study the evolution of the
satellite attitude during the panels deployment, we considered not only the torques from the torsion springs and
the elastic oscillations of the flexible panels, but also the restoring and damping aerodynamic torques, which
depend on the satellite shape and thus change substantially during the panels deployment process. Numerical
simulations show that if the satellite has intermediate stable equilibrium positions, the combined effect of all
above-mentioned torques may result in qualitatively different regimes of oscillations in the angle of attack
after the deployment. These oscillations have low-frequency harmonics, related to the aerodynamic torque,
and a high-frequency one, induced by the elastic oscillations of the panels after the collisions in the system
caused by panels latching. The amplitude of the high-frequency oscillations depends on the post-collision state
of the system, which is found analytically using the Appell algorithm. The post-collision state, in its turn,
depends on the inevitable inaccuracies of the deployment process, causing the panels to start their rotation
at slightly different moments in time. As a result of the study, recommendations for the torsion spring-driven
panels deployment in VLEO are formulated. Their focus is to maintain the attitude stability of the satellite
and reduce the vibrations of its body in presence of disturbances, such as elastic oscillations of the panels
themselves or uneven panels deployment.
DOI
V. S. Aslanov, D. A. Sizov Attitude Dynamics of Spinning Magnetic LEO/VLEO Satellites (Aerospace, 2023)
With the growing popularity of small satellites, the interaction with the air in low and especially in very low Earth orbits becomes a significant resource for passive angular stabilisation. However, the possibility of spin motion remains a considerable challenge for missions involving aerodynamically stabilised satellites. The goal of this paper was to investigate the attitude motion of arbitrarily spinning satellites in LEO and VLEO under the action of aerodynamic, gravitational, and magnetic torques, taking into account the aerodynamic damping. Using an umbrella-shaped deployable satellite as an example, the study demonstrated that both regular and chaotic attitude regimes are possible in the attitude motion. The occurrence of chaos was verified by means of Poincaré sections. The results revealed that, to prevent chaotic motion, active attitude control and reliable deployment techniques for aerodynamically stabilised satellites are needed. DOI Download paper
V. S. Aslanov, D. A. Sizov Chaotic pitch motion of an aerodynamically stabilized magnetic satellite in
polar orbits (Chaos, Solitons, and Fractals, 2022)
The paper is devoted to the chaotic attitude dynamics of magnetic satellites with stabilizing panels. The pitch motion under the gravitational and restoring aerodynamic torques and small perturbations, namely, the magnetic torque and the aerodynamic damping, is considered. On the example of a CubeSat having an aerodynamic instability, it is demonstrated that the unperturbed phase space evolves with orbital altitude both quantitatively and qualitatively, forming different sets of homoclinic and heteroclinic trajectories. The Melnikov method is used to find the combinations of system parameters resulting in regular and chaotic motions. The occurrence of chaos is verified by means of Poincaré sections.
V. S. Aslanov, D. A. Sizov Chaos in flexible CubeSat attitude motion due to aerodynamic instability (Acta Astronautica, 2021)
CubeSats, small satellites the size of shoeboxes or even smaller, are becoming increasingly popular around the world. They are simple and inexpensive, and are now being launched en masse by various universities to study both Earth and solar system bodies. Cubsats flying in low-Earth orbits sometimes have tail fins to take advantage of the stabilizing effect of interaction with the rarefied atmosphere. However, it may so happen that a satellite suddenly starts to rotate unpredictably (chaotically) due to various disturbances, e.g. elastic vibrations of the tail panels, which cannot be perfectly rigid. The article investigates this very phenomenon.
DOI Download paper
D. A. Sizov, V. S. Aslanov Space Debris Removal with Harpoon Assistance: Choice of Parameters and Optimization (J. of Guidance, Control, and Dynamics, 2020)
This paper discusses three phases of the space debris removal with harpoon assistance: capture, tether deployment, and towing. The harpoon impact momentum is used to detumble the target. Equations of motion for each phase are given in dimensionless form, which significantly reduces the number of parameters describing the system. The aim of the paper is to propose algorithms for choosing optimal parameters for the capture and tether deployment phases. This optimization provides small amplitudes of the tether and debris oscillations during towing. The numerical simulations of the removal of a spent Ariane 4 upper stage H10 confirm the correctness of the proposed mathematical models and optimization algorithms.
DOI Download paper
V. S. Aslanov, D. A. Sizov A spent upper stage removal mission aimed to reduce debris impact footprint size (Acta Astronautica, 2020)
A process of a spent upper stage removal from low Earth orbit is considered, which consists of three phases: towing of the stage using a tether; descent of the stage into the low-density atmosphere; motion of its debris fragments after the breakup caused by the aerodynamic and thermal loads. It is shown that the attitude motion of the stage during its descent largely affects its breakup altitude and consequently the size of debris impact footprint and its position on the surface of the Earth. A certain number of ways to reduce the footprint extent are proposed. As an example of using the proposed method, a numerical simulation of the removal of a spent Ariane 4 upper stage H10 was performed. The results of the study can be used for planning missions to clean up space debris from low Earth orbit.
More papers on my Scopus page
Dmitry Sizov. Personal webpage
Copyright © 2023 Dmitry Sizov. Personal webpage - Все права защищены.
На платформе GoDaddy
Мы используем файлы cookie для анализа трафика сайта и оптимизации вашего сайта. Принимая условия использования файлов cookie, ваши данные будут объединены со всеми другими пользовательскими данными.