Space debris in low earth orbits region: Formation and reduction process analysis in past decade

2021 ◽  
Author(s):  
A.I. Nazarenko ◽  
I.V. Usovik
Keyword(s):  
Space Debris ◽  
Process Analysis ◽  
Reduction Process ◽  
Low Earth Orbits ◽  
Earth Orbits

scholarly journals Resonant Orbital Dynamics in LEO Region: Space Debris in Focus

2014 ◽  
Vol 2014 ◽  
pp. 1-12 ◽  
Author(s):  
J. C. Sampaio ◽  
E. Wnuk ◽  
R. Vilhena de Moraes ◽  
S. S. Fernandes
Keyword(s):  
Collision Avoidance ◽  
Frequency Analysis ◽  
Space Debris ◽  
Semimajor Axis ◽  
Orbital Dynamics ◽  
Accurate Information ◽  
The Earth ◽  
Low Earth Orbits ◽  
Line Elements ◽  
Earth Orbits

The increasing number of objects orbiting the earth justifies the great attention and interest in the observation, spacecraft protection, and collision avoidance. These studies involve different disturbances and resonances in the orbital motions of these objects distributed by the distinct altitudes. In this work, objects in resonant orbital motions are studied in low earth orbits. Using the two-line elements (TLE) of the NORAD, resonant angles and resonant periods associated with real motions are described, providing more accurate information to develop an analytical model that describes a certain resonance. The time behaviors of the semimajor axis, eccentricity, and inclination of some space debris are studied. Possible irregular motions are observed by the frequency analysis and by the presence of different resonant angles describing the orbital dynamics of these objects.

scholarly journals Out-of-plane relative motion of a spacecraft with an aerodynamic compensator during contactless space debris removal

2021 ◽  
Vol 27 (2) ◽  
pp. 15-27
Author(s):  
A.A. Fokov ◽  
◽  
S.V. Khoroshylov ◽  
D.S. Svorobin ◽  
◽  
...  
Keyword(s):  
Relative Motion ◽  
Space Debris ◽  
Ion Beam ◽  
Reaction Force ◽  
Orbital Plane ◽  
Cross Sectional ◽  
Out Of Plane ◽  
Simplifying Assumptions ◽  
Low Earth Orbits ◽  
Earth Orbits

The article investigates the feasibility of using an aerodynamic compensator for contactless removal of space debris from low Earth orbits, taking into account aerodynamic disturbances in the direction perpendicular to the orbital plane. The object of the research is a modified scheme of the “ion beam shepherd” de-orbiting concept. The modification consists in replacing an additional electric thruster with an aerodynamic compensator designed to compensate the shepherd spacecraft motion caused by the reaction force of the main electric thruster, the ion plume of which creates a “braking” effect on the space debris object. The shepherd spacecraft with the aerodynamic compensator has a relatively large cross-sectional area. In this case, it is necessary to control the relative motion caused by the aerodynamic disturbances in the direction perpendicular to the orbital plane. This control requires additional propellant for the thrusters of the relative motion control system of the shepherd spacecraft. The article presents the calculation of the propellant consumption using a number of simplifying assumptions. The validity of these assumptions is verified by numerical integration of the equations of relative motion. The feasibility of using the aerodynamic compensator for contactless removal of space debris, taking into account aerodynamic disturbances acting in the direction perpendicular to the orbital plane, is shown.

scholarly journals Defunct Satellites in Nearly Polar Orbits: Long-term Evolution of Attitude Motion

2018 ◽  
Vol 27 (1) ◽  
pp. 264-277 ◽  
Author(s):  
Dmitry Pritykin ◽  
Sergey Efimov ◽  
Vladislav Sidorenko
Keyword(s):  
Space Debris ◽  
Eddy Currents ◽  
Intermediate Phase ◽  
Gravity Gradient ◽  
Attitude Motion ◽  
Attitude Dynamics ◽  
Ellipsoid Of Revolution ◽  
Low Earth Orbits ◽  
High Space ◽  
Earth Orbits

Abstract Low Earth orbits (LEO) are known as a region of high space activity and, consequently, space debris highest density. Launcher upper stages and defunct satellites are the largest space debris objects, whose collisions can result in still greater pollution, rendering further space missions in LEO impossible. Thus, space debris remediation is necessary, and the LEO region is a primary target of active debris removal (ADR) projects. However, ADR planning requires at least an approximate idea of the candidate objects’ attitude dynamics, which is one of the incentives for our study. This paper is mainly focused on modeling and simulating the attitude dynamics of defunct satellites. We consider a “boxwing” configuration satellite with an ellipsoid of inertia close to an oblate ellipsoid of revolution. The dynamical model takes into account the gravity-gradient torque, the torque due to the residual magnetic moment, and the torque due to eddy currents induced by the interaction of conductive materials with the geomagnetic field. A better understanding of the intermediate phase of the exponential deceleration and existing final regimes is achieved owing to a more accurate model of the eddy-current torque than in most prior research.We also show the importance of orbital precession, which contributes to the overall attitude motion evolution.

Large-size space debris flyby in low earth orbits

2017 ◽  
Vol 55 (5) ◽  
pp. 361-370 ◽  
Author(s):  
A. A. Baranov ◽  
D. A. Grishko ◽  
Y. N. Razoumny
Keyword(s):  
Space Debris ◽  
Large Size ◽  
Low Earth Orbits ◽  
Earth Orbits

Space debris monitoring based on inter-continental stereoscopic detections

2020 ◽  
Author(s):  
Alessandro Sozza ◽  
Massimo Cencini ◽  
Leonardo Parisi ◽  
Marco Acernese ◽  
Fabio Santoni ◽  
...  
Keyword(s):  
Space Debris ◽  
European Space Agency ◽  
Three Dimensional ◽  
Reconstruction Method ◽  
Space Agency ◽  
Space Objects ◽  
Dimensional Reconstruction ◽  
Low Earth Orbits ◽  
Earth Orbits ◽  
The Impact

<p>The monitoring of space debris and satellites orbiting around Earth is an essential topic in the space surveillance. The impact of debris, even of small size, against active spatial installations causes serious damage, malfunctions and potential service interruptions. Collision-avoidance maneuverings are often performed but they require increasingly complex protocols. Density of space debris is now so high that even astronomical observations are often degraded by it. Although it does not affect space weather, it may interfere with weather satellites.<br>We have developed an innovative experimental technique based on stereometry at intercontinental scale to obtain simultaneous images from two optic observatories, installed in Rome (at the Urbe Airport and in Collepardo on the Apennines) and in Malindi (Kenya). From the observations on Earth, it's possible to reconstruct the three-dimensional position and velocity of the objects. The distance between the two observatories is crucial for an accurate reconstruction. In particular, we have considered the sites of Urbe and Collepardo, with a baseline of 80 km, to detected Low-Earth orbits (LEO), while we have considered a baseline of 6000 km, between Urbe and Malindi, to observe geostationary orbits (GEO).<br>We will present the validation of the three-dimensional reconstruction method via a fully synthetic procedure that propagate the satellite trajectory, using SGP4 model and TLEs data (provided by NASA), and generate synthetic photographs of the satellite passage from the two observatories. Then we will compare the synthetic results with the experimental results obtained using real optic systems. The procedure can be automatized to identify unknown space objects and even generalized for an arbitrary number of sites of observation. The identified debris will be added to the catalogue DISCOS (Database and Information System Characterizing Objects in Space) owned by the European Space Agency (ESA) to improve the space surveillance and the ability to intervene in the case of potential risks. </p>

Atmosphere density changes caused by the motion of spacecrafts in low Earth orbits

2009 ◽  
Vol 15 (1) ◽  
pp. 13-18 ◽  
Author(s):  
A.I. Maslova ◽  
◽  
A.V. Pirozhenko ◽  
Keyword(s):  
Atmosphere Density ◽  
Low Earth Orbits ◽  
Earth Orbits

scholarly journals Analysis of the advantages of an aerodynamic compensator in contactless space debris removal

2020 ◽  
Vol 2020 (4) ◽  
pp. 55-64
Author(s):  
A.A. Fokov ◽  
◽  
S.V. Khoroshylov ◽  
D.S. Svorobin ◽  
◽  
...  
Keyword(s):  
Control System ◽  
Space Debris ◽  
Position Control ◽  
Ion Beam ◽  
Orbital Plane ◽  
Cross Sectional ◽  
Debris Removal ◽  
Low Earth Orbits ◽  
The Cost ◽  
Propellant Consumption

A modified scheme of the known technology for contactless space debris removal, which is called Ion Beam Shepherd, is considered. This scheme uses an aerodynamic compensator in order to reduce the propellant consumption of the additional electrojet thruster of the shepherd spacecraft. The thruster serves to compensate the spacecraft motion caused by the action of the main electrojet thruster, whose ion plume “brakes” the space debris object. The aerodynamic compensator significantly increases the spacecraft cross-sectional area compared to the space debris object one. This fact, together with the aerodynamic perturbations acting in the direction perpendicular to the orbital plane, calls for estimating the propellant consumption of the control system thruster to maintain the required position of the spacecraft relative to the space debris object in that direction. The goal of this article is to identify the advantages of using the aerodynamic compensator in space debris removal from low Earth orbits using the Ion Beam Shepherd technology. The tasks of the study are to estimate the reduction in the cost of the momentum of the additional electrojet thruster during contactless space debris object de-orbiting due to the use of the aerodynamic compensator and the additional cost of the momentum of the thruster of the spacecraft – space debris object relative position control system to correct deviations perpendicular to the orbital plane. Using a number of simplifying assumptions, integral estimates of these costs are obtained. Using these cost estimates, it is shown that the use of an aerodynamic compensator is advantageous in terms of the cost of the saved electrojet thruster propellant (xenon) regardless of the type of the spacecraft control system thruster.

scholarly journals Solar radiation pressure resonances in Low Earth Orbits

2017 ◽  
Vol 473 (2) ◽  
pp. 2407-2414 ◽  
Author(s):  
Elisa Maria Alessi ◽  
Giulia Schettino ◽  
Alessandro Rossi ◽  
Giovanni B. Valsecchi
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Solar Radiation Pressure ◽  
Low Earth Orbits ◽  
Earth Orbits
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