scholarly journals Attitude Motion of Cylindrical Space Debris during Its Removal by Ion Beam

2017 ◽  
Vol 2017 ◽  
pp. 1-7 ◽  
Author(s):  
Vladimir S. Aslanov ◽  
Alexander S. Ledkov
Keyword(s):  
Space Debris ◽  
Ion Beam ◽  
Center Of Mass ◽  
Phase Portraits ◽  
Gravity Gradient ◽  
Attitude Motion ◽  
Cylindrical Shape ◽  
Contactless Method ◽  
Large Space ◽  
Ion Flow

The paper is devoted to the problem of space debris mitigation. Contactless method of the space debris deorbiting is considered. It is assumed that ion thrusters on the active spacecraft create the ion flow, which blows the debris and slows it down. The objectives of this work are the development of mathematical models and the research of space debris motion under the action of the ion flow. It is supposed that the space debris is a rigid body of a cylindrical shape. Calculation of ion beam force and torque was performed for a self-similar model of plasma plume expansion using the hypothesis of ion fully diffused reflection from a surface. A mathematical model describing plane motions of the cylindrical space debris under the influence of gravity gradient torque and the ion flux was constructed. It was shown that motion of the space debris around its center of mass has a significant effect on its removal time. Phase portraits, describing the motion of the space debris relative to its center of mass, were constructed. Comparison of the descent times in different motion modes was carried out. The results can be used to create new effective systems of large space debris removal.

scholarly journals Influence of Satellite Motion Control System Parameters on Performance of Space Debris Capturing

Aerospace ◽  
2020 ◽  
Vol 7 (11) ◽  
pp. 160
Author(s):  
Mahdi Akhloumadi ◽  
Danil Ivanov
Keyword(s):  
Control System ◽  
Motion Control ◽  
Control Algorithm ◽  
Space Debris ◽  
Equations Of Motion ◽  
Center Of Mass ◽  
Attitude Motion ◽  
System Parameters ◽  
Thrust Vector ◽  
Rendezvous And Docking

Relative motion control problem for capturing the tumbling space debris object is considered. Onboard thrusters and reaction wheels are used as actuators. The nonlinear coupled relative translational and rotational equations of motion are derived. The SDRE-based control algorithm is applied to the problem. It is taken into account that the thrust vector has misalignment with satellite center of mass, and reaction wheels saturation affects the ability of the satellite to perform the docking maneuver to space debris. The acceptable range of a set of control system parameters for successful rendezvous and docking is studied using numerical simulations taking into account thruster discreteness, actuators constrains, and attitude motion of the tumbling space debris.

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.

Problematic issues of spacecraft development for contactless removal of space debris by ion beam

2021 ◽  
Author(s):  
V.A. Obukhov ◽  
V.A. Kirillov ◽  
V.G. Petukhov ◽  
G.A. Popov ◽  
V.V. Svotina ◽  
...  
Keyword(s):  
Space Debris ◽  
Ion Beam

scholarly journals Roto-Translational Control of Spacecraft in Low Earth Orbit Using Environmental Forces and Torques

2021 ◽  
Vol 11 (10) ◽  
pp. 4606
Author(s):  
Camilo Riano-Rios ◽  
Alberto Fedele ◽  
Riccardo Bevilacqua
Keyword(s):  
Translational Control ◽  
Attitude Control ◽  
Center Of Mass ◽  
Low Earth Orbit ◽  
Gravity Gradient ◽  
Adaptive Controllers ◽  
Attitude Error ◽  
Track Formation ◽  
Relative Orbit ◽  
Along Track

In this paper, relative orbit and attitude adaptive controllers are integrated to perform roto-translational maneuvers for CubeSats equipped with a Drag Maneuvering Device (DMD). The DMD enables the host CubeSat with modulation of aerodynamic forces/torques and gravity gradient torque. Adaptive controllers for independent orbital and attitude maneuvers are revisited to account for traslational-attitude coupling while compensating for uncertainty in parameters such as atmospheric density, drag/lift coefficients, location of the Center of Mass (CoM) and inertia matrix. Uniformly ultimately bounded convergence of the attitude error and relative orbit states is guaranteed by Lyapunov-based stability analysis for the integrated roto-translational maneuver. A simulation example of an along-track formation maneuver between two CubeSats with simultaneous attitude control using only environmental forces and torques is presented to validate the controller.

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 Ion Beam Shepherd for Contactless Space Debris Removal

2011 ◽  
Vol 34 (3) ◽  
pp. 916-920 ◽  
Author(s):  
Claudio Bombardelli ◽  
Jesus Pelaez
Keyword(s):  
Space Debris ◽  
Ion Beam ◽  
Debris Removal
Sign in / Sign up

Export Citation Format

Share Document