# Vladimir AslanovSamara National Research University · Theoretical Mechanics

Vladimir Aslanov

Professor

## About

152

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Citations since 2016

## Publications

Publications (152)

This book provides an overview of the cutting-edge research on the topic of contactless ion beam transportation for the removal of space debris. It covers topics such as space debris attitude motion, the motion of rigid bodies in an inhomogeneous high-speed rarefied medium, gravity gradient torque, and more. It examines and compares the various way...

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 demonst...

The paper focuses on the development of a new mission to explore Phobos using an anchored tether system located below the L1 Mars–Phobos libration point and deployed toward Mars at a length slightly greater than the distance from Phobos. The basic assumptions in terms of a planar circular restricted three-body problem are formulated. The motion equ...

Available until November 2022 at the link: https://authors.elsevier.com/c/1fnxc1LW8X6ZXr
Space debris is one of the most urgent issues of modern astronautics, which solution requires a systematic and coordinated efforts of international community. Several lines of action can be identified to combat the space debris threat including improvement of...

The paper deals with the attitude dynamics of CubeSats with flexible stabilizing panels in free molecular flow taking into account the aerodynamic damping. In addition to the operating position, characterized by zero angle of attack, aerodynamically stabilized satellites may have intermediate equilibrium positions. The presence of unstable equilibr...

The paper focuses on the study and development of a mission to use the L1 libration point for deployment of a tether system in the direction of a moon in the planar elliptic restricted three-body problem on the example of the Mars-Phobos system. An orbiting spacecraft, which deploys the tether system, is located at the L1 libration point and is hel...

The paper considers the contactless transportation of space debris by means of an ion beam generated by an active spacecraft electrodynamic engine. The three-dimensional motion of a space debris object relative to its center of mass is studied. Space debris is assumed to be a dynamically symmetric cylindrical rigid body. The aim of the paper is to...

Contactless space debris removal systems are the promising direction for solving the space debris problem. An ion beam transportation method is based on blowing the space debris with a high-speed plasma flow generated by the engine of an active spacecraft. The aim of the work is to evaluate the effect of controlling the attitude motion of space deb...

This paper explores the feasibility and benefits of a new way of the Phobos sample return delivery mission to a
Phobos Sample Return (PSR) orbiter using the electrostatic field artificially generated in proximity to the Mars–
Phobos L1 libration point. The proposed method uses the electrostatic interaction to retrieve an orbit sample
container (OS)...

The process of removal of a passive object by an active spacecraft is considered. It consists of three phases: harpoon capture, tether deployment and towing. The impact impulse from the harpoon is used to reduce the angular velocity of the target and to drive it into a towing state. A thrust control law for the tether deployment phase is proposed a...

This paper focuses on the study of a new type of a planar, circular restricted three-body problem with an attractive artificial electrostatic field (E-field) at collinear libration points. For instance, this attractive field can be generated by an orbiting spacecraft located at the Mars-Phobos L1 libration point and an electrostatic capsule launche...

This paper describes a process for identifying the intact objects in orbit that (a) pose the greatest debris-generating potential risk to operational satellites or (b) would reduce the risk the most if they were removed or prevented from colliding with each other (i.e., remediated). To accomplish this, a number of diverse, international space organ...

This paper deals with the attitude motion of LEO satellites with deployable side panels designed for passive aerodynamic stabilization in a rarefied atmosphere. The influence of the aerodynamic and gravitational torques on the planar attitude motion near the unstable and stable equilibrium positions is studied. The presence of the unstable equilibr...

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 pape...

This Special Section of Acta Astronautica contains peer-reviewed papers selected from the contributions of the participants at the Sixth International Conference on Tethers in Space (TiS 2019), held June 12–14, 2019 at Universidad Carlos III de Madrid (UC3M), Spain. TiS 2019 provided continuity to TiS 2016, which was held at The University of Michi...

The space debris removal is one of the most important challenges of astronautics. The creation of contactless transportation systems based on the ion beam is a promising direction for solving this problem. The orientation of the debris object in the ion beam has a great influence on the magnitude and direction of the force transmitted by this beam....

The development of systems for transporting space objects by an active spacecraft is an urgent task of modern astronautics. One of the promising areas in this field is contactless ion beam transport systems. The goals of this work are to study a space object attitude motion dynamics during its contactless transportation and the influence of this mo...

The 3U CubeSat with deployable side panels designed for passive aerodynamic stabilization in a rarefied atmosphere is considered. The goal of this study is to increase the orbital lifetime of the satellite by modification of its nose section. It is shown that the pyramidal nose substantially decreases the aerodynamic drag of the satellite and, cons...

The attitude motion of a small satellite with deployable side panels designed for passive aerodynamic stabilization in a rarefied atmosphere is considered. The influence of the aerodynamic and gravitational torques on the motion near the unstable and stable equilibrium positions is studied. The presence of the unstable equilibrium position and flex...

The attitude dynamics of a cylindrical body under the action of an ion beam generated by the low-thrust engine of an active spacecraft is studied. The aim of the work is the analysis of chaotic and regular attitude motion of the body during contactless transportation. The eccentricity of the orbit could cause chaotic motion of the system. A simplif...

The rendezvous of two spacecraft (passive and active) using a tether system is studied. Two laws of the tether control are proposed to ensure the safe rendezvous of bodies. A minimum allowable thrust of the active spacecraft and the parameters of the tether control laws are defined, under which the rendezvous is implemented safe. Based on the resul...

The paper considers the process of removing a passive object by an active spacecraft, consisting of three stages: harpooning the object, deploying the tether, and towing. The shock pulse from the harpoon is used to reduce the angular velocity of the object and transfer it to the towing state. An algorithm for determining the position of the capture...

The paper is devoted to the issue of active large space debris removal. The contactless method of influencing space debris through the electrostatic interaction is considered. The main advantages of this method are possibility of space debris removal in geosynchronous orbit with low energy costs and absence of a dangerous and complex stage of space...

The use of ion flow for the implementation of contactless force action transmission from an active spacecraft to a passive object is a promising technology for the creation of active large space debris removal systems. Keeping a certain orientation of large space debris with respect to the oncoming ion stream in the process of its removal from the...

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...

This research is devoted to the problem of delivering a small payload to the Earth from the orbit using an orbital space elevator, which consists of two space stations connected by a massless tether and a passive climber moving along the tether. The aim of the work is to study the possibility of transferring the climber from one end of the orbital...

The aim of this paper is to generate a feedback control law of the space tug and debris for the removal and detumbling of the space debris or defunct satellites using electrostatic forces. The goal is to provide a stable relative motion of the tug and the debris, both in terms of translation and rotation. With the spacecraft and debris nominally ch...

A new way to removal small space debris using a heavy collector in GEO is considered. The proposed scenario involves three types of consecutive maneuvers: capturing of debris into an area bounded by Hill sphere of the heavy collector, towing and discharging debris in a graveyard orbit. The plane motion equations of the debris relative to the collec...

Attitude dynamics of nanosatellites with a module on retractable beams is considered. The movable module is attached to the main body of the nanosatellite with the help of retractable beams of variable length. The attitude control is fulfilling by the beams length changing that translates the position of the mass center and creates the torque from...

Space debris removal by a low thrust tethered spacecraft is considered in this paper. The objective of the work is the development of a simplified mathematical model describing the perturbed motion of the space tethered system under the influence of the aerodynamic drag forces and low thrust of the spacecraft’s engines and study the evolution of th...

The paper focuses on the study of stability of a pendulum with a moving mass in the vicinity of equilibrium position. The control law of the relative motion of the moving mass is considered as given. A small parameter is introduced that characterizes the magnitude of small disturbance caused by the relative motion of the moving mass. Using the aver...

The simple principle of space debris capture was based on the use of the heavy orbital collector placed so that space debris is in an attraction area of the collector confined to the Hill sphere. The basic idea of the proposed method was confirmed by numerical integration of the motion equation of the debris in polar coordinates relative to the col...

The developed mathematical model of the tethered tug–debris satellite system with the debris object, considered as a rigid body, allows exploration of the motion of the system during the active debris removal missions. The debris object as a rigid body slightly affects the stationary solutions of the equation of the system but can induce chaotic pi...

The aim of this paper is to investigate the control of the space tug and debris for the removal and detumbling of the space debris or defunct satellites using electrostatic forces. The goal is to provide a stable relative motion of the tug and the debris, both in terms of translation and rotation. With the spacecraft and debris nominally
charged wi...

This paper is devoted to the problem of a small payload delivery from an orbit to the Earth by a reusable space tether system consisting of a satellite in circular orbit, a tether, and a bottom module. The payload is placed in a dynamically symmetrical bead capsule, which can slide along the tether. Three scenarios for the payload delivery are prop...

The paper focuses on the dynamics of a rendezvous of a chaser and a large space debris connected by a viscoelastic tether. It is assumed that constant thrust acts on the chaser and a control is realized by changing the length of the tether. The goal is to find the control law that provides a soft docking of two bodies on an orbit. Also, we consider...

The paper is devoted to the issue of active large space debris removal. The contactless method of influencing space debris through the ion flow is considered. The main advantage of this method is absence of a dangerous and complex stage of space debris capturing or docking. In this study, the project "Ion Beam Shepherd" was taken as a basis. The ai...

The problem of delivering a payload from orbit without the consumption of jet fuel is considered. To solve this problem, it is proposed to use a reusable space transport system that consists of a satellite in a circular orbit, a weightless tether, a capsule with a payload, and a lower module. The purpose of the paper is to develop a mathematical mo...

One of the most promising methods of geosynchronous debris reorbiting is touchless actuation using electrostatic force. This paper investigates the dynamics and stability of two charged spacecraft formation when both spacecraft are charged with the same sign so that the active spacecraft (space tug) pushes the passive spacecraft (debris object) to...

Статья посвящена проблеме уборки космического мусора. Рассматривается бесконтактный метод воздействия. Предполагается, что оснащенный ионными двигателями активный космический аппарат-уборщик создает поток ионов, который обдувает мусор и таким образом замедляет его движение. Целью работы является разработка математической модели и исследование с ее...

This chapter contains several separate issues of space flight mechanics, which are of great practical interest but were not included in previous chapters. However, the author believes that it is advantageous to add the material into the book. The problem of the gravitational stabilization of the satellite by a controlled motion of a point mass on b...

This chapter is devoted to a tether-assisted reentry capsule return mission. The mathematical model of the space tethered system is given. Simplified equations are obtained for the case of the deployed tether. Analytic solutions for satellite motion around its center of mass under the influence of the gravitational moment and tether tension force a...

Returning from orbit to a surface of a planet is one of the most difficult and important problems of modern astronautics. This chapter explores uncontrolled descent of the reentry capsule into an atmosphere. We discuss the aerodynamic features of reentry capsules of various shapes. Equations of motion in the atmosphere for the axisymmetric and asym...

In this chapter, we study a problem of removal of large space debris by a tether tow. A space transportation system is composed of two bodies connected by the tether. The first body is space debris (upper rocket stage or a large nonfunctional satellite) and the second body is a space tug. An attitude motion of the system in general and space debris...

In this chapter, we study an attitude motion of free dual-spin satellite gyrostats that consists of a platform with a triaxial ellipsoid of inertia and the rotor with a small asymmetry with respect to the axis of rotation. The system with perturbations caused by a small asymmetry of the rotor and the time-varying moments of inertia of the rotor is...

This chapter presents the basics of mathematics and mechanics used in the book. In the first section, the elliptic integrals and elliptical functions are considered. In mechanics, these mathematical objects describe nonlinear oscillations, unlike the trigonometric functions, which describe linear oscillations. In the second section, rigid body kine...

The article deals with the transportation operation of a payload delivery from a circular orbit using a space-tethered system. The use of the tether allows transferring the payload capsule to the reentry orbit without using the jet fuel. The whole transport operation can be divided into three stages: braking for the payload exit from the original o...

This paper focuses on the attitude dynamics of a defunct axisymmetric satellite under the action of Coulomb forces to enable active space debris removal. Touchless Coulomb interaction occurs between an active spacecraft and the passive satellite at a fixed separation distance. The recently developed multi-sphere method of Schaub and Stevenson allow...

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 deb...

The plane motion in a circular orbit of a tethered system consisting of a space tug and a nonoperational spacecraft with propellant outage is considered, and the system motion with respect to its center of mass under the action of the gravitational torque and a constant driving force of the space tug is studied. Lagrangian formalism is used to cons...

A new technique of docking of a space tug with spent non-cooperative orbital stage by using a deployable elastic probe is proposed. The developed mathematical models demonstrate the proposed method and cover primary stages of the relative motion of the space tug and debris, including docking stage and the probe retraction stage. The simulation resu...

Among proposed applications of tethers in space, tether-assisted payload deorbiting projects are closest to the wide practical implementation. Three experiments were carried out successfully to date. The idea is to avoid the use of jet engines to generate a brake pulse, which transfers the payload on the descent orbit. The necessary reduction in ve...

The problem of a tether-assisted payload return from an elliptical orbit is considered in this study. In contrast to the existing works devoted to this issue, the article deals with a tether length control that provides a transfer of the payload into a descent trajectory from the tether rotation mode. Application of the swing principle for the teth...

Chaotic motion of the tethered towing of debris using a low-thrust tug is considered. Stable and unstable stationary solutions are presented for the in-plane motion of the system in a circular orbit, which depend on the value of the tug's thrust. The unstable solutions give rise to the chaotic motion of the system in the presence of additional dist...

The dynamics of the rigid body connected with the space tug by the elastic rope in a gravitationless space is considered. The equations of motion are derived from a Lagrange formalism. The influence of initial conditions on the rigid body behaviour is studied. The posibility of existence of critical behaviour of movement which can cause the entangl...

During the past few decades, space tether systems have
attracted the attention of researchers from around the world.
The range of problems, and where they fi nd application, is
extremely wide. Various transport operations, electricity
generation, exploration of deep space, and many other tasks
can be resolved with the help of space tether systems....

To my parents, and wife Lyudmila. Preface Soviet sputnik ushered in the space era in October, 1957. This launch occurred almost 70 years ago and nonetheless interest in the creation and use of space technics continues unabated. New challenges formulate new ideas, which be implemented in the new space programs. Currently, global unexpected, includin...

Rigid Body Dynamics for Space Applications explores the modern problems of spaceflight mechanics, such as attitude dynamics of re-entry and space debris in Earth's atmosphere; dynamics and control of coaxial satellite gyrostats; deployment, dynamics, and control of a tether-assisted return mission of a re-entry capsule; and removal of large space d...

Presentation for the engineering notes V. V. Yudintsev, V. S. Aslanov Detumbling Space Debris Using Modified Yo-Yo Mechanism. Journal of Guidance, Control, and Dynamics, Vol. 40, No. 3 (2017), pp. 714-721. http://dx.doi.org/10.2514/1.G000686

This paper focuses on a docking of two bodies by means of a tether in a force-free field which is studied in the framework of space debris removal problem. The two bodies are connected by the viscoelastic tether. One of the bodies (tug) is under constant thrust. In the initial time the bodies are at some distance from each other. Analysis of the te...

The problem of a payload delivery from an elliptical orbit to Earth surface by a space tethered system is considered. This operation includes three stages: tethered motion, orbital flight of the payload to the border of the atmosphere, and its descent into the atmosphere. The third stage is critical for the whole mission, because the payload can be...

The chaotic motion of the tethered tug-debris system with the low thrust tug is considered in the context of active debris removal (ADR) missions. Stable and unstable stationary solutions are presented for the in-plane motion of the system in a circular orbit, which depend on the tug's thrust and orbital angular rate. The unstable solutions give ri...

The chaotic motion of the tethered tug-debris system with the low thrust tug is considered in the context of active debris removal (ADR) missions.Stable and unstable stationary solutions are presented for the in-plane motion of the system in a circular orbit, which depend on the tug’s thrust and orbital angular rate.The unstable solutions give rise...

Conical-shaped reentry capsules with a spherical bottom and a displaced center of mass from the axis of symmetry are widely used in astronautics for payload delivery. In the case of control-system breakage, modern reentry capsules allow a successful landing to be carried out in an uncontrolled mode. At the same time, the aerodynamic features of thi...

Dynamics and control of a tether-assisted return mission of a re-entry capsule are considered. Efficiency of the braking process of the capsule depends on a deflection angle of the tether from a local vertical before separating the capsule from the tether. The aim is of this paper to find a tether length control law that allows to increase the defl...

The field of space tethers has received very much attention in recent decades. The central advantage of using
tethers in many of these applications is that very little fuel needs to be consumed. The tethered systems offer
numerous ways of beneficial implementation on modern spacecrafts and allow to perform multiple tasks including
such as payload d...

Transport operations in space using tether systems is a most promising technology currently developed in the world. A towing of nonfunctional satellites and orbital stages to the boundary of the atmosphere using tethered space tug relate to such operations. The paper deals with the motion of a tether system, which includes three elements: a passive...

We study the pitch motion dynamics of a rigid body in a resistant medium under the influence of a biharmonic torque . Such nutation angle dependence of the biharmonic aerodynamic torque is typical for uncontrolled re-entry vehicles of segmentally conical, blunted conical, and other shapes (Soyuz, Mars, Apollo, Viking, Galileo Probe, Dragon). The pr...

Active debris removal using a space tug with a tether is one of the promising techniques to decrease the population of large non-functional satellites and orbital stages in near Earth orbits. Properties of debris should be taken into account in the development of the space tugs. In this paper we consider the motion of a debris objects with fuel res...

The attitude motion is studied of asymmetric dual-spin gyrostats which may be modeled as free systems of two rigid bodies, one asymmetric and one axisymmetric. Exact analytical solutions of the attitude motion are presented for all possible ratios of inertia moments of these bodies. The dynamics of free gyrostats with zero internal torque is consid...

Active debris removal is one of the promising techniques that will decrease the population of large, non-functional spacecraft (space debris) on orbit. Properties of space debris should be taken into account during planning an active debris removal mission. In this paper the thrusting phase of tethered deorbit of large space debris with flexible ap...

Active exploration of the space leads to growth of a near-Earth space pollution. The frequency of the registered collisions of space debris with functional satellites highly increased during last 10 years. As a rule a large space debris can be observed from the Earth and catalogued, then it is possible to avoid collision with the active spacecraft....

The problem of deorbiting large space debris (SLD) by means of a tethered space tug is considered. A mathematical model that describes the plane motion of the system is developed. The model takes into account the effects of the atmosphere and the rotary motion of the SLD around the SLD center of mass. The effects of the moment of tension force, gra...

The motion of a free gyrostat consisting of a platform with a triaxial ellipsoid of inertia and a rotor with a slight asymmetry with respect to the axis of rotation is considered. Dimensionless equations of motion for a system with perturbations caused by the small asymmetries of the rotor are written in Andoyer-Deprit variables. These perturbation...

In this note we show by producing counterexamples that main results which appeared in the articles by Doroshin (International Journal of Non-Linear Mechanics 50, 2013) are not new solutions.