Review of Active Space Debris Removal Methods

Mark, C. Priyant; Kamath, Surekha

doi:10.1016/j.spacepol.2018.12.005

Cited by 183 publications

(59 citation statements)

References 47 publications

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“…where U V is the functional dependence of the velocity pulse gained over one enabling cycle on the phase of solar activity and source data; U N is the functional dependence of the number of times ERPS is enabled on the phase of solar activity and source data. (9) and (10) are solved numerically using the mathematical model, given in [12], accounting for the pulse change in velocity, in the apogee of the orbit after the battery is charged.…”

Section: Devising a Methodology For Determining The Parameters Of Thementioning

confidence: 99%

“…At present, the following de-orbiting methods are used and developed to reduce the clogged near-Earth space [6][7][8][9][10][11]:…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

“…Despite such a variety of methods for clearing the low orbits from debris, the most common of them for large-sized SOs, such as the launch vehicle orbital stages and spacecraft that have completed their mission, is the de-orbiting using the JPS [9][10][11]. This method makes it possible to remove SOs within a predefined time to the specified target orbits.…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

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Development of the combined method to de-orbit space objects using an electric rocket propulsion system

Golubek

Dron

Dubovik

et al. 2020

EEJET

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A method has been developed for the combined de-orbiting of large-size objects of space debris from low-Earth orbits using an electro-rocket propulsion system as an active de-orbiting means. A principal de-orbiting technique has been devised, which takes into consideration the patterns of using an electric rocket propulsion system in comparison with the sustainer rocket propulsion system. A procedure for determining the parameters of the de-orbiting scheme has been worked out, such as the minimum total speed and the time of the start of the de-orbiting process, which ensures its achievement. The proposed procedure takes into consideration the impact exerted on the process of the de-orbiting by the ballistic factor of the object, the height of the initial orbit, and the phase of solar activity at the time of the de-orbiting onset. The actual time constraints on battery discharge have been accounted for, as well as on battery charge duration, and active operation of the control system. The process of de-orbiting a large-size object of space debris has been simulated by using the combined method involving an electro-rocket propulsion system. The impact of the initial orbital altitude, ballistic coefficient, and the phase of solar activity on the energy costs of the de-orbiting process have been investigated. The dependences have been determined of the optimal values of a solar activity phase, in terms of energy costs, at the moment of the de-orbiting onset, and the total velocity, required to ensure the de-orbiting, on the altitude of the initial orbit and ballistic factor. These dependences are of practical interest in the tasks of designing the means of the combined de-orbiting involving an electric rocket propulsion system. The dependences of particular derivatives from the increment of a velocity pulse to the gain in the ballistic factor on the altitude of the initial orbit have been established. The use of these derivatives is also of practical interest to assess the effect of unfolding an aerodynamic sailing unit

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Section: Devising a Methodology For Determining The Parameters Of Thementioning

confidence: 99%

“…At present, the following de-orbiting methods are used and developed to reduce the clogged near-Earth space [6][7][8][9][10][11]:…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

Section: Literature Review and Problem Statementmentioning

confidence: 99%

See 1 more Smart Citation

Development of the combined method to de-orbit space objects using an electric rocket propulsion system

Golubek

Dron

Dubovik

et al. 2020

EEJET

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“…A coherent strategy, along with technological and platform developments, is needed for the de-orbiting, re-orbiting, or servicing satellites, in particular considering the advent of such constellations. The issue of the space debris and related mitigation strategies is receiving growing attention [10], [12], and a variety of concepts have been proposed, see for example [13] and [14]. In this context, RemoveDebris has been the first space mission to demonstrate technologies for the active removal of space debris.…”

Section: Introductionmentioning

confidence: 99%

The active space debris removal mission RemoveDebris. Part 2: In orbit operations

et al. 2020

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This is the second of two companion papers that describe the development of the RemoveDEBRIS space mission. This second article describes the in-orbit operations that were performed to demonstrate technologies to be used for the active removal of space debris, whereas the first paper described the development of the satellite's hardware. The RemoveDebris mission has been the world's first Active Debris Removal (ADR) mission to successfully demonstrate, in orbit, some cost effective technologies, including net and harpoon capture; and elements of the whole sequence of operations, like the visionbased navigation. The satellite was launched the 2 nd of April 2018, to the International Space Station (ISS) and from there, on the 20 th of June 2018, was deployed via the NanoRacks Kaber system into an orbit of 405 km altitude. During the mission, two 2U CubeSats have been released by the mothercraft platform as artificial debris targets, to demonstrate net capture and cameras to be used for vision based navigation. Harpoon capture has been demonstrated by deploying a target and then firing at it a harpoon tethered to the platform. The various phases of the missions have been monitored using relevant telemetry and video cameras, and this paper reports the results of the various demonstrations.

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“…With the development of space technology, space manipulators have played an important role in on-orbit service (OOS), such as on-orbit assembly, maintenance, docking, and space debris capture [ 1 , 2 , 3 ]. In general, the spacecraft capture mission can be divided into five phases: (a) orbital approach; (b) rendezvous; (c) robotic arm deployment; (d) pre-grasping; (e) grab operation [ 4 ].…”

Section: Introductionmentioning

confidence: 99%

PD-Impedance Combined Control Strategy for Capture Operations Using a 3-DOF Space Manipulator with a Compliant End-Effector

Kang

Zhang

et al. 2020

Sensors

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The contact force/torque between the end-effector of the space manipulator and the target spacecraft will reduce the efficiency and safety of the capture task. A capture strategy using PD-impedance combined control algorithm is proposed to achieve compliant contact between the chaser and target spacecraft. In order to absorb the impact energy, a spring-damper system is designed at the end-effector, and the corresponding dynamics model is established by Lagrange’s equation. Then a PD-impedance control algorithm based on steady-state force tracking error is proposed. Using this method, a compliant contact between the chaser and target spacecraft is realized while considering the dynamic coupling of the system. Finally, the general equation of the reference trajectory of the manipulator end-effector is derived according to the relative velocity and impact direction. The performance of the proposed capture strategy is studied by a co-simulation of MSC Adams and MATLAB Simulink in this paper. The results show that the contact plane at the end-effector of the manipulator can decelerate and detumble the target spacecraft. Besides, the contact force, relative velocity, and angular velocity all decrease to zero gradually, and the final stable state can be maintained for a prescribed time interval.

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Review of Active Space Debris Removal Methods

Cited by 183 publications

References 47 publications

Development of the combined method to de-orbit space objects using an electric rocket propulsion system

Development of the combined method to de-orbit space objects using an electric rocket propulsion system

The active space debris removal mission RemoveDebris. Part 2: In orbit operations

PD-Impedance Combined Control Strategy for Capture Operations Using a 3-DOF Space Manipulator with a Compliant End-Effector

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