Demonstrating a new technology for space debris removal using a bi-directional plasma thruster

Kazunori Takahashi,Christine Charles,Rod W Boswell,Akira Ando

doi:10.1038/s41598-018-32697-4

Kazunori Takahashi, Christine Charles + Show 2 more

Open Access

https://doi.org/10.1038/s41598-018-32697-4

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Abstract

Space debris removal from Earth orbit by using a satellite is an emergent technological challenge for sustainable human activities in space. In order to de-orbit debris it is necessary to impart a force to decelerate it, resulting in its atmospheric re-entry. A satellite using an energetic plasma beam directed at the debris will need to eject plasma in the opposite direction in a controlled manner in order to maintain a constant distance between it and the debris during the deorbiting mission. By employing a magnetic nozzle plasma thruster having two open source exits, bi-directional plasma ejection can be achieved using a single electric propulsion device. Both the forces exerted on the thruster and the target plate simulating the debris are simultaneously measured in a laboratory space simulation chamber showing that a force decelerating the debris and a zero net force on the thruster can be successfully obtained. These two forces can be individually controlled by external electrical parameters, resulting in the ability to switch the acceleration and deceleration modes of the satellite and the debris removal mode using a single electric propulsion device.

Highlights

Space debris orbiting around the Earth has become a serious problem over the past few decades[1,2,3]; collisions with satellites cause damage to the spacecraft but can result in an increase in the amount of debris[4]
In the case of imparting a force to the debris by plasma ejection from a satellite using an electric propulsion device, such as the ion-beam shepherd (IBS) method, the satellite is simultaneously propelled in the opposite direction, making it difficult to maintain the distance between the debris and the satellite
Imparting momentum flux F1 to the debris will cause its deceleration, final re-entry into the Earth atmosphere and natural burn up. (b) The open exits magnetic nozzle rf plasma thruster forming the single electric propulsion device where control of the momentum flux imparted onto the debris is obtained via the control of the plasma momentum fluxes ejected at each open exit using variable external parameters

Summary

Introduction

Space debris orbiting around the Earth has become a serious problem over the past few decades[1,2,3]; collisions with satellites cause damage to the spacecraft but can result in an increase in the amount of debris[4]. Most of the contactless concepts (laser-ablation and IBS) have proposed imparting a force to the debris thereby decelerating them in a direction opposite to their velocity to transfer them to a lower altitude where they re-enter the Earth’s atmosphere and naturally burn up. The IBS proposal would require two ion-gridded thrusters on the satellite as shown, one of which imparts a force to the debris and another balances the thrust by ejecting plasma in the direction opposite to the debris. Imparting momentum flux F1 to the debris (horizontal arrow F1 pointing to the right) will cause its deceleration, final re-entry into the Earth atmosphere and natural burn up. Imparting momentum flux F1 to the debris (horizontal arrow F1 pointing to the right) will cause its deceleration, final re-entry into the Earth atmosphere and natural burn up. (b) The open exits magnetic nozzle rf plasma thruster forming the single electric propulsion device where control of the momentum flux imparted onto the debris is obtained via the control of the plasma momentum fluxes ejected at each open exit using variable external parameters (solenoids currents and propellant gas flow rates)

Methods

Results

Conclusion