Abstract The dynamic interaction of a “magnetized” sphere (a sphere with a magnetic field source) with a hypersonic rarefied plasma flow was studied experimentally to model the interaction of a “magnetized” spacecraft with the ionospheric plasma. The experiments were conducted at the plasma flow velocity parallel and normal to the sphere's magnetic field. The electromagnetic drag coefficient was determined as a function of the ratio of the magnetic pressure to the dynamic pressure and the ratio of the mini-magnetosphere dimension to the spacecraft dimension (sphere radius). It was shown that a spacecraft's magnetic field of about 0.8–1.5 T produces an electromagnetic drag comparable with the drag produced using ion beam technologies of space debris removal, which require dedicated spacecraft with plasma accelerators. Energy-efficient compact sources of a 0.8–1.5 Т magnetic field for space debris objects may be made using special arrangements of small-size permanent magnets – Halbach arrays.
Highlights Conditions for physical modelling of spacecraft–ionosphere interaction are given. Drag on “magnetized” spacecraft vs. magnetic/dynamic pressure ratio is determined. An onboard magnetic field of 0.8 … 1.5 T may be produced using Halbach arrays.
Drag on a spacecraft produced by the interaction of its magnetic field with the Earth's ionosphere. Physical modelling
Acta Astronautica ; 166 ; 41-51
2019-10-07
11 pages
Article (Journal)
Electronic Resource
English
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