Teather-less Spacecraft Deorbit System Using Lorentz Force

Paper number

IAC-11,A6,4,8,x10509

Author

Mr. Niccolo Cymbalist, Concordia University, Canada

Year

2011

Abstract

Deorbiting procedures for spacecraft are an increasing priority in low Earth orbit. New techniques are
needed to ensure that satellites can be disposed of quickly and safely at the end of their lifecycle to
prevent accumulation of space debris and possible collision between orbiting objects. As satellites are
becoming more popular and inexpensive, there is a pressing need for innovative techniques and new
deorbiting mechanisms. This paper proposes a novel deorbiting technique using the resulting Lorentz
force generated by the interaction of a quickly moving charged spacecraft and the Earth's natural
magnetic field to deorbit a satellite. The proposed technique accomplishes this by purposely inducing a
charge to the spacecraft. The charging mechanism will be activated when the spacecraft has reached the
end of its useful life. Depending on whether the spacecraft is in a prograde or retrograde orbit, the
spacecraft will be charged positively, by discharging electron current using a cathode, or charging the
spacecraft negatively by discharging ion current. This concept will be effective in every orbit with a
significant radial Lorentz force component. It will be most effective in an equatorial orbit, with
effectiveness decreasing as the satellite orbit inclination increases. We will numerically simulate the
concept for various categories of orbits, including prograde and retrograde orbits of various inclinations
and at various altitudes. We will present estimates of the time required to deorbit a spacecraft of the
cubesat class in various orbits as well as assess the potential of applying this technique to larger
satellites. Additionally, we will outline the design of the system which will charge the spacecraft,
including an assessment of the added risks to the spacecraft. Finally, we will include a discussion of the
decay of the induced charge bias of the spacecraft due to spacecraft-plasma interactions.

Abstract document

IAC-11,A6,4,8,x10509.brief.pdf

Manuscript document

IAC-11,A6,4,8,x10509.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.