Copyright © 2018 by the International Astronautical Federation (IAF). All rights reserved. Expansion of space utilization activities increases the number of large debris like an upper stage of the launch vehicle in congested orbit at altitude of 700-1000 km. These debris collide with others producing a lot of smaller debris that would cause further collisions to spacecrafts and their destruction in orbit. For these reasons, some low-cost debris removal systems are proposed, and a part of fundamental technologies was already demonstrated by space agencies in space. The atmosphere at the altitude of 700-1000 km is composed of neutral particles of He, H, O and ions of O+, H+. One of the conventional deorbit system uses a deployable sail capturing the neutral particles to produce a drag force. The drag force decreases orbital velocity of a spacecraft and then the spacecraft will move to the lower orbit to the earth. This type of deorbit system is very simple, but a large-scale structure is needed to produce enough drag force. In this research, we focus on the ion particles existing in the atmosphere at high altitude to enhance the drag force for the removal system. The concept of deorbit system utilize an ion sheath generated by a charged deployable thin film. In this paper, as a preliminary study, we describe the fundamentals of the debris removal system using the charged sail, changes of the atmospheric environment in LEO, the analysis by 3-dimensional full particle electrostatic code developed by this research group, and the calculation of experimental environment parameters by scaling for ground experiments.