Space Debris Removal System using a Small Satellite
- Paper number
IAC-06-B6.4.02
- Author
Dr. Shin-ichiro Nishida, Japan Aerospace Exploration Agency (ISTA/JAXA), Japan
- Coauthor
Ms. Satomi Kawamoto, Japan Aerospace Exploration Agency (ISTA/JAXA), Japan
- Coauthor
Dr. Yasushi Okawa, Japan Aerospace Exploration Agency (ISTA/JAXA), Japan
- Coauthor
Dr. Fuyuto Terui, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Shoji Kitamura, Japan Aerospace Exploration Agency (JAXA), Japan
- Year
2006
- Abstract
Since the number of satellites in Earth orbit is steadily increasing, space debris could eventually pose a serious problem to near-Earth space activities, and therefore effective measures to mitigate it are important. End-of-life de-orbiting and orbital lifetime reduction capability of each satellite could be an effective means for reducing the number of debris by lowering the probability of the collisions between objects. On the other hand, the active removal of space debris and the retrieval of failed satellites by spacecraft are considered to be other measures. The Institute of Aerospace Technology, Japan Aerospace Exploration Agency (JAXA), is investigating an active space debris removal system using a small satellite and the applicability of electro-dynamic tether (EDT) technology as its high efficient orbital transfer system. By launching a small low cost remover satellite by piggyback, whenever it launches a new LEO satellite, and removing a debris on its near orbit aims at reducing the debris steadily. A small expendable EDT package is under development that consists of a bare conductive tether and field emitter array cathodes (FEAC) that utilize carbon-nano-tube. The bare tether will collect electrons from ambient plasma and the FEAC will emit electrons. Thus, this package presents a possible technique for lowering the orbit of a debris removal system without the need for propellant. A flight demonstration using an upper stage of a rocket or a small satellite is planned to establish the EDT technology and the folder arm technology. Capturing is an indispensable and important task for the retrieval of large space debris. It is common for many large debris objects to tumble, since angular momentum may have remained in the attitude control systems when failure occurred. On-orbit experiments of capturing satellite have been conducted successfully on ETS-VII in 1999 for the case where the target possesses visual markers and handles to facilitate grasping. However, space debris does not generally possess such convenient features they non-cooperative. In this case, since the conditions for capture are not favorable, tracking errors will lead to loading, and momentum transfer will occur during the capture process. Therefore, load relief is an important problem on folding a space debris. Development of a new folder arm hardware and its control system is furthered in consideration of this point. First, details of a system concept and mission scenario of space debris remover using a small satellite for piggyback launch are described in this paper. Results of feasibility studies of this system are described. Next, a demonstration plan using small satellites to establish and demonstrate the EDT and the folder arm technology is described. Then, the status of prototypes of bare tether, a reel mechanism, a deploying mechanism and the FEAC and their testing are described. Finally, this paper deals with a prototype folder arm and its control method, vision sensor for capturing a tumbling non-cooperative target satellite.
- Abstract document
- Manuscript document
IAC-06-B6.4.02.pdf (🔒 authorized access only).
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