Development status of active space debris removal system
- Paper number
IAC-05-B6.3.03
- 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
Mr. Shoichi Yoshimura, Japan Aerospace Exploration Agency (IAT/JAXA), Japan
- Coauthor
Dr. Fuyuto Terui, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Atsushi Nakajima, Japan Aerospace Exploration Agency (IAT/JAXA), Japan
- Coauthor
Dr. Shoji Kitamura, Japan Aerospace Exploration Agency (JAXA), Japan
- Year
2005
- 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 Space Technology and Aeronautics, Japan Aerospace Exploration Agency (JAXA), is investigating an active space debris removal system and the applicability of electro-dynamic tether (EDT) technology as its high efficient orbital transfer system. 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 planed to establish the EDT 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. Load relief is an important problem. In the satellite capture experiment of the ETS-VII, load relief during capture was performed by means of compliance control using a 6-axis force/torque sensor installed in the wrist of the robot arm. However, in such a system, the flexible segment of the arm lying between the sensor and actuators does not allow the control bandwidth of the arm force control system to be set high enough to enable capture of a non-co-operative target. A system which gives active compliance is in each joint as the relief method of the load at the time of capture. First, details of a scenario of space debris capturing/removal sequence are described in this paper. Results of feasibility studies of this system are described. Next, a test flight experiment using an upper stage of a rocket or a small satellite is planed to establish and demonstrate the EDT technology. 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 space robot arm and its new control method for capturing a tumbling non-cooperative target satellite.
- Abstract document
- Manuscript document
IAC-05-B6.3.03.pdf (🔒 authorized access only).
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