The JAXA has been evaluating the risk of the micro-debris from the ADEOS-II (Midori-II) satellite anomalies. The results showed the damage on the wire harness and other equipment even when the impact of the micro-debris was due to particles in the range of 100un to several millimeters. It is difficult to obtain data on the environment space in required to evaluate the frequency of impact on a satellite by micro-debris, and currently, ware unable to get real-time data. Under these circumstances, it is urgent that environmental data be measured to understand the effect of impact by micro-debris on the safe operation of a satellite and the accurate evaluation of these frequency of impacts. In this paper, we describe the issues related to the impact on a satellite by micro-debris and the technology for measuring micro-debris

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he Aerospace Research and Development Directorate (ARD) of the Japan Aerospace Exploration Agency (JAXA) has been comprehensively studying the space debris problem, focusing on observation, modeling, protection and mitigation. ARD/JAXA has created a space debris optical observation facility to research and develop observation technologies in the Nyukasa highlands in Nagano prefecture, at an altitude of 1,870 m. The facility has two domes, in which a 35-cm Newtonian optical telescope and a 25-cm Baker Ritchey-Chretien optical telescope arc installed. One of our most important tasks is to develop automatic GEO debris detection software. Ordinarily, a faint object requires a long exposure time to accumulate a weak light signal until a detectable level is reached. However, a short exposure is necessary for GEO debris detection, or star streaks may obscure debris tracks. We have proposed a stacking method that superimposes multiple images to enable the detection of faint GEO debris signals. In this paper, we introduce JAXA’s observatory and some results from the software under development.

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Orbital debris modeling at Kyushu University was initiated with satellite impact testing, aiming to investigate low-velocity impact phenomena possible in the geosynchronous Earth orbit. Testing results were incorporated in an orbital debris evolutionary model for the geosynchronous Earth orbit region, named GEODEEM. Kyushu University also has developed an orbital debris evolutionary model for the low Earth orbit, named LEODEEM. The orbital debris evolutionary models are an essential tool to predict the future orbital debris environment and to discuss on what and how to do for orbital debris mitigation. This paper will briefly introduce orbital debris modeling being conducted at Kyushu University.

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The active removal of existing space debris is the one of the most proactive strategies available to suppress space debris growth. The Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency, is investigating an active space debris removal system that employs highly efficient electrodynamic tether (EDT) technology as its orbital transfer system. As the first step toward the realization of this debris removal system, an EDT flight experiment using a small satellite is planned to establish and demonstrate EDT technology, and to measure EDT characteristics such as electron emission and collection in the space plasma. In this paper, the results of precise numerical simulations for mission analysis arc presented, including available electric currents, orbital changes, tether stability and deployment dynamics, considering small satellite characteristics.

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