LEO Debris Environment Modeling in Japan
- Paper number
IAC-06-B6.2.06
- Author
Mr. Tomohiro Narumi, Kyushu University, Japan
- Coauthor
Prof. Toshiya Hanada, Kyushu University, Japan
- Coauthor
Ms. Satomi Kawamoto, Japan Aerospace Exploration Agency (ISTA/JAXA), Japan
- Coauthor
Dr. Seishiro Kibe, Thailand
- Year
2006
- Abstract
Study and long term prediction of orbital debris environment are urgent needs for secure human space development and exploration. This paper introduces the current status of an orbital debris evolutionary model for low Earth orbit (LEO), named LEODEEM and being developed under collaboration of Japan Aerospace Exploration Agency. The objective of LEO modeling is to discuss on effective mitigation measures to conserve orbital environment. In the model an object with a perigee altitude less than 2,000 km is considered as a LEO object. The model calculates long-term evolution of artificial objects greater than 1 cm in LEO with future space operations, including collisions and explosions. LEO modeling is on going based on the following techniques: 1) adopting a high-speed analytic orbit integrator, taking into account the zonal harmonics of the Earth’s gravity, atmospheric drag, third body perturbations, and solar radiation pressure, 2) small objects such as breakup fragments and mission related objects are binned by dimensions of perigee and apogee radii, inclination, and ballistic coefficient, while intact objects are tracked individually, 3) collision probability is estimated based on an error sphere around an object. Currently, the model is being tuned up based on the modeling baseline provided by the Inter-Agency Space Debris Coordination Committee, containing a population snapshot on January 1, 2002, and breakup and insertion history from 1994 through 2001. The details of the model and results will be presented in this paper.
- Abstract document
- Manuscript document
IAC-06-B6.2.06.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.