Low-cost Small Satellite System for Electro-Dynamic Tether Demonstration Mission

Paper number

IAC-09.B4.4.12

Author

Mr. Yoshihiro Tsuruda, Kyushu University, Japan

Coauthor

Mr. Michael Shoemaker, Kyushu University, Japan

Coauthor

Prof. Tetsuo Yasaka, Kyushu University, Japan

Coauthor

Prof. Jozef van der Ha, Kyushu University, Japan

Coauthor

Prof. Toshiya Hanada, Kyushu University, Japan

Coauthor

Mr. Shunsuke Onishi, Kyushu University, Japan

Year

2009

Abstract

The space debris problem is unavoidable for the future space age.  As a recent example, the collision of IRIDIUM33 and COSMOS2251 on 10th February 2009 had a significant impact on the orbital debris environment.  One method of avoiding such satellite collisions is the de-orbiting of non-functional satellites by using Active Debris Removal (ADR) techniques.  The Electro-Dynamic Tether (EDT) system is being developed by JAXA (Japan Aerospace eXploration Agency) as one of the ADR applications.  The EDT system can produce thrust for de-orbiting by using the Lorentz force induced by the conductive tether as it crosses the geomagnetic field.  This system requires a small amount of electric power and propellant compared to other methods, thus, it provides a useful de-orbiting function as an embedded unit for future satellites.  An autonomous rendezvous and docking spacecraft to attach a standalone EDT system to existing debris may be a future application.  However, on-orbit validation of the tether deployment system and the electron emitting device is required.  
In this context, Kyushu University has started the design of a small satellite for an EDT demonstration mission.  So far, we have designed two small satellites from 2003, QTEX (Kyushu University Tether Satellite Experiments) and QSAT (Kyushu Satellite) for a polar plasma observation mission.  Through these two projects, we have studied the low-cost 50-kg class small satellite system and established a general-purpose satellite based on the original unit concept and the distributed processing concept by using the CAN (Controller Area Network) bus.  We called this general-purpose satellite system USAT (Universal SATellite).  The USAT system satisfies the piggy-back conditions of the Japanese H-IIA launcher, essentially all of the subsystem components consist of COTS (Commercial-Off-The-Shelf) units.  These key features allow the low-cost development and the on-orbit demonstration.  
In this paper, we introduce the system characteristics of USAT for the EDT demonstration mission and explain the benefits of overall system design.

Abstract document

IAC-09.B4.4.12.pdf

Manuscript document

IAC-09.B4.4.12.pdf (🔒 authorized access only).

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