Study on Non-Contact Space Debris Deorbit Technology and System by Using Irradiation and Reaction of Electric Thruster Exhaust Flows and Development of the Osaka Institute of Technology 4th PROITERES Nano-Satellite for Its Practical Experiment in Space
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The Osaka Institute of Technology (OIT) 4th PROITERES satellite, as shown in Fig.1, is planned as a nano-satellite in order to achieve a main mission in which space debris makes deorbit by electric propulsion. The principle of deorbiting space debris is exposure of thruster plume to space debris by an electric thruster; that is, reaction impulse is given to debris, and after that debris decreases velocity and deorbits. Accordingly, the 4th PROITERES can deorbit space debris with safety without contacting with space debris and the satellite. Our university is developing four kinds of electric propulsion. These electric thrusters are investigated, and for the 4th PROITERES satellite for deorbiting space debris a suitable electric thruster will be selected. Reaction impulse bit of a pulsed plasma thruster (PPT) is measured on a downstream plate by pendulum method. As a result, a reaction impulse bit is average 1.718mNs. Because a previously directly measured thruster impulse bit of the PPT was about 2.2mNs, a reaction impulse bit is about 30% decrease. Now, the 4th PROITERES satellite is developing for launching in 2020.
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Physical characteristics: Original contains color illustrations
Study on Non-Contact Space Debris Deorbit Technology and System by Using Irradiation and Reaction of Electric Thruster Exhaust Flows and Development of the Osaka Institute of Technology 4th PROITERES Nano-Satellite for Its Practical Experiment in Space
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