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Mission Background

In recent years, the risk of space debris causing pollution in space and disrupting space activities has increased. Active Debris Removal (ADR) initiatives are being promoted as a countermeasure. To perform ADR, it is necessary to estimate the attitude and shape of debris beforehand. Light curve dynamics estimation (light curve inversion) has been proposed for this purpose. Light curve inversion is a technique for estimating the attitude and motion of an object and its shape by observing the variation of sunlight reflected by the object. It has also been used to estimate the shape of asteroid Itokawa before the Hayabusa spacecraft's approach. However, there is no actual demonstration combining the actual attitude of debris and light curve. Therefore, it is necessary to demonstrate the light curve inversion in orbit for "space environment conservation" and "safe and secure space activities" to improve space environment protection.

Mission Objective

Main Objective

Demonstration of dynamic estimation by optical observation combining attitude observation data and light curve in orbit


  • Space demonstration of machined integrated structures that can be mass-produced with stable quality
  • In-orbit demonstration of a membrane separation-type separation device
  • Detection and timing of collisions with small debris
  • Investigation of the effect of atmospheric drag on the attitude of high surface mass ratio objects
  • Strengthening collaboration between universities and local industries in Kyushu

System Overview

600 km sun-synchronous orbit
3U CubeSat (300 x 100 x 100 mm) as the main structure
A 1.5 m sail is deployed in orbit
Attitude is estimated from magnetic and gyro sensors and the amount of power generated by solar cells.