Development of Engineering Test Satellite type III (ETS-III)
Abstract
Mission goals and design features of the Japanese ETS-III spacecraft are described. The ETS-III is intended for verifying the on-orbit performance of three-axis stabilization functions, solar paddle deployment, and orientation and thermal control systems. Payload equipment to be tested includes a vidicon, an ion drive motor, heat pipe and louver thermal control mechanisms, and a magnetic attitude control system. The ETS-III will travel a 1000 km orbit with 45 deg inclination, with a mission life of one year. An attempt has been made to automate most spacecraft functions using high reliability components. The component reliability and performance verification testing procedures are outlined.
- Publication:
-
13th Symposium on Space Technology and Science
- Pub Date:
- 1982
- Bibcode:
- 1982spte.symp.1131T
- Keywords:
-
- Japanese Space Program;
- Payloads;
- Satellite Attitude Control;
- Satellite Design;
- Scientific Satellites;
- Three Axis Stabilization;
- Block Diagrams;
- Heat Pipes;
- Ion Engines;
- Louvers;
- Temperature Control;
- Thermal Vacuum Tests;
- Vidicons;
- Launch Vehicles and Space Vehicles