An overview of the conceptual design of manned engineering satellites is presented. The mission scenarios for developing manned engineering satellites involve: (1) selecting mission equipment to enable preferential development and validation of mandatory technologies among those for Environmental Control and Life Support System (ECLSS); (2) selecting mission equipment to enable development and validation of independent domestic technologies as well as utilizing to the utmost the manned space technology acquired through the Japanese Experimental Module (JEM); and (3) installing the most effective mission on the basis of relationships with Extravehicular Activity (EVA), robot, and retrieval-type spacecraft technologies, and trends of overseas manned space technology. The results of reviews on the system and subsystems, such as attitude and orbit control, structure, thermal control, electric power, communication, and data processing subsystems are outlined. The results of reviews on the structure, weight, and reentry phase operation are presented.
Yuujin Gijutsu Shiken Eisei (Manned Engineering Test Satellites)
1992
22 pages
Report
No indication
English
Manned Spacecraft , Astronautics , Manned spacecraft , Reusable spacecraft , Satellite design , Japanese spacecraft , Spacecraft equipment , Spacecraft instruments , Spacecraft modules , Spacecraft structures , Closed ecological systems , Data systems , Rocket engines , Satellite configurations , Satellite control , Spacecraft power supplies , Spacecraft reentry , Structural design , Telecommunication , Temperature control , Weight (Mass) , Foreign technology