Session
Session 1: Advanced Concepts I
Abstract
This paper presents the ongoing feasibility study and bus system for microsatellite “Hibari”. The main technical missions for Hibari is called “Variable Shape Attitude Control (VSAC)”. This VSAC is based on an idea to utilize a reaction torque when a part of the satellite structure, for example, solar array paddles is appropriately rotated by actuators. The previous research concluded that VSAC successfully achieved the rapid maneuvering while maintain the high attitude stability against disturbances [1], and thus, it can be applied to a variety of advanced attitude control missions. Hibari project also aims at its application to astronomical mission requiring high pointing stability and agile maneuvering. This paper is mainly comprised of 3 parts: detail mission statement, ongoing feasibility studies and bus system configuration. First, we mention the mission requirement and detail mission sequence for both technical and science missions. Second, we show the ongoing feasibility studies to confirm that all mission requirement is satisfied by VSAC. Third, this paper describes each subsystem configuration to meet the system requirement stated in the mission’s section. And then, we wrap up in the conclusion section and stated the future study for advanced VSAC use in the end.
Variable Shape Attitude Control Demonstration with Microsat "Hibari"
This paper presents the ongoing feasibility study and bus system for microsatellite “Hibari”. The main technical missions for Hibari is called “Variable Shape Attitude Control (VSAC)”. This VSAC is based on an idea to utilize a reaction torque when a part of the satellite structure, for example, solar array paddles is appropriately rotated by actuators. The previous research concluded that VSAC successfully achieved the rapid maneuvering while maintain the high attitude stability against disturbances [1], and thus, it can be applied to a variety of advanced attitude control missions. Hibari project also aims at its application to astronomical mission requiring high pointing stability and agile maneuvering. This paper is mainly comprised of 3 parts: detail mission statement, ongoing feasibility studies and bus system configuration. First, we mention the mission requirement and detail mission sequence for both technical and science missions. Second, we show the ongoing feasibility studies to confirm that all mission requirement is satisfied by VSAC. Third, this paper describes each subsystem configuration to meet the system requirement stated in the mission’s section. And then, we wrap up in the conclusion section and stated the future study for advanced VSAC use in the end.
