| Budget Amount *help |
¥3,600,000 (Direct Cost: ¥3,600,000)
Fiscal Year 2006: ¥900,000 (Direct Cost: ¥900,000)
Fiscal Year 2005: ¥2,700,000 (Direct Cost: ¥2,700,000)
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| Research Abstract |
First, this research examined the attitude and orbital dynamics of spinning solar sail spacecraft on earth-and interplanetary-orbit, which is investigated for future deep space exploration in Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (ISAS/JAXA). Numerical simulations estimated the influence of its spinning rate and an uncertain offset between its center-of-mass (cm) and center-of pressure (cp) on the attitude variation.
Then, considering an amount of the calculated influence, this research designed and assembled a ground experimental system for validation of an attitude control system for a spinning solar sail. The experimental system simulates a solar radiation pressure (SRP) force using earth gravity force; originally, air flow were supposed to be employed as modeling for SRP, but it was turned out that flow disturbance and vortex easily generates disturbance force and torque for the system. Besides, small inertia force acting its payload mass due to counter effect of sail acceleration is also experimentally simulated through gravity force compensation using a counter balance system. Furthermore, the system can control its cm/cp offset by moving the payload mass placed at the tip of a two-axis gimbaled control boom.
The experimental system verified its fundamental performance as a ground-placed validation setup for a spinning solar sail system, in measuring induced torque and force in each axis for changing the cm/cp offset and spinning rate.
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