An Introduction to Space Instrumentation,
Edited by K. Oyama and C. Z. Cheng, pp. 165-179.
© TERRAPUB, 2013.
Information Technology Center, Tokai University, Hiratsuka 259-1292, Japan
The Magnetic Field Measurement (MFM) sensor has been designed to measure the geomagnetic field deviation induced by the low latitude Sq current system. The magnetometer system used in this rocket experiment is a triaxial fluxgate magnetometer with ring-core sensors. It has a detectable geomagnetic field range of ±65,535 nT and has a high resolution of 0.2 nT/bit for each axial component. Magnetometer is also one of attitude determination sensors during the flight of rocket. And the Sun Aspect Sensor (SAS) using the CMOS linear image sensor is loading in this rocket experiment, simultaneously. It has a detectable angle range of ±60 degrees in the direction of elevation angle and has a high resolution of 0.5 degree/bit. In this paper, we deal with both instruments of MFM and SAS, and the method of rocket attitude determination using the data for NCKU SR-10 sounding rocket in the Taiwan-Japan Space joint experiment.
Key words: Sounding rocket SR-10, magnetic field measurement, Sq current, sun aspect sensor, attitude.