| タイトル | Solar Anomalous and Magnetospheric Particle Explorer attitude control electronics box design and performance |
| 著者（英） | Fox, S. M.; Chamberlin, K.; Clagett, C.; Frederick, M.; Gruner, T.; Schnurr, R.; Correll, T.; Shiflett, L.; Quinn, T.; Wennersten, M. |
| 著者所属（英） | NASA Goddard Space Flight Center |
| 発行日 | 1993-01-01
1993 |
| 言語 | eng |
| 内容記述 | The attitude Control Electronics (ACE) Box is the center of the Attitude Control Subsystem (ACS) for the Solar Anomalous and Magnetospheric Particle Explorer (SAMPEX) satellite. This unit is the single point interface for all of the Attitude Control Subsystem (ACS) related sensors and actuators. Commands and telemetry between the SAMPEX flight computer and the ACE Box are routed via a MIL-STD-1773 bus interface, through the use of an 80C85 processor. The ACE Box consists of the flowing electronic elements: power supply, momentum wheel driver, electromagnet driver, coarse sun sensor interface, digital sun sensor interface, magnetometer interface, and satellite computer interface. In addition, the ACE Box also contains an independent Safehold electronics package capable of keeping the satellite pitch axis pointing towards the sun. The ACE Box has dimensions of 24 x 31 x 8 cm, a mass of 4.3 kg, and an average power consumption of 10.5 W. This set of electronics was completely designed, developed, integrated, and tested by personnel at NASA GSFC. SAMPEX was launched on July 3, 1992, and the initial attitude acquisition was successfully accomplished via the analog Safehold electronics in the ACE Box. This acquisition scenario removed the excess body rates via magnetic control and precessed the satellite pitch axis to within 10 deg of the sun line. The performance of the SAMPEX ACS in general and the ACE Box in particular has been quite satisfactory. |
| NASA分類 | SPACECRAFT INSTRUMENTATION |
| レポートNO | 95A80410 |
| 権利 | Copyright |
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