ADCS OBC with magnetorquer control, IMU and sensor PCDU
ǀ FLIGHT HERITAGE: YES ǀ EM PRICE: €8,500 ǀ FM PRICE: €10,000 ǀ
The ADCS-P3 is an interface and control computer for the attitude determination and control systems for advanced nano and microsatellite missions using a distributed sensor and actuator architecture. The ADCS-P3 is designed to operate with external attitude sensors connected via CAN bus or UART such as sun sensors, star trackers, GPS and others and using external actuators for control. However an IMU with 6 degrees of freedom and 3 axis magnetometer are integrated in the unit. The ADCS-P3 includes power distribution with latch-up protected outputs for externally connected 12 devices and 3 external magnetorquers.
The ACDS software running on the internal Cortex processor is based around an extended Kalman filter allowing a number sensors with varying performance to contribute to the attitude determination and control precision. The system is capable of several different pointing modes such as nadir, sun tracking, ground spot tracking and inertial pointing. In addition, the controller is able to track two prioritized targets simultaneously given that the primary target has at least one free axis. In this case, the free axis can be used to e.g. optimize the direction of solar panels towards the sun while pointing an antenna, camera or other payload towards a ground target.
Integral to the control system architecture is a built-in simulator which is capable of complete ADCS simulation with and without sensors and actuators in the loop. The simulator can run both on the ADCS hardware itself, but it can also be run on a linux-based PC at simulations speeds up to 10,000 times real-time. The simulator is extremely useful both to design ADCS objectives but also to verify the integrated system integrity.
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