Attitude Control Module PnP ADCS-N1
TY-Space Technology
A plug-and-play (PnP) satellite attitude determination and control module (ADCS-N1) integrating star trackers, sun sensor, gyroscope, magnetometer, reaction flywheels, magnetic torquers, and GNSS into one system.
Technical specifications
- Star Tracker - Quantity
- 2
- Star Tracker - Accuracy (Pointing/Rolling)
- 5" (3sigma) / 50" (3sigma)
- Star Tracker - Update Rate
- 10 Hz
- Star Tracker - Dynamic Range
- 2 deg/s
- Sun Sensor - Quantity
- 1
- Sun Sensor - Measurement Accuracy
- 0.1 deg (3sigma)
- Sun Sensor - Update Rate
- 10 Hz
- Sun Sensor - Field of View
- 90x90 deg
- Gyroscope - Quantity
- 1
- Gyroscope - Zero-Bias Stability
- 0.5 deg/h (Allan variance)
- Gyroscope - Angle Random Walk
- 0.03 deg/sqrt(h)
- Gyroscope - Velocity Range Measuring
- +/-300 deg/s
- Magnetometer - Quantity
- 1
- Magnetometer - Magnetic Measuring Range
- +/-8 Gauss
- Magnetometer - Linearity Error
- +/-1.0% FS
- Magnetometer - Magnetic Field Error
- 10 nT (1sigma)
- Reaction Flywheel - Quantity
- 4
- Reaction Flywheel - Max Output Angular Momentum
- 20 mNms
- Reaction Flywheel - Max Output Force Moment
- 2.5 mNm
- Reaction Flywheel - Speed Control Accuracy
- 1 rpm
- Reaction Flywheel - Force Moment Control Accuracy
- 10 nT (1sigma) [as printed on source page]
- Magnetic Torquer - Quantity
- 3
- Magnetic Torquer - Max Output Magnetic Moment
- 0.82 A*m2 (12V) / 0.34 A*m2 (5V)
- GNSS - Quantity
- 1
- GNSS - Resolution
- <=10 m
- GNSS - Velocity Accuracy
- <=0.1 m/s
About
The Attitude Control Module PnP ADCS-N1 is a fully integrated, plug-and-play attitude determination and control system (ADCS) for small satellites, combining a complete suite of sensors and actuators in a single module. It includes 2 star trackers (5 arcsec pointing / 50 arcsec rolling accuracy at 3-sigma, 10 Hz update rate, 2 deg/s dynamic range), a sun sensor (0.1 deg accuracy, 10 Hz, 90×90 deg FOV), a gyroscope (0.5 deg/h zero-bias stability, 0.03 deg/sqrt(h) angle random walk, +/-300 deg/s rate range), a magnetometer (+/-8 Gauss range, +/-1.0% FS linearity error, 10 nT field error), 4 reaction flywheels (20 mNms max angular momentum, 2.5 mNm max torque, 1 rpm speed control accuracy), 3 magnetic torquers (0.82 A*m2 at 12V / 0.34 A*m2 at 5V max magnetic moment), and a GNSS receiver (<=10 m position resolution, <=0.1 m/s velocity accuracy). By packaging attitude sensing, control actuation, and navigation into a single plug-and-play module, the ADCS-N1 simplifies satellite bus integration and provides full 3-axis attitude determination and control capability for small satellite/CubeSat missions.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.
