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.
Attitude Control Module PnP ADCS-N1
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.
Description
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, 90x90 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.
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 |
