Spacecraft Attitude Adjustment System Design for Small Satellites

This document presents the design of an attitude adjustment system for small satellites. The system implements the following core functionalities:

- Attitude Measurement: Utilizes sensors including gyroscopes, star trackers, and magnetometers to determine satellite orientation. The implementation involves sensor fusion algorithms (like Kalman filters) to process raw data and compute precise attitude quaternions or Euler angles.

- Attitude Control: Employs control actuators such as reaction wheels and magnetorquers to adjust satellite attitude based on measurement feedback. The control logic typically involves PID controllers or more advanced control algorithms that calculate required torque commands from attitude error signals.

- Orbit Calculation: Determines satellite position and trajectory through measurement data processing and orbital mechanics computations. This module implements algorithms for orbit propagation (e.g., using SGP4 models) and navigation solution convergence.

- System Management: Includes design and implementation of power management, memory allocation, and data transmission protocols to ensure efficient and stable system operation. This involves real-time task scheduling, power budgeting algorithms, and communication protocol handlers for reliable data transfer.

To ensure system reliability and stability, rigorous testing and validation procedures will be conducted. Comprehensive fault detection, isolation, and recovery (FDIR) algorithms will be implemented, along with detailed maintenance protocols to guarantee normal operation under various complex environmental conditions.