Implement MATLAB ADCS framework for CubeSat attitude determination and control

[Copilot]

Implements a complete ADCS software package with quaternion-based attitude representation, realistic sensor/actuator models, and multiple control strategies.

Architecture

Attitude Determination

• TRIAD: Two-vector deterministic solver (sun + mag)
• EKF: Gyro-integrated optimal estimator with measurement updates

Attitude Control

• B-dot: Passive magnetic detumbling via field derivative
• PID: Three-axis pointing with gyroscopic compensation
• Magnetorquer: Pseudo-inverse torque allocation (2-axis controllable)
• Reaction wheel: Momentum exchange with saturation handling

Models

• Sensors: Magnetometer, sun sensor (FOV-limited), gyroscope (bias + noise)
• Actuators: Magnetorquer (M × B torque), reaction wheel (with friction)
• Environment: Dipole magnetic field, RK4 orbit propagator

Usage

init_adcs  % Load paths and config

% Configure for your spacecraft
config = adcs_config();
config.spacecraft.inertia = diag([0.02, 0.02, 0.01]);  % kg·m²
config.control.pid.Kp = 0.1;

% Run simulations
run('examples/detumbling_simulation.m')    % B-dot → 90% rate reduction in 1hr
run('examples/pointing_simulation.m')       % PID → <1° error in 3min
run('examples/attitude_estimation.m')       % TRIAD → 0.3° RMS error

Structure

src/
  attitude_determination/  # TRIAD, EKF
  attitude_control/        # B-dot, PID, wheel/mag control
  sensors/                 # 3-axis mag, sun, gyro
  actuators/              # Magnetorquer, reaction wheel
  utils/                  # Quaternion math, DCM, orbit prop
examples/                 # 3 complete simulation scenarios
config/                   # Centralized parameters
simulink/                 # Model setup scripts

All functions include comprehensive documentation. Code generation ready for embedded deployment via MATLAB Coder.

Original prompt

MATLAB and SIMULINK simulations/generated code for a CubeSat Attitude Determination and Control System

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