A miniature rocket system capable of stabilizing itself during flight by actively adjusting the direction of thrust — combining embedded control, sensor fusion, and 3D design to mimic real aerospace control systems. Design, build, and test a self-stabilizing rocket using a custom flight computer and control algorithms.
The project focuses on building a miniature rocket system capable of stabilizing itself during flight by actively adjusting the direction of thrust. The entire setup combines embedded control, sensor fusion, and 3D design to mimic real aerospace control systems on a smaller scale. Overall the idea was to design, build, and test a self-stabilizing rocket using a custom flight computer and control algorithms.
Goals included improving rocket flight stability using active thrust vector control; integrating sensors and control logic for real-time attitude correction; building a fully functional prototype — from electronics to mechanical design — using 3D printing and embedded systems; and testing the control accuracy and responsiveness through simulation and live launches.
Defined the control objective: stabilize pitch and yaw during thrust. Modeled the control loop using MATLAB/Simulink or similar tools. Designed a lightweight 3D-printed thrust mount for servo-driven nozzle movement.
Built a custom flight computer using ESP WROOM 32 (for processing and data logging). Integrated MPU6050 (gyro + accelerometer) for orientation and BMP280 for altitude sensing. Used micro servos to control the nozzle's angular position.
Implemented a PID controller, tuned with the Ziegler–Nichols method. Applied a Kalman filter for sensor fusion and noise reduction. Programmed real-time data collection and servo control in C++ using Arduino IDE / PlatformIO. The system was first validated through stability simulations to fine-tune PID parameters before flight. Static ground tests were then performed to analyze servo response and verify control stability. Finally, live flight tests using an Apogee E16 motor confirmed the system's performance — demonstrating stable flight, reduced oscillations, and precise attitude correction. The integration of sensor fusion improved response accuracy, while PID tuning effectively minimized overshoot.
Stabilizing pitch and yaw during thrust with a lightweight, real-time control system.
Sensor fusion and noise reduction for reliable attitude estimation (Kalman filter, PID tuning).
Validating control accuracy and responsiveness through simulation, ground tests, and live launches.
Live flight tests with Apogee E16 motor demonstrated stable flight, reduced oscillations, and precise attitude correction.
The integration of sensor fusion improved response accuracy; PID tuning effectively minimized overshoot.
Fully functional prototype from electronics to mechanical design, using 3D printing (Bambu Lab A1 Mini, PLA) and embedded systems.
The system was developed through concept and system design, hardware integration, control algorithm implementation, and simulation, testing, and validation. Control methods: PID control, Kalman filter, Ziegler–Nichols tuning. Manufacturing: 3D printing (Bambu Lab A1 Mini, PLA material).
The integration of sensor fusion improved response accuracy, while PID tuning effectively minimized overshoot.
Future work could include different motor classes, additional sensors, or post-flight data analysis tooling.