The increasing cost and inefficiency of expendable launch vehicles have driven the aerospace industry toward the development of reusable rocket systems capable of vertical takeoff and controlled re-landing. Reusable Launch Vehicles (RLVs) significantly reduce mission costs, improve launch frequency, and promote sustainable space exploration. This project presents the design and development of a scaled Rocket Launch and Re-Landing Model that demonstrates the fundamental principles of controlled vertical ascent, autonomous guided descent, and safe vertical landing.

The proposed system integrates electrical and control engineering concepts such as sensor-based feedback, embedded systems, propulsion control, and autonomous flight algorithms. Key components include a microcontroller-based flight controller, inertial measurement sensors, altitude sensing, thrust control mechanisms, and a mechanical landing buffer system. Advanced control strategies such as PID control and Model Predictive Control (MPC) are employed to ensure stability, trajectory optimization, and precise landing under varying conditions.

The project also focuses on analyzing landing dynamics, load distribution on landing legs, and shock absorption techniques to minimize impact forces during touchdown. Simulation studies are used to model flight behavior and optimize control parameters before experimental validation. The prototype demonstrates repeated launch and re-landing cycles, validating the feasibility of reusable rocket concepts at a low-cost experimental scale.

This work serves as an educational and practical platform for understanding modern reusable rocket technologies while bridging the gap between theoretical aerospace concepts and hands-on engineering implementation. The proposed model contributes to the advancement of cost-effective, reliable, and sustainable space transportation systems and provides a foundation for future research in reusable launch vehicle technology.