Development of Hybrid Actuator System for Recovery of the Model Rockets

Model rockets are the advanced mechatronic systems established through the design, manufacturing, and integration of the model-scale mechatronic sub-systems for a rocket mechanism capable of operating at low altitudes. The safe recovery and reusability of model rockets are prominent tasks to address. Various actuator systems are used in model rockets to solve the safe recovery problem by safely releasing and recovering the payloads that they carry at specific altitudes, allowing the rockets to be recovered. Traditionally, model rockets have employed recovery units powered by gunpowder. This research aims to design a novel hybrid actuator system integrating mechanical components with pressurized gas and servo motor components as an alternative to traditional gunpowder systems to enhance reliability and safety. The objective is to develop a prototype of a hybrid recovery actuator system using CO
2
tubes and servo motors. The principle behind the designed recovery system relies on the release of CO
2
gas, which facilitates the separation of the rocket motor body from the main body. This principle is based on the mechanism within the designed actuator system, which functions by releasing the potential energy stored in compressed springs. Servo motors triggered by signals from the rocket’s flight computer release the springs, allowing the CO
2
gas to escape. The released gas separates the rocket bodies, ensuring a safe descent. Within the scope of this research, the efficiency and effectiveness of the CO
2
based hybrid recovery actuator system are evaluated through the production of a prototype. The experimental results unveiled that the development of the CO
2
based hybrid recovery actuator system enables safe and successful recovery of model rockets. To achieve the timely release of the CO
2
gas in the recovery system, the required pressure is determined via experimental studies for the separation of rocket bodies, ensuring a safe descent.