Design of Hydrazine Thruster Cluster Propulsion System in Space Probe

Designing the control system is a crucial phase in spacecraft development. Control systems come in various forms, typically including electrical actuators, cold gas thrusters, and monopropellant thrusters. Monopropellant micro-thrusters generate more thrust compared to other actuators and are more cost-effective for short space missions. This research focuses on the design of the propulsion system for hydrazine monopropellant thrusters on a space probe. Based on the required torque for attitude control, twelve micro-thrusters were utilized. Each axis is controlled by four actuators, with each actuator required to provide 10 Newtons of thrust. For this purpose, 10 N hydrazine thrusters were employed. The thrusters are arranged on the carrier within the biological capsule as two sets of four and two sets of two. Each set is designed modularly, meaning that the propellant tank and connections for each set are independent of the other sets. This study determined the necessary quantities of hydrazine and nitrogen gas, as well as the required tank volumes for the system.