Designing a 200 N Bi-Propellant Thruster: Key Considerations

This lecture focuses on the design of a 200 N bi-propellant thruster, emphasizing the critical parameters and assumptions necessary for effective design. The instructor outlines the objective of designing a thruster within a 30-minute timeframe, detailing the performance specifications, including the use of HTP as an oxidizer and hypergolic pyridine as fuel. The lecture covers essential design elements such as main dimensions, mass flow rate, and optimal mixture ratios, while also discussing the implications of chamber pressure and nozzle area ratios. Various design methodologies are presented, including the implementation of a bell-shaped nozzle and considerations for combustion chamber length. The instructor provides insights into the cooling requirements and injection methods, specifically focusing on impingement techniques. Throughout the lecture, the importance of specific impulse and characteristic speed in thruster performance is highlighted, providing a comprehensive overview of the factors influencing thruster architecture and efficiency.