Yüksek kademe karma roketler için elektrik tahrikli kriyojenik pompa geliştirmesi

The performance of a rocket propulsion system utilizing liquid propellants depends on the propellant feed system (PFS) performance and capability. A PFS must be able to deliver the propellant at the desired flow rate and pressure into the combustion chamber. The most commonly used mechanisms for PFS consist of pressurization by a cold gas or pressurization by a pump. The first method requires pressurizing the entire feed system including propellant tanks to its delivery pressure while the second one pressurizes only a small portion of the feed line but requires a mechanical power source. These two methods have been used widely where pumps are employed on high thrust and power applications while cold gas pressurization is employed on relatively small and less sophisticated systems. The reason for this is that only capable power sources for high-performance pumps were turbines and this approach was not viable for lower thrust level systems due to its complexity and cost. As the space industry leans towards micro-satellites, the development of launch vehicles in this class is gaining more attention. Weight disadvantage of pressure-fed systems, complexity, development cost and time of turbopump systems and emerging power electronics, battery, and electric motor technologies arouse the question of the viability of electric driven pumps on micro-satellite level propulsion systems. This study is aimed to show the advantages of electric pump utilization over cold gas pressurization in hybrid rockets through an electric pump development process. For this, a hydraulic and mechanical design is made from a set of system requirements and the performance of this pump is assessed by means of CFD analysis. The CFD model is validated by pump tests. Then two separate hybrid rocket propulsion systems are designed, one of which employs electric pump and the other is pressure-fed. A system-level comparison of performance on different operational parameters, concluding high fidelity evidence for the thesis argument. Final results show that electric pumps are quite beneficial for upper stage hybrid rocket propulsion systems.