Achieving new technologies with high Reliability while reducing the cost and time of the Design cycle is one of the most significant challenges in developing complex systems. This paper discusses the Reliability-Based Design of a space system during the conceptual Design phase. Generally, there are eight steps in Designing for Reliability. As applied to a liquid propellant engine with electro-pump technology, these steps include planning, determination of failure modes, Reliability modeling, Reliability allocation, propagation of uncertainty, implementation of the chosen method in Reliability analysis, Reliability prediction, and Reliability evaluation. Each step contains sub-steps that follow in a specific order.In the second step, the prediction of failure modes is carried out using two FMEA methods alongside Design constraints. The third step involves developing the Reliability block diagram for the electro-pump. In the fourth step, various Reliability feature methods are introduced and reviewed. The fifth step presents four approaches to investigate uncertainty: sampling methods, analytical methods such as FORM and SORM, polynomial estimation using Taylor series, and advanced methods like random expansion.Subsequently, the uncertainty in the electro-pump engine is addressed alongside the limited functions in the electro-pump engine. Finally, in the seventh step, the Reliability evaluation of the electro-pump engine is discussed. This evaluation is conducted to validate the proposed method, where Reliability is determined using two indicators: specific impulse and mass ratio (initial mass to final mass).