evaluation of non-turbopump feed systems for application in a two-stage launch vehicle

Given the significant cost associated with space missions, optimizing launch vehicles (lvs) has been a major focus. the main component of a launch vehicle, and a significant contributor to its cost, is the propulsion system. propulsion systems can be primarily categorized into two types based on their feeding mechanisms: pump-fed and pressure-fed.. this paper, considers the development of non-turbopump propulsion systems for optimum lv design. to this purpose, disciplines modeling of lv have been presented. multidisciplinary design optimization of non-turbopump lv is proposed based on the all at once framework, and validation has been given. the desired mission is to send the maximum payload mass into a 250 km orbit with the minimum total mass of the lv. according to the results, the new optimal gas pressure fed lv concept is introduced as a low-cost and efficient launcher in terms of mass, dimensions, and performance. by mission optimization, the optimal gpf-lv can carry and inject 1857 kg of payload with 85.602 tons of gross mass (μ_pay=0.02169) into a 250 km orbit.