h. naseh

One of the most important steps in designing spacecraft is designing their control system. There are many types of control systems, often including electric thrusters, cold gas thrusters, and monopropellant thrusters. Monopropellant thrusters generate more propulsion than other thrusters and are more cost-effective for short space missions. In this study, arrangement of 12 hydrazine monopropellant thrusters on a spacecraft was investigated. Based on the required torque, twelve thrusters were used to control the situation of the spacecraft, so that each axis is controlled by four thrusters and each thruster must provide the propulsion force equal to 10 N. For this purpose, 10 N hydrazine monopropellant thrusters were used. Finally, three different arrangements of thrusters were presented. The third type of arrangement was selected due to its independence from changes in the space center of mass of the spacecraft and also zero slope of the thrusters relative to the main axes.

The purpose of this study is to provide an efficient Multi-Objective Multidisciplinary Robust Design Optimization (MOMRDO) framework. To this end, Bi-Level Integrated System Synthesis (BLISS) framework is implemented as a fast Multi-disciplinary Design Optimization (MDO) framework. Progressive Latin Hypercube Sampling (PLHS) is developed as a Design of Experiment (DOE) of the Uncertainty Analysis (UA). This systematic approach leads to a fast, adaptive and efficient framework for Robust Design Optimization (RDO) of complex systems. The accuracy and performance of the proposed algorithm have been evaluated with various tests. Finally, the RDO of a hydrazine monopropellant thruster is defined as a case study. The results show that the proposed method is a fast and efficient method for the multi-objective optimization design of complex systems, and this approach can be used for other engineering applications as well.