Elektrik itki sistemleri kullanarak küçük uydu ay görevleri için sistem seviyesinde eniyileme yaklaşımı ve Türkiye uzay ekonomisi için görev maliyet incelemesi

This thesis presents a system-level optimization approach to perform low-cost small satellite lunar mission by using existing ion and hall propulsion systems. The system-level optimization finds minimum flight time accompanied with maximum payload mass, minimum initial spacecraft mass and optimum spacecraft volume values. To create accurate mission analysis two types of optimization approaches are studied; iterative method and constrained optimization method. These methods calculates various mission scenarios such as ion thruster LEO departure orbit, ion thruster GEO departure orbit and hall thruster LEO and GEO departure orbits. In the iterative method, ion thruster LEO departure case results a spacecraft mass of 213 kg and corresponding 23mN thrust value. This case needs 64 kg xenon propellant to perform 980 days flight duration to the Moon. The optimum spacecraft volume is found as 0.70m3 and costs $108.5M. Same thrust level of 23mN for GEO departure case takes 880 days with 58 kg xenon gas. The total cost reduces $2.5M. However by using hall thruster system, LEO departure case needs 0.8m3, 247 kg spacecraft including 82 kg xenon propellant. 77 mN thrust results 208 days ight time towards the Moon that ends up with $121M total cost. The GEO departure Hall case reduces the flight time an amount of 45 days by consuming 65 kg propellant. Total spacecraft mass and volume values are 230 kg, 0.71m3 that costs $115M. Finally, the overall cost of lunar mission cases is discussed for Turkey space economy. The space technology demand of investment will increase up to $400M in 2020s, an overall cost with $100M lunar mission seems applicable however needs significant collaboration among universities,private sector and government.