نوع مقاله : مقاله پژوهشی
نویسندگان
1 دانشگاه آزاد اسلامی واحد علوم و تحقیقات تهران/دانشکده نفت و مهندسی شیمی/گروه مهندسی شیمی
2 استادیار -دانشکده نفت و مهندسی شیمی -گروه مهندسی شیمی -دانشگاه آزاد اسلامی واحد علوم و تحقیقات
3 دانشیار مهندسی شیمی ، دانشگاه صنعتی مالک اشتر
چکیده
کلیدواژه‌ها
موضوعات
عنوان مقاله [English]
نویسندگان [English]
In this research, the heterogeneous decomposition reaction of hydrazine and ammonia in a space propulsion system of hydrazine monopropellant type with an adiabatic fixed bed reactor and 30% iridium catalyst Ir/γ-〖Al〗_2 O_3 is used to create a thrust force of 5 newtons and a specific impulse of 220 seconds and the application of position change or orbital motion. This process is created by two heterogeneous reactions and turning into hot light gases of hydrogen and nitrogen leaving the reactor bed and then the nozzle of the thrust force in the opposite direction of the gas flow. Considering that the iridium 30% Ir/γ-〖Al〗_2 O_3 is a reference and main catalyst that has suitable mechanical, physical, and thermal properties but is very rare and expensive, the purpose of using a nickel replacement catalyst 15% is Ni/γ-〖Al〗_2 O_3. Compared to iridium, this catalyst is very abundant and cheap, and has functional characteristics, suitable and close to iridium. Regarding the correctness and accuracy of the performance results of two catalysts in a space propulsion system and vacuum conditions and the same static and operational test in a stable and uniform flow of hydrazine to the reactor bed for 30 seconds were measured and evaluated by evaluation indicators such as creating force Thrust (5 newtons), special impulse (about 230 seconds), bed pressure drop (less than 1 bar), minimum amount of ammonia decomposition are compared. Finally, due to the compatibility of nickel catalysts with iridium, a suitable alternative is approved.
کلیدواژه‌ها [English]
)