TY - JOUR ID - 151532 TI - Study the Performance of Hydrazine Monopropellant Thruster Catalysts with Different Iridium Loading JO - Space Science, Technology and Applications JA - JSSTA LA - en SN - AU - Ghadiri Massoom, Nooredin AU - rajabi, alireza AU - amirifar, mohamad ali AU - Amirsardari, Zahra AU - Dourani, Akram AU - kamranifar, majid AD - Researcher/Iranian Space Research Center AD - Iranian Space Research Center AD - Space Transportation Research Institute Y1 - 2022 PY - 2022 VL - 2 IS - 1 SP - 96 EP - 108 KW - Iridium Nanoparticles# Loading# Weight percentage# γ KW - alumina core# Hydrazine dissociation# Monoproellant thruster DO - 10.22034/jssta.2022.325976.1052 N2 - In this paper, the effects of different weight percentage of iridium (Ir) nanoparticles loadings on performance parameters of hydrazine catalyst and monopropellant thruster have been studied. Nanoparticles of iridium with different contents of 10 wt%, 20 wt%, and 30 wt% has been coated on gamma-alumina of 1 to 2 mm size for decomposition of hydrazine during some various steps of calcination. These catalysts then have been tested in a 1 N thruster. The tests were conducted using a scenario of different stages of steady and pulsating fires of different times and duty cycles. The test results showed that catalyst loss was minimum with 30 wt% of iridium nanoparticles loading. Despite of this, there were no meaningful difference between other parameters such as pressure roughness, thrust, specific impulse, and catalyst crushing. The results showed a good value of characteristic velocity. All parameter values of three type of catalysts were in the expected and desired range UR - https://journal.isrc.ac.ir/article_151532.html L1 - https://journal.isrc.ac.ir/article_151532_c8e202aa7f9c69dea72f0d64e82497b4.pdf ER -