Session
Poster Session 1
Abstract
More countries are relying on small satellites to conduct research in Low-Earth Orbit (LEO). This has increased focus on developing microthrusters to counter atmospheric drag. This paper aims to design such a microthruster for the CubeSat to augment orbital lifetime and allow more meaningful space experimentation. This was done by first selecting an available microthruster design that met altitude boosting requirements. This design was then reconstructed with material changes, and tested for material suitability. A second design, with optimised geometry, was then conceptualised. This new microthruster will use 3,3(')-azobis(6-amino-1,2,4,5-tetrazine)-mixed N-oxides (DAATO3.5) as its solid propellant. However, due to import restrictions, tests were performed using ammonium carbonate and comparisons were made to approximate the performance of DAATO3.5, by calculating an efficiency factor (η) based on simulated and experimental results. Prototypes with ammonium carbonate were tested in vacuum (10-3 mbar) and gave a specific impulse of 9.15 s. This was found to be 22.21% (η) of simulated results. Applying this factor to DAATO3.5 gave a specific impulse of 24.9 s for a 16-microthruster array. This would give an altitude gain of 5.45 km, increasing orbital lifetime by 20% (12 days).
Designing a Boosting Microthruster for Altitude Maintenance of Picosatellites
More countries are relying on small satellites to conduct research in Low-Earth Orbit (LEO). This has increased focus on developing microthrusters to counter atmospheric drag. This paper aims to design such a microthruster for the CubeSat to augment orbital lifetime and allow more meaningful space experimentation. This was done by first selecting an available microthruster design that met altitude boosting requirements. This design was then reconstructed with material changes, and tested for material suitability. A second design, with optimised geometry, was then conceptualised. This new microthruster will use 3,3(')-azobis(6-amino-1,2,4,5-tetrazine)-mixed N-oxides (DAATO3.5) as its solid propellant. However, due to import restrictions, tests were performed using ammonium carbonate and comparisons were made to approximate the performance of DAATO3.5, by calculating an efficiency factor (η) based on simulated and experimental results. Prototypes with ammonium carbonate were tested in vacuum (10-3 mbar) and gave a specific impulse of 9.15 s. This was found to be 22.21% (η) of simulated results. Applying this factor to DAATO3.5 gave a specific impulse of 24.9 s for a 16-microthruster array. This would give an altitude gain of 5.45 km, increasing orbital lifetime by 20% (12 days).
