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Journal of Aerospace Science and Technology، جلد ۱۴، شماره ۲، صفحات ۸۰-۹۵
عنوان فارسی Designing, construction and testing a passive, two-sided, and efficient de-orbiting mechanism for CubeSats
چکیده فارسی مقاله In this article, we analyze the existing de-orbiting mechanisms in the world and analyze different types of these mechanisms for Nano satellites, also known as CubeSats. Moreover, a new passive and efficient design of the de-orbiting mechanism for the CubeSats have been proposed. Utilizing de-orbiting mechanisms are important in Nano satellites or CubeSats to prevent production of space debris in LEO (low-earth orbit), and in NASIR-1 CubeSat, Sail Drag method was used to do so. In this method, the satellite is deorbited using passive two-sided de-orbiting approach in 1.7 years on average, or less than a maximum of 2 years. Software analysis is used to calculate membrane size and the required boom mechanisms in LEO, 600 km from the earth’s surface. Drag sail is designed using software and the prototype as well as the final version for engineering model are made and tested. The passive two-sided sail drag design of NASIR-1 is a more efficient mechanism compared to active, four-sided models in terms of volume, weight and the required electrical power and it offers a larger available externa surface on CubeSat’s surfaces.
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عنوان انگلیسی Designing, construction and testing a passive, two-sided, and efficient de-orbiting mechanism for CubeSats
چکیده انگلیسی مقاله In this article, we analyze the existing de-orbiting mechanisms in the world and analyze different types of these mechanisms for Nano satellites, also known as CubeSats. Moreover, a new passive and efficient design of the de-orbiting mechanism for the CubeSats have been proposed. Utilizing de-orbiting mechanisms are important in Nano satellites or CubeSats to prevent production of space debris in LEO (low-earth orbit), and in NASIR-1 CubeSat, Sail Drag method was used to do so. In this method, the satellite is deorbited using passive two-sided de-orbiting approach in 1.7 years on average, or less than a maximum of 2 years. Software analysis is used to calculate membrane size and the required boom mechanisms in LEO, 600 km from the earth’s surface. Drag sail is designed using software and the prototype as well as the final version for engineering model are made and tested. The passive two-sided sail drag design of NASIR-1 is a more efficient mechanism compared to active, four-sided models in terms of volume, weight and the required electrical power and it offers a larger available externa surface on CubeSat’s surfaces.
کلیدواژه‌های انگلیسی مقاله Drag Sail mechanism,De-orbiting,CubeSat,passive,Low-Earth Orbit (LEO)
نویسندگان مقاله Hamed Alisadeghi |
Aerospace engineering department,K.N. Toosi University of technology, tehran, iran

Parsa Abbasrezaee |
Aerospace Department, K.N.Toosi University of Technology, Tehran, Iran

نشانی اینترنتی https://jast.ias.ir/article_139284_7c6195f0ef792fa17fb022aba57fe776.pdf
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