Designing, construction and testing a passive, two-sided, and efficient de-orbiting mechanism for CubeSats

Document Type : Original Article

Authors

1 Aerospace engineering department,K.N. Toosi University of technology, tehran, iran

2 Aerospace Department, K.N.Toosi University of Technology, Tehran, Iran

Abstract

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.

Keywords

Main Subjects


Article Title [فارسی]

Designing, construction and testing a passive, two-sided, and efficient de-orbiting mechanism for CubeSats

Authors [فارسی]

  • Hamed Alisadeghi 1
  • Parsa Abbasrezaee 2
1 Aerospace engineering department,K.N. Toosi University of technology, tehran, iran
2 Aerospace Department, K.N.Toosi University of Technology, Tehran, Iran
Abstract [فارسی]

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.

Keywords [فارسی]

  • Drag Sail mechanism
  • De-orbiting
  • CubeSat
  • passive
  • Low-Earth Orbit (LEO)