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Comparison between Multiple bare tethers and Single Bare Tether for Deorbiting satellites

Deepthi Narasimhan1,Ananya M2,Suraj R3,Chiranthan K4,Ankur Mahur5,Maithili Pathak6,Seemaparvez Shaik7,Aldrin . A8,Arunadevi T. M9,Aditya Bhaskaran10
Jain, Deemed to be University, Bengaluru1Sahyadri College of Engineering and Management, Mangalore2Amrita Vishwa Vidyapeetham Coimbatore3Ramaiah Institute of Technology, Bengaluru4Sir M.Visvesvaraya institute of technology, Bengaluru5K. J. Somaiya College of Engineering, Vidyavihar, Mumbai6Findem7Hindustan Institute of technology and Science8Freelancer9SRM Institute of Science & Technology10

Document details

Publishing year2021 PublisherESA Space Debris Office Publishing typeConference Name of conference8th European Conference on Space Debris
Pagesn/a Volume
T. Flohrer, S. Lemmens, F. Schmitz


As per the Inter-agencies Space Debris Coordination Committee (IADC) guidelines, the satellites in Low Earth Orbits (LEO) must have an orbital lifetime of fewer than 25 years. Tethers used in previous missions have been subjected to damage due to their extremely large lengths. Hence a multi-tether design with each tether shorter in length is proposed which could thus reduce the probability of damage to tethers. This paper compares the working of multiple bare short electro-dynamic tethers versus a single long bare tethered system on a satellite in Low Earth Orbit (LEO) for end of life de-orbiting to combat the further formation of space debris. The paper shows the use of several shorter tethers, each equally long, placed in parallel orientation on one face of the satellite. It also upholds the fact that the same drag force can be produced using a multiple tether system as that of a single long tether. A similar comparison considering the de-orbiting time of both the systems are presented along with the effects of initial induced voltage and current. Optimum spacing distances between the multiple short tethers to obtain the maximum efficiency from each are also discussed in the paper.