Barberpole, mechanism for space tether deployment

Paper number

IAC-05-C2.P.02

Author

Prof. Carlo Menon, Simon Fraser University, Canada

Coauthor

Mr. Michiel Kruijff, Delta-Utec, The Netherlands

Coauthor

Mr. Antonios Vavouliotis, University of Patras, Greece

Coauthor

Mr. Angelos Miaris, University of Patras, Greece

Coauthor

Prof. Vassilis Kostopoulos, University of Patras, Greece

Coauthor

Prof. Francesco Angrilli, University of Padova, Italy

Year

2005

Abstract

The Young Engineers Satellite 2 (YES2) is a demonstrating mission aimed at testing a revolutionary payload transport system for future use on the International Space Station (ISS). The YES2 mission, scheduled for a launch on a Soyuz Foton module in 2006, will show that tether technology provides an excellent way towards the implementation of a frequent sample return from space. An unmanned inflatable capsule will accurately land in a foreseen spot by using a very simple and lightweight tether hardware. The capsule will be ejected from the Foton module and its re-entry will be guided deploying a 32 km Dyneema tether. By bringing the deployment to a halt, a pendulum like swing will be induced. When the capsule and tether will be swinging through the local vertical, the tether will be cut leaving the capsule free to re-enter towards the Earth. 
The need of a robust tether braking mechanism led the authors of this paper to develop a special mechanical device: the Barberpole. This mechanism has a crucial importance for the success of YES2 mission since it controls the whole dynamics of the capsule re-entry. The Barberpole was accurately designed and a reliable and efficient flight model was built. Thermal analyses were carried out showing that the Barberpole braking operations will not thermally compromise the performance of the tether. A mathematical model of the Barberpole was developed and successfully used to characterize the ideal performance of the mechanism. A custom built ground experimental testbed was also designed, built and employed to identify the model parameters of the Barberpole. This testbed was of primary importance to simulate the deployment phase and test the reliability of the Barberpole. A parabolic flight experiment was also performed to test the mechanism in a micro-gravitational environment.
This paper describes the mathematical model, design strategies and analyses carried out for the newly developed Barberpole. It also presents the experimental systems which were developed and used for testing the braking mechanism. The experimental results which are discussed, are consistent with the simulation results. The performed tests were repeatable and showed that the barberpole was reliable and it fitted the requirements of the YES2 mission.

Abstract document

IAC-05-C2.P.02.pdf

Manuscript document

IAC-05-C2.P.02.pdf (🔒 authorized access only).

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