Deployment of Solar Sails by Joule Effect: Thermal Analysis and Experimental Results

Gianluigi Bovesecchi,Sandra Corasaniti,Maria Elisa Tata,Girolamo Costanza,Fabrizio Paolo Piferi

doi:10.3390/aerospace7120180

Gianluigi Bovesecchi, Sandra Corasaniti + Show 3 more

Open Access

https://doi.org/10.3390/aerospace7120180

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Journal: Aerospace	Publication Date: Dec 16, 2020
Citations: 4	License type: CC BY 4.0

Affiliation: University of Rome Tor Vergata

Abstract

Space vehicles may be propelled by solar sails exploiting the radiation pressure coming from the sun and applied on their surfaces. This work deals with the adoption of Nickel-Titanium Shape Memory Alloy (SMA) elements in the sail deployment mechanism activated by the Joule Effect, i.e., using the same SMA elements as a resistance within suitable designed electrical circuits. Mathematical models were analyzed for the thermal analysis by implementing algorithms for the evaluation of the temperature trend depending on the design parameters. Several solar sail prototypes were built up and tested with different number, size, and arrangement of the SMA elements, as well as the type of the selected electrical circuit. The main parameters were discussed in the tested configurations and advantages discussed as well.

Highlights

The working principle of solar sails is based on the impingement of solar radiation photons on the sail surface [1]
Since small values of radiation pressure are reached in the solar system, in the order of μPa for the planets close to the Sun, it is necessary to design sails with quite large surfaces in order to exploit this propulsion system
A suitable electrical circuit, in which the Shape Memory Alloy (SMA) elements were used as resistances, was made so that the SMA elements can be activated reaching the critical transformation temperature by Joule effect

Summary

Introduction

The working principle of solar sails is based on the impingement of solar radiation photons on the sail surface [1]. In this way the solar radiation pressure can be employed to propel spacecrafts [2,3]. This force can be maximized in the presence of a highly reflective surface and low weight [4]. Since small values of radiation pressure are reached in the solar system, in the order of μPa for the planets close to the Sun, it is necessary to design sails with quite large surfaces in order to exploit this propulsion system. It is necessary to foresee the folding and the packaging so that these, after being stowed inside satellites and launched into orbit, can properly be deployed once reached their operational position [5]

Results

Discussion

Conclusion