Deployable mechanisms for small to medium sized space debris removal

This research aims to propose a new paradigm in orbital debris removal systems. While most groups addressing this \nissue focus on the high priority of removing the largest debris, we consider the threat posed by those smaller than 10cm as \nserious. A 2cm paint chip is known to be able to render useless most spacecraft as well as being way more difficult to follow \nand thus to avoid. We propose a mission to sweep the main Low Earth Orbits with a 100 to 500 metre diameter cupola \nthat would collect small debris. The cupola consists of a deployable mechanism supporting a membrane. The deployment \nmechanism has to reach a minimal expansion ratio of about 30, in order to create a very wide collecting surface. The \nmembrane covering its surface would be rigid enough to capture most small debris and to at least slow down the mediumsized \nones, accelerating their fall. An overview of our almost-rigid-link mechanism proposed to support the collecting surface \nis presented. The proposed mechanisms is based on previous work on deployable mechanisms developed for a variety of \napplications. However, conventional deployable rigid-link mechanisms typically produce expansions that are much smaller \nthat the ratio required in the present application. Therefore, cable or belts systems are included in order to further increase the \nexpansion ratio while maintaining a low mass. While in operation, the cupola will obviously be subjected to many ultra-highvelocity \nimpacts and its orientation will likely undergo deviations from the targeted optimum. Therefore, another important \nfeature of the proposed debris removal concept is the development of means of reorienting and stabilizing the cupola using \ninternal electric deployment actuators instead of fuel thrusters. The concept of reorientation using internal actuators is \npresented and simple examples are provided. Finally, the performance of the concept is confronted to data analysis from \nMASTER09 and with the recent release of ORDEM3. This data serves as the basis for the design specifications. Space \ndebris removal is a high priority for the future of space missions and space exploration. The approach proposed here is \nbelieved to be one of the pieces of the puzzle.

Récupéré en direct depuis OpenAlex et désinversé. Les résumés ne sont pas conservés dans cette base de données : les index inversés représentent 8,6 Go des 9,3 Go de texte de la base, et le serveur dispose de 13 Go libres.