Les besoins croissants en moyens de télécommunication nécessitent le développement de grands réflecteurs spatiaux paraboliques. Un nouveau concept d'architecture d'antenne déployable est ainsi proposé en partenariat avec le CNES. La conception de son ossature repose sur une revue de solutions pour faire appel à des mécanismes de ciseau associés à des articulations flexibles. Des modélisations numériques par éléments finis sont d'abord développées pour simuler le déploiement par restitution de l'énergie emmagasinée dans ces articulations lors du pliage. Un démonstrateur expérimental avec un système de compensation gravitaire est ensuite réalisé. Des essais et mesures sont effectués pour caractériser son comportement en statique et dynamique puis sont comparés avec les résultats issus des simulations. La mise en forme de la surface réflectrice par un réseau de câbles est étudiée par la suite. Une méthode innovante de recherche de forme permettant d'obtenir un réseau parabolique en tension uniforme est alors proposée. Elle est appliquée à différentes typologies de réseaux et l'erreur de surface résultant de sa facettisation est évaluée. Le procédé d'accrochage de ce réseau sur l'ossature de l'antenne est également traité. / The growing needs in telecommunications require the development of large parabolic reflectors. A new conceptual design for the architecture of a deployable antenna is therefore proposed in partnership with the CNES. The design of its framework is based on a review of solutions which leads to scissor mechanisms associated with flexible joints. Numerical modelings with finite elements are first developed to simulate the deployment by the release of the energy stored in the joints after the folding. An experimental prototype with a gravity compensation device is then realized. Tests and measurements are performed to characterize the static and dynamic behavior and compared with the results of simulations. Shaping of the reflective surface by a net of cables is then studied. A new form-finding method for obtaining a net with a uniform tension is then proposed. It is applied to different parabolic typologies of nets and the error due to surface faceting is evaluated. The process of net attachment on the antenna rim structure is also treated.

New Horizons, Voyager 1 & 2, and Pioneer 10 & 11 are the only spacecraft to ever venture past Pluto and provide information about space at those large distances. These spacecraft were very expensive and primarily designed to study planets during gravitational assist maneuvers. They were not designed to explore space past Pluto and their study of this environment is at best a secondary mission. These spacecraft rely on radioisotope thermoelectric generators (RTGs) to provide power, an expensive yet necessary approach to generating sufficient power. With Cubesats graduating to interplanetary capabilities, such as the Mars-bound MarCO spacecraft, matching the modest payload requirements to study the outer Solar System (OSS) with the capabilities of low-power nano-satellites may enable much more affordable access to deep space. This paper explores a design concept for a low-cost, small spacecraft, designed to study the OSS and satisfy mission requirements with solar power. The general spacecraft design incorporates a parabolic reflector that acts as both a solar concentrator and a high gain antenna. This paper explores a working design concept for a small spacecraft to operate up to 100 astronomical units (AU) from the sun. Deployable reflector designs, thermal and radiation environments, communications and power requirements, solar system escape trajectory options, and scientific payload requirements are detailed, and a working system is proposed that can fulfill mission requirements with expected near-future innovations in a few key technologies.