The IKAROS solar sail from the Japan Aerospace Exploration Agency (JAXA) was designed to reach Venus. To achieve this, it was placed in orbit by a rocket, and using variable reflection modules, it maintained its orbit through photon pressure. The Payankeu solar sail, supported by the U3P (Union for the Promotion of Photon Propulsion) and developed by the University of La Réunion, will have to leave an Earth orbit at 50,000 km to reach the Moon at 400,000 km. For its expedition to the Moon, can Payankeu be equipped with variable reflection modules akin to those on IKAROS, allowing it to modify its orbit rather than merely sustaining it ? Unlike IKAROS, which traveled along an elliptical path, Payankeu will have to follow a spiral trajectory, requiring much more frequent maneuvering of the sail than its predecessor. The sail will thus be subjected to additional constraints, and the effects on the device need to be determined to anticipate its behavior. The aim of this study is to determine whether the use of the reflective module provides sufficient maneuverability for Payankeu's mission. Once in space, Payankeu deploys its sail thanks to the centrifugal force generated by its rotation speed. It is then directed by variable reflection modules that twist the sail, allowing the sail to move forward and change direction. However, the gyroscopic effect due to the rotation speed opposes the changes in orientation of the satellite by reducing the impact of torsion forces. These forces are linked to the surfaces of the variable reflection modules of the sail. It becomes essential to know beforehand the characteristics of the satellite's movement to compensate for the gyroscopic effect. An anticipated study of the sail deployment will determine the sufficient intensity of the couples to compensate for these effects and to maintain the sail in rotation. This study will be conducted through the implementation of an analog modeling of sail deployment, which will be relevant in understanding sail deployment. It will allow to estimate the satellite's speed and the surfaces of the reflecting modules, elements conducive to the optimal maneuverability of Payankeu.