A heavy version of the Ariane launcher is hypothesized for a manned mission to Mars. This enhanced Ariane has 100 mt LEO capability and 36 mt capability for transMars injection (V∞=3.5km/s). In order to simplify the scenario and minimize the costs, it is proposed a pre-deploy semi-direct architecture with several rather small spaceships, 3astronauts and an aerocapture maneuver for Mars orbit insertion. There are several advantages: First, as the payload to the Mars surface is split into equal parts, the same landing space vehicle can be used with mass and size compatible with the payload capability of the launcher. Second, the choice of relatively small landers allows the use of simple deployable rigid heatshields, which could be used both for aerocapture and entry, descent and landing. The use of small landers also reduces the complexity of the tests for the qualification of the descent and landing systems and procedures, which is a critical aspect of the preparation phase. 5 launches are required in this architecture.