The future manned exploration of Mars will require the landing of very large payloads on Mars. This paper presents the technical design and mission architecture of Argo Nova, a spacecraft capable of landing 10 tonnes on the surface of Mars, while staying within human-rated acceleration limits. A trajectory feasibility analysis is performed to select the most efficient strategy for reaching Low Mars Orbit. The technical design focuses on the entry, descent and landing phase and proposes a 2-stage structural design combined with an asymmetric Hypersonic Inflatable Aerodynamic Decelerator (HIAD). A subsytem level design is presented for each critical system of the lander. To assess the feasibility and performance of the overall design, an aerodynamic analysis of the spacecraft during descent is performed. Based on this, the descent profile is optimized in terms of duration, maximum loads and fuel requirements.