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This paper presents the preliminary design of the descent and landingtrajectory of the ESA Argonaut lunar lander. The mission scenario and drivingsystem constraints are presented and accounted for in the design of afuel-optimal trajectory that includes divert capabilities, as required toachieve a safe landing. A sub-optimal descent and landing trajectory is thenpresented and computed from the optimal one, and the related on-board guidancealgorithms are derived. The proposed end-to-end guidance solution represents aneasily implementable alternative to on-board optimization, minimizing theverification & validation effort, computational footprint, and programmaticrisk in the development of the related GN&C capabilities. A dedicated off-lineoptimization process is also outlined, and exploited to optimize the propellantconsumption of the sub-optimal trajectory and to ensure the fulfillment ofsystem constraints despite the use of simple algorithms on-board. Thesub-optimal trajectory is compared to the optimal baseline, and conclusions aredrawn on the applicability of the proposed approach to the Argonaut mission.

Descent & Landing Trajectory and Guidance Algorithms with Divert Capabilities for Moon Landing