SAMA

Main Goals of the Project

Within the context of the Terra Novae 2030+ Exploration Strategy, ESA is evaluating the possibility of conducting a mission to Mars by the late 2020s, aimed at demonstrating discrete-event drag modulation aerocapture. This technique simplifies orbit insertion by jettisoning part of the aeroshell during atmospheric entry, thereby reducing drag and varying the ballistic coefficient. This mission serves to demonstrate key aspects such as the successful orbit insertion of an aerocapture module and the adequate design for the aeroshell and TPS (Thermal Protection System) in the case of an aerocapture maneuver. This would allow for the scaling up of this type of technology for larger missions.

Two architectures have been studied: a standalone mission and a piggyback option. The standalone mission envisions a dedicated launch and the use of a large-diameter deployable heat shield, a requirement for future large-scale applications of this technology. The piggyback mission, on the other hand, involves the demonstrator being hosted on another Mars-bound spacecraft and released prior to orbit insertion. Current activity aims to design, manufacture, and test this separable aeroshell system, composed of a Nose and a Drag Ring, at a breadboard level, aiming to reach TRL 4 through functional laboratory verification of the separation mechanisms subjected to aerodynamic loads representative of flight.

CIRA Activities in the Project

Within the scope of the project, CIRA plays a central role both in defining the Thermal Protection System (TPS) for the Flight Model and in the comprehensive development of the breadboard, ranging from design to experimental verification.

Regarding the flight vehicle, CIRA has consolidated the thermo-structural sizing of the TPS (Nose and Drag Ring sections) through numerical analyses based on aerothermodynamic loads derived from trajectories calculated by TAS-I, the project's Prime Contractor, to which CIRA acts as a subcontractor. Current activities focus on finalizing the design and subsequent manufacturing of the breadboard. This unit is designed to ensure full representativeness of the flight system in terms of mechanical interfaces, mass distribution, moments of inertia, and Center of Gravity (CoG) position.

In parallel, the experimental setup is being defined. CIRA is responsible for developing the dedicated facility for testing the separation mechanisms. This facility is designed to accurately replicate critical operating conditions, specifically the application of representative aerodynamic forces and the imposition of rotational motion on the breadboard, which are prerequisites for triggering the separation between the Nose and the Drag Ring.

General Project Information

Funding Programme: ESA

Start Date: 03/01/2025; End Date: 06/07/2025

Coordinating Organization: ESA

Partners: Thales Alenia Space Italia, CIRA, Sener

CIRA Contact: Giuseppe Maria Infante, g.infante@cira.it