Robust, affordable, semi-direct Mars mission

Abstract

A new architecture is proposed for the first manned Mars mission, based on current NASA developments (SLS and Orion), chemical propulsion for interplanetary transit, aerocapture for all vehicles, a split strategy, and a long stay on the surface. Two important choices make this architecture affordable and appropriate for the first mission. The first is splitting the Earth return vehicle into two parts that are launched separately and dock in Mars orbit. This is necessary to make aerocapture feasible and efficient, which considerably reduces mass. The second is reducing the crew to 3 astronauts. This simplifies the mission and reduces the SLS payload mass under the 45-metric ton limit for a direct TMI (trans-Mars injection) burn without LEO assembly. Only 4 SLS launches are required. The first takes the Mars ascent vehicle and in situ resource utilization systems to the planet's surface. The second takes the first part of the Earth return vehicle, the habitat, into Mars orbit. Two years later, two further SLS launches take a dual-use habitat (outbound trip and surface), Orion, and an enhanced service module to LEO, and then into Mars orbit, followed by the landing of the habitat on the surface. Transit time is demonstrated to be easily reduced to less than 6 months, with relatively low impact on propellant mass and none at all on the architecture.

Preliminary study of rescue systems for Mars landing

“…Other resources should be available, such as a habitable module to make sure that the astronauts can reach a safe haven. In most Mars mission architectures, such a habitable module is indeed pre-positioned on Mars before the astronauts' arrival [13][14][15][16]. In nominal conditions, there is an accurate control of the descent and the landing ellipse is of the order of 10 kilometres large at the end of the aerodynamic braking [17].…”

“…Instead of a satellite, another space vehicle can be used. Remarkably, an areosynchronous orbit is proposed for the Earth return vehicle of several Mars mission architectures [12,15]. This space vehicle cannot be used for accurate measurements as it would be too far from the planet.…”

Analytical Predictive Guidance Algorithm Based on Single Ballistic Coefficient Switching for Mars Aerocapture

“…It can significantly reduce the velocity increment required for a planetary orbital mission and reduce the amount of propellant needed. It is one of the promising technologies for large-scale space exploration missions in the future, such as a manned Mars exploration mission [1][2][3][4].…”

Analytical Predictor-Corrector Guidance Algorithm Based on Drag Modulation Flight Control System for Mars Aerocapture

“…Therefore, it is one of the problems on how to save the propellant and enter the target orbit quickly and accurately. Aerocapture is an effective way to solve the problem above [1][2][3]. The fundamental principle of aerocapture is to reduce the velocity by utilizing the aerodynamic drag effectively when crossing the planet's atmosphere, and only a small amount of propellant is needed for achieving the target orbit.…”