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Ultrafast transfer of low-mass payloads to Mars and beyond using aerographite solar sails (2308.16698v1)

Published 31 Aug 2023 in astro-ph.IM and astro-ph.EP

Abstract: With interstellar mission concepts now being under study by various space agencies and institutions, a feasible and worthy interstellar precursor mission concept will be key to the success of the long shot. Here we investigate interstellar-bound trajectories of solar sails made of the ultra-light material aerographite, known for its low density (0.18 kg m${-3}$) and high absorptivity ($\mathcal{A}{\sim}1$), enabling remarkable solar irradiation-based acceleration. Payloads of up to 1 kg can swiftly traverse the solar system and the regions beyond. Our simulations consider various launch scenarios from a polar orbit around the Earth with direct outbound trajectories and Sun diver launches with subsequent outward acceleration. Utilizing the poliastro Python library, we calculate positions, velocities, and accelerations for a 1 kg spacecraft (including 720 g aerographite mass) with 10$4$ m$2$ of cross-sectional area, corresponding to a 56 m radius. A direct outward Mars transfer yields 65 km s${-1}$ in 26 d. The inward Mars transfer, with a sail deployment at a minimum distance of 0.6 AU, achieves 118 km s${-1}$ in 126 d. Transfer times and velocities vary due to the Earth-Mars constellation and initial injection trajectory. The direct interstellar trajectory peaks at 109 km s${-1}$, reaching interstellar space in 5.3 yr defined by the heliopause at 120 AU. Alternatively, the initial Sun dive to 0.6 AU provides 148 km s${-1}$ of escape velocity, reaching the heliopause in 4.2 yr. Values differ based on the minimum distance to the Sun. Presented concepts enable swift Mars flybys and interstellar space exploration. For delivery missions of sub-kg payloads, the deceleration remains a challenge.

Citations (2)

Summary

  • The paper demonstrates the use of ultralight aerographite sails to achieve 65 km/s, reducing Mars transit times to 26 days from a polar Earth launch.
  • The study employs poliastro-based simulations showing that a Sun dive maneuver boosts payload speeds to 118 km/s and shortens transit times further.
  • The research explores interstellar prospects, projecting that aerographite sails can reach terminal velocities up to 148 km/s for heliopause missions in under 5.3 years.

Ultrafast Transfer of Low-Mass Payloads to Mars and Beyond Using Aerographite Solar Sails

The paper conducted by Karlapp et al. explores the domain of interstellar precursor mission concepts, focusing on the use of aerographite as a solar sail material for rapid transportation of low-mass payloads within our solar system and beyond. This exploration aims to leverage the ultra-lightweight and highly absorptive properties of aerographite to achieve significant accelerations through solar radiation pressure, proposing a viable strategy for both scientific exploration and the establishment of technology for future interstellar endeavors.

Key Findings and Methodologies

  • Material Utilization: The paper leverages the low density (0.18 kg/m³) and high radiation coupling constant (~1) of aerographite to facilitate rapid acceleration of solar sails. This enables the transport of payloads up to 1 kg with a considerable cross-sectional sail area of 10,000 m² (sail radius of 56 meters).
  • Trajectories and Simulation: Utilizing the poliastro Python library, various trajectories are computed for both outward and inward transfers. The outward scenario involves a direct launch from a polar orbit around Earth, achieving a relative velocity of 65 km/s to Mars in approximately 26 days. An inward trajectory, involving a Sun dive to 0.6 astronomical units (AU) from the Sun before deploying the sail, results in a velocity of 118 km/s relative to Mars, with a travel time of 126 days.
  • Interstellar Prospects: The paper also models trajectories aimed at surpassing the heliopause, the presumed boundary of our solar system, set at 120 AU. A direct outward trajectory achieves a terminal velocity of 109 km/s with a transit time of 5.3 years to interstellar space, while using a Sun dive, the escape velocity reaches 148 km/s, reducing travel time to 4.2 years.

Numerical Results and Implications

The simulations highlight the considerable impact of using aerographite, notably its ability to significantly cut down transfer times to Mars and increase flyby velocities. Such characteristics are critical for time-sensitive missions, providing flexibility and speed that were previously constrained by conventional propulsion systems.

Moreover, the paper highlights the scalability of the aerographite sail concept, suggesting a natural progression from existing solar sail missions like IKAROS, albeit with vastly lighter materials and larger sail areas. This use of highly efficient solar sails could redefine mission architecture for both intra-solar and interstellar missions, offering a near-term pathway to test technologies required for long-term human and robotic exploration endeavors.

Challenges and Future Directions

One of the pivotal challenges identified is the deceleration upon reaching Mars or other celestial targets. Options for addressing this include aerocapture techniques and other innovative deceleration methods, which need further exploration. The paper also encourages further refinement of solar sail design and navigation technologies to better leverage the unique properties of aerographite.

Looking ahead, successful demonstrations of these missions could set the stage for longer-term interstellar travels, making aerographite solar sails an exciting frontier in aerospace material science and space propulsion. While the realization of such missions requires overcoming significant technical hurdles, the foundations laid by this paper underpin a compelling case for developing high-speed, low-mass exploration systems.

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