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System Engineering a Solar Thermal Propulsion Mission Concept for Rapid Interstellar Medium Access

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A Correction to this article was published on 27 August 2021

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Abstract

The interstellar medium (ISM) represents the next frontier in space exploration, with many new discoveries to be made. The challenge, being so far away from Earth, the ISM requires many decades to reach. To advance our knowledge of what exists beyond our solar system, new approaches for rapid access are required. One such approach is solar thermal propulsion (STP). The approach uses several Venus and Earth gravity assists to fly to Jupiter and use its gravity well to dive towards the Sun. Approaching within three solar radii a perihelion burn would be performed, maximising the spacecraft’s ΔV to achieve high solar system escape velocities. A unique aspect of the STP mission concept is that the Sun is used not only as a gravity well for an Oberth manoeuvre, but also to heat the fuel to ultra-high temperatures (> 3000 K), enabling a monopropellant burn with high specific impulse (Isp). Prior preliminary studies indicated escape velocities of over 20 astronomical unit (AU)/year would be possible. An in-depth modelling exercise was undertaken to determine how such a system would perform. The model in this paper showed the current STP design is capable of providing just under 9 ± 1 AU/year, but there are many technology developments that could increase escape velocity. The technologies vary from items that could be implemented in the near term, like turbo-pumps driven by the hydrogen, to items requiring more extensive development programs like thin coatings which do not erode in superheated hydrogen. After reviewing the STP approach, and comparing it to a solid rocket motor (SRM), it was found that with currently available technology, SRM outperforms STP with an escape velocity of approximately 10–12 AU/year. However, future advances in heat exchanger lining materials, turbo pumps, and advanced heat exchanger geometries may enable solar thermal propulsion to provide higher escape velocities, providing one of the fastest ways to exit the solar system. Ultimately, if all technology paths could be implemented with minimal side effects, the performance in a best-case scenario could reach up to 16 AU/year.

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Abbreviations

AU:

Astronomical Unit

ACS:

Attitude control system

C/C:

Carbon–carbon

DOD:

Depth of discharge

DSM:

Deep space maneuver

IMLI:

Integrated multi-layer insulation

ISM:

Interstellar medium

ISMP:

Interstellar medium probe

I sp :

Specific impulse

KBO:

Kuiper belt object

RVC:

Reticulated vitreous carbon

RTG:

Radioisotope thermoelectric generator

SOFI:

Spray-on foam insulation

SRM:

Solid rocket motor

STP:

Solar thermal propulsion

TVC:

Thrust vector control

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Acknowledgements

The authors would like to thank Thomas Peev, Kevin Anderson, and Jaymee Panian who contributed to the models and calculations summarised here. This research was carried out at the Jet Propulsion Laboratory, California Institute of Technology under a contract with the National Aeronautics and Space Administration (80NM0018D0004). The information presented about the STP mission concept is pre-decisional and is provided for planning and discussion purposes only.

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Authors and Affiliations

  1. Jet Propulsion Laboratory, California Institute of Technology, 4800 Oak Grove Dr., Pasadena, CA, USA

    Jonathan Sauder, Michael Preudhomme, Juergen Mueller, Dean Cheikh, Eric Sunada, Reza R. Karimi, Abigail Couto & Jacqueline Rapinchuk

  2. Blue Origin, 21218 76th Avenue S, Kent, WA, USA

    Nitin Arora

  3. Mandala Space Ventures, 41 South Chester Avenue, Pasadena, CA, 91106, USA

    Leon Alkalai

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  1. Jonathan Sauder
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Correspondence to Jonathan Sauder.

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Sauder, J., Preudhomme, M., Mueller, J. et al. System Engineering a Solar Thermal Propulsion Mission Concept for Rapid Interstellar Medium Access. Adv. Astronaut. Sci. Technol. 4, 77–90 (2021). https://doi.org/10.1007/s42423-021-00077-2

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