Design of a rapid transit to Mars mission using laser-thermal propulsion

TL;DR

This paper proposes a laser-thermal propulsion system using a large Earth-based laser array for rapid Mars transit, offering high thrust and specific impulse without nuclear reactors, and details the design, aerocapture, and mission architecture.

Contribution

It introduces a novel laser-thermal propulsion concept with a 10-meter laser array enabling rapid Mars transit, including detailed design and mission analysis.

Findings

Achieves specific impulses of 3000 s with laser-thermal propulsion.

Enables rapid Mars transit in approximately 45 days.

Offers a reusable propulsion architecture with high thrust and efficiency.

Abstract

The application of directed energy to spacecraft mission design is explored using rapid transit to Mars as the design objective. An Earth-based laser array of unprecedented size (10~m diameter) and power (100~MW) is assumed to be enabled by ongoing developments in photonic laser technology. A phased-array laser of this size and incorporating atmospheric compensation would be able to deliver laser power to spacecraft in cislunar space, where the incident laser is focused into a hydrogen heating chamber via an inflatable reflector. The hydrogen propellant is then exhausted through a nozzle to realize specific impulses of 3000 s. The architecture is shown to be immediately reusable via a burn-back maneuver to return the propulsion unit while still within range of the Earth-based laser. The ability to tolerate much greater laser fluxes enables realizing the combination of high thrust and high specific impulse, making this approach favorable in comparison to laser-electric propulsion and occupying a parameter space similar to gas-core nuclear thermal rockets (without the requisite reactor). The heating chamber and its associated regenerative cooling and propellant handling systems are crucial elements of the design that receive special attention in this study. The astrodynamics and the extreme aerocapture maneuver required at Mars arrival after a 45-day transit are also analyzed in detail. The application of laser-thermal propulsion as an enabling technology for other rapid transit missions in the solar system and beyond is discussed.