By beaming hundreds of Megawatts to next-generation ion drive it will be 15 times faster
The system could propel a 12-year mission to 500 AU and could send missions to Pluto/Charon in 3.6 years and Jupiter missions in roughly a year.
Over 1000 times more power and over forty times more mission mass
Having megawatts beamed to the mission with lasers enables 80-ton missions to Jupiter versus less than two tons for the Galileo mission. The Galileo mission had less than a kilowatt of power.
The system needs a 2-km diameter aperture with an output power of 400 MW at a laser frequency of 300 nm driving a vehicle with a 110-meter diameter photovoltaic array powering a 10 MW electric propulsion system at a specific impulse of 40,000 s.
In Phase II, they will address the still outstanding technical feasibility issues including:
(1) Demonstrating that photovoltaic (PV) coupons can be operated at more than 6 kV in the plasma environment created by the lithium-ion propulsion system.
(2) Demonstrating PV cell efficiency of 50% or greater for monochromatic inputs.
(3) Modeling the characteristic of the lithium plasma plume created by the ion propulsion system.
(4) Demonstrating operation of a small aperture (0.3 m to 1 m dia.), low power (a few hundred watts) phased array with long a coherence length and beacon feedback that is scalable to large apertures.
(5) Investigation of beacon phase locking for long round-trip light time delays.
(6) Investigating laser location impacts on cross-track thrust.
Phase II work will develop a technology roadmap including technology demonstration missions recommended as stepping stones to get to the final system architecture.
Two kilometer aperture and 400 MW lasers
Both the laser array and the PV arrays are easily extended to larger power levels. The mass per unit power of the laser amplifiers is about 5 kg/kW currently with a strong push to bring this down to 1 kg/kW in the next five years. The solar photovoltaic is about 7 kg/kW but is expected to be improved over the next few years. The radiator panels are the most difficult to scale up, at about 25 kg/kW. This is an area that needs work, though in all simulations for mission masses the assumption is 25 kW (radiated) for the radiator panels.
ATK has to scale their existing 10 meter diameter design to push the PV arrays to 30 meter diameter which will yield about 225 kW per manufactured unit, or 450 kW per pair and still fit in an SLS PF1B 8.4 m diameter fairing. The scaling and deployment of the PV arrays to larger sizes for various launch vehicles is shown below. Even larger sizes into the megawatt range can be anticipated in the future.
In 5-10 years with a SpaceX BFR and some robotic space construction – 2 kilometer apertures should be buildable in orbit
The SpaceX BFR could be flying in about 5 years. This will enable 150-ton payloads and could deliver over a megawatt of solar arrays every launch.
If the solar arrays were assembled in space then the solar arrays could be made lighter since they would not need to be able to withstand the 3-G strain of launch.
The US military will be building hundreds of megawatt and multi-megawatt combat lasers for Navy ships, army and air force systems by the mid-2020s. These systems will provide the technological base and production capacity for the 400 megawatt laser array.