I achieved a reasonable representation of the solar power infrastructure. Doing the math, I came to the conclusion that:

1. Precession of close orbits around the Sun is not possible.

2. Forced precession of a stable polar orbit around the Sun would require a solar sail made of optical material, bending light rather than reflecting it, and having an average of about 0.5 kg per square meter to work. I decided this would be too difficult, so I went with a constellation of Fresnel lenses in stable equatorial solar orbits without any propulsion.

3. I decided to place an intermediate relay lens at the L1 lagrange point. This would provide control over the beam with just a 10-second time-lag, versus a 16-minute time lag. It would also have greater targeting precision, and able to target multiple receivers orbiting Earth.

4. I've included two applications for solar power, the traditional SPS-type application where energy is beamed to Earth, and my own Orbital Skyhook launch system where energy is used to support a high-frequency launch schedule using a rotating tether.

5. Forced precession of a geosynchronous orbit about the polar axis is impossible. Power interruptions are accepted in my design, and detailed in the draft.

6. I still have to re-work my ARMXER system, including a plan for a geometrically increasing, or at least self-sustaining launch schedule - to get all that equipment up there. I also have yet to integrate the ARMXER with ground-based aviation infrastructure, given a precessing orbit, and set performance limits on rendezvous aircraft. As such I don't go into much detail about the Orbital Skyhook yet. Just the energy supply.

ARMXER Orbital Skyhook Infrastructure