An analysis on rockets for interstellar travel

Hi all,

I had posted this originally in the homework help section, but the assignment is completed and submitted, so no longer relevant. I thought some might find it interesting.

The crux of the article revolves around a hypothetical 5,000 metric ton (dry mass) spacecraft, and examines propellant requirements vs exhaust velocity, the power requirements to achieve the requisite amount of thrust for an interstellar journey in one lifetime, the technology requirements to achieve that power output, and the thermal control system that would be required for any resultant waste heat. 

Article is aimed at the "average" reader interested in the topic, so I aimed to make it as easy to understand as is feasible. 

Comments and critiques welcome.

Rockets For Manned Interstellar Travel.pdf