An efficient orbit to fly a space craft from the L1 lagrange point to mars sun-synchronous orbit?

Hello there everyone,


I joined this competition callled The International Space Settlement
Design Competition organized by Nasa. In the request for proposal of
the
competition that is given to me and my team, they require us to design
a space settlement qthat will be the habitat of 14 000 people orbiting
around Mars.

so can anyone tell me an efficient orbit to fly a space craft from the
L1 lagrange point to mars sun-synchronous orbit?

Thank you.

kelvin wrote:
Hello there everyone,


I joined this competition callled The International Space Settlement
Design Competition organized by Nasa. In the request for proposal of
the
competition that is given to me and my team, they require us to design
a space settlement qthat will be the habitat of 14 000 people orbiting
around Mars.

so can anyone tell me an efficient orbit to fly a space craft from the
L1 lagrange point to mars sun-synchronous orbit?

Hohmann transfer orbit.
Is probably a good term to google on.
Efficient orbit is pretty much irrelevant - you may be able to shave off
a few percent over the simple transfer orbit, but not much more.
Also look up aerobraking.
But, this is far, far above the state of the art in aerobraking.
You've also got to consider if it's being built from martian materials,
or if you're shipping it in one block from the earth or lunar manufacture.

At the moment it's a meaningless question - you've got to predicate
it on some existing space infrastructure.

http://www.cds.caltech.edu/~shane/pa..._ross_2001.pdf