The Lagrange 1 and Lagrange 2 regions are the hubs of the trajectories that Ross, Lo, Martin, and Belbruno advocate. Szebehely developed equations to find the L1 and L2 regions. Using his equations I made a L1 and L2 spreadsheet.
Of interest is the 3 body mass parameter, usually denoted $\mu$.
$\mu=mass_{orbiting body}/(mass_{orbiting body} + mass_{central body})$
As central and orbiting bodies go, the Earth Moon system has a hefty $\mu$. But Pluto and Charon is even larger.
Pluto/Charon 1.043E-01
Earth/Moon 1.216E-02
Sun/Jupiter 9.545E-04
Sun/Saturn 2.856E-04
Saturn/Titan 2.374E-04
Jupiter/Ganymede 7.789E-05
Jupiter/Callisto 5.684E-05
Sun/Neptune 5.153E-05
Jupiter/Io 4.700E-05
Sun/Uranus 4.366E-05
Jupiter/Europa 2.526E-05
Saturn/Rhea 4.046E-06
Sun/Earth 3.039E-06
Sun/Venus 2.448E-06
Saturn/Dione 1.935E-06
Saturn/Tethys 1.091E-06
Sun/Mars 3.229E-07
Saturn/Enceladus 1.935E-07
Sun/Mercury 1.659E-07
Saturn/Mimas 7.037E-08
Mars/Phobos 1.682E-08
Sun/Pluto& Charon 7.149E-09
Mars/Deimos 2.803E-09
Sun/Ceres 4.741E-10
Big $\mu$'s make for a very interesting set of trajectories emanating from the L1 and L2 necks. Something nudged outward from the EML2 would fly to a 1.7 million kilometer apogee in a simple earth moon system. And the Sun Earth L1 and L2 is only 1.5 million kilometers from Earth. Here's a variety of trajectories from EML2:
As you can see some pellets find their way to near Earth perigees and others are thrown into heliocentric orbits outside of Earth's sphere of influence.
Above a ship is launched at a certain phase of the moon, set by inputing Barycentric Longitude of Sun. As it passes by the moon, a lunar assist raises apogee. At apogee the sun's tidal influence raises perigee allowing a ballistic slide to EML2. LEO to EML2 is accomplished with 3.1 km/s.
This is somewhat like the path Belbruno used to save the Hiten Mission. Note that Hiten had already achieved a 290,000 km apogee. 3.1 km/s had already been invested when Belbruno stepped in.
Is 3.1 km/s from LEO to a loosely bound lunar orbit ground breaking and revolutionary? No. Farquhar's route from LEO to EML2 takes only 3.4 km/s. And Farquhar's route is about 8 days whereas the the trips out to the edge of Earth's Hill Sphere and back take months. A .3 km/s savings is nice but not a major game changer in my opinion.
When it comes to the sun and rocky planets of the inner solar system, the 3 body mass parameter is miniscule. The trajectories from the Sun Earth L1 and L2 regions are much less varied and dramatic thatn the paths from EML1 and EML2.
Above are the heliocentric orbits payloads would follow if nudged from the Sun Earth L1 and L2. These orbits have a semi-major axis little different from Earth's. That means the synodic period is quite large, about 20 years for the payload nudged from SEL2. And when the payload finally gets lapped by the Earth 20 years later, it's about 43º from perihelion. Not being close to Earth, Earth's gravity makes no dramatic changes to the payload path.
The payload released from SEL2 would not come back to a near Earth neighborhood until 160 years later.
I did a blog post Pot Holes On the Interplanetary Super Highway. Shane Ross, one of the architects of the ITN, left a comment:
Hollister, yes, the superhighway definitely has its limitations. It
was inspired by comets, which have plenty of time, but of course we
don't for planning space missions (unless we take Deep Time approach).
I suspect that gravitational corridors which naturally connect
Earth-bound orbits with Mars-bound orbits using no-fuel do exist, but
might take a long time to achieve (I'm thinking thousands of years of
flight time between the two planets). But using some propulsion, we
may be able to reduce that time to several decades. This is probably
still too much time for a mission, especially a manned mission, so for
now, conventional approaches will probably continue to be used.
It would be an interesting study to try to map out the Earth-Mars
natural connections. It would have to involve the concept of multiple
gravity assists, or consecutive gravity assists, as discussed in
http://www2.esm.vt.edu/~sdross/talks/DS07_2007_Keplerian_Map_Talk.pdf
http://www2.esm.vt.edu/~sdross/papers/multiple_gravity_assists.pdf
Shane Ross, 'evangelist' :)
Belbruno and Toppotu have found a path using some propulsion. It entails a 2 km/s aphelion burn to slide into a ballistic path into Mars capture. But a .7 km/s burn at a near Mars periapsis will also capture a payload into a loosely bound Mars orbit. So it is actualy 1.3 km/s more expensive than a straightforward Hohmann orbit.
These pathways are interesting when it comes to systems with a large $\mu$. That includes the Earth and moon, gas giants and their larger moons, as well as the sun and gas giants.
However it is not much use for departing Earth for other regions of the solar system. Departing from Earth, it's helpful to reach different parts of the Earth Moon neighborhood including SEL1 and SEL2, but that's about it.
As you might guess, I was once a huge fan of the possibilities of ITN. I've invested some time and effort studying it hoping to find just the sort of map you're asking for. I have pretty much discarded that hope.
