# Raising Perigee

Vehicles leave the launch loop in an elliptical orbit with a perigee at 80 km loop altitude, a radius of 8458 km near the equator. The launch loop is very efficient and not constrained by the exponential Tsiolkovsky rocket mass multiplier, so launches to high apogee orbits cost less than double the cost to LEO apogees, and both are surprisingly inexpensive. Given an kinetic energy cost of \$200/MWHr (perhaps \$150/MWHr scaled by efficiency), the launch cost to a low MEO orbit (10 orbits per sidereal day) is \$1.85/kg (!), and to a 10 sidereal day HEO orbit is \$3.09/kg.

The far greater cost is apogee insertion; that requires either a capture system or an apogee insertion rocket. The delta V for the MEO orbit above is 439 m/s and for the HEO orbit is 25 m/s --- 17 times cheaper! High orbits are "closer" from a launch loop.

A one sidereal day construction orbit may be optimum for most missions; it "returns" to a perigee over the launch loop once per sidereal day; launches and returns can occur daily. Actually, not quite; the orbit "returns" about 4 minutes earlier per day, and "resyncronizes" to the solar day once per year. Solar days seem more natural because our lives are scheduled by the Sun, not the stars. Spacefarers will march to a slightly different drummer.

Here's a table of perigee delta V's for different destination orbits. I've chosen a perigee at 2000 km to avoid LEO debris and collisions; if perigee changes, apogee changes oppositely to keep the same period and semimajor axis.

 orbit apogee launch period radius delta cost sid. days km V m/s \$/kg 0.10 9790 439 1.85 0.20 20462 307 2.36 0.25 25088 270 2.47 0.33 32163 227 2.60 0.50 44746 177 2.73 1.00 75950 114 2.89 construction orbit 2.00 125486 73 2.98 3.00 167032 56 3.02 4.00 204116 46 3.04 5.00 238200 40 3.06 6.00 270068 35 3.07 8.00 328935 29 3.08 9.11 359385 27 3.09 moon/3 10.00 383039 25 3.09 13.66 473527 21 3.10 moon/2 27.32 756599 13 3.12 moon

RaisingPerigee (last edited 2018-10-05 05:15:28 by KeithLofstrom)