Launch Azimuth
Kourou is located approximately 500 kilometres (310 mi) north of the equator, at a latitude of 5°10'. Ariane 5 GTO launch azimuth 80 degrees from north. Is the launch azimuth designed to clear the coast (running NW-SE) for safety reasons? The inclination of the GTO orbit is 0.5°
Since launch loop will throw payloads directly into transfer orbits, launch azimuth should be arranged to put the equatorial plane crossing near apogee as far from earth as possible. For logistical convenience and safety, the launch loop west station should be south of the intertropical convergence zone (ITC) in January, and the whole system should be erected when the rain and wind is minimized. A loop with a 2000 kilometer track and 300 kilometer inclines will be 23 degrees west to east.
What is the optimum azimuth for injection into a geostationary circular equatorial orbit (42164 km radius), or into a server sky M288 circular equatorial orbit (12789 km radius)?
Equatorial Launch, Two Impulse Hohmann
If we launch from the equator, latitude \phi , the best trajectory is a two impulse Hohmann, with the Launch Loop providing launch velocity v_L at an altitude a_L , radius r_L= R_e + a_L . Start with an azimuth angle ( launch angle deflection to the north) of \alpha = 0 and zero elevation angle, parallel to the earth's surface (or close to parallel).
Ignoring second order effects, the launch vehicle will follow an elliptical transfer orbit to an apogee at the destination orbit, and require one velocity change \Delta v_d to enter the destination orbit. We want to minimize \Delta v_d , because that scales the size of the rocket engine needed at apogee.
A Newtonian orbit with a perigee of r_L and an apogee of r_d has a semimajor axis r_s = 0.5 ( r_d + r_L ) and an eccentricity e = ( r_d - r_L ) / ( r_d+ r_L) . Let \theta be the angle from perigee; the elliptical equatorial transfer orbit will intersect the destination orbit where \theta = \pi . The orbit radius is r = r_L / (1 + e \cos( \theta ) ) . The orbit's characteristic velocity \large v_0 = \sqrt{ { \mu \over 2 } \left( { 1 \over r_L } + { 1 \over r_d } \right) } . Earth's standard gravitational parameter \mu = 3.9860044e14 m³/s². The velocity as a function of angle is v = v_0 ( 1 + e \cos{ \theta } ) , so perigee velocity (or absolute launch velocity) v_L = v_0 ( 1 + e ) and apogee velocity v_a = v_0 ( 1 - e ) . The perigee velocity is the exit velocity relative to the loop vector-summed with the Earth rotation velocity at the exit latitude, 7.292115e-5 radians/sec \times r_L \cos( \phi ) . For a loop exit altitude of 120 km, and an exit latitude of 5 degrees south, r_L = 6498 km and the rotation velocity at that altitude is 472 m/s.
This will get a drawing later.
x is the direction of the perigee at the equator, pointing out of the page, in the equatorial plane.
y is the direction 90 degrees east of perigee orthogonal to x, pointing right on the page, in the equatorial plane.
z is north, pointing up on the page, orthogonal to x and y,and the equatorial plane.
The planar equatorial orbit has a direction vector of:
\left[\matrix{ r_x \\ r_y \\ r_z }\right] ~ = ~ \left[\matrix{ \cos( \theta ) \\ \sin( \theta ) \\ 0 }\right] { r_L \over { 1 + e \cos( \theta ) } }
\left[\matrix{a^2-b^2& -1\\ 1& 2ab}\right]