Solution to the geocentric lambert boundary value...

Solution to the geocentric lambert boundary value problem for a complete force field

Abstract

Given values for geocentric spacecraft positions x0 and x1 at times t01 and given realistic acceleration values x(τ), τ ε [t0,t1], calculate the three velocity components of x0 at t0. Accelerations for a realistic force model include those due to a complete geopotential, air drag, solar photon pressure, and luni-solar gravity perturbations. Lancaster-Blanchard-Gooding solutions to the two-body Lambert Problem are used to initialize a solution to the full force model problem.