Extending the Patched-Conic Approximation to the Restricted Four-Body Problem

摘要: This paper presents an investigation of how to refine patched-conic orbit approximations with a restricted four-body setup. By approximating overall as series two-body orbits, offer greatly simplified way analyzing missions. However, they are limited in their ability fully represent particular orbit. Therefore, we must use numerical integration technique more precisely describe interplanetary extending the approximation problem, achieve precise transfer description. Taking into consideration gravitational influences sun, Earth, and Mars at all times, compute spacecraft’s from Earth Mars. The integrator provides estimate state vehicle upon its arrival initial conditions adjusted effects measured. Also, values required departure burn compared for Hohmann solution, approximation, problem.