Optimal Trajectory Synthesis for Spacecraft Asteroid Rendezvous

Several researchers are considering the plausibility of being able to rapidly launch a mission an asteroid, which would fly in close proximity asteroid deliver impulse particular direction so as deflect from its current orbit. Planetary motion, general, and motion asteroids, particular, subject planetary influences that characterised by kind natural symmetry, results orbiting stable periodic or almost orbit exhibiting number orbital symmetries. Tracking following proximity, is this paper. In paper, problem synthesizing optimal trajectory NEO such considered. A strategy involving optimization co-planar segment permits satellite approach alongside chosen. Two different state space representations Hill–Clohessy–Wiltshire (HCW) linearized equations relative used obtain trajectories for spacecraft approaching asteroid. It shown using representation HCW where secular states explicitly represented, not only synthesized but also result lower magnitudes control inputs must be applied continuously over extended periods time. Thus, solutions obtained particularly suitable low thrust satellites can realized electric thrusters.