  In this work, we performed a dynamical analysis of a spacecraft around a
nearly equal-mass binary near-Earth asteroid with application to the asteroid
2017 YE5, which is also a possible dormant Jupiter-family comet. Thus, we
investigated the motion of a particle around this binary system using the
circular restricted three-body problem. We calculated the locations of the
Lagrangian points of the system and their Jacobi constant. Through numerical
simulations, using the Poincar\'e Surface of Sections, it was possible to find
several prograde and retrograde periodic orbits around each binary system's
primary, some exhibiting significantly-sized higher-order behavior. We also
calculated the stability of these orbits. After finding the periodic orbits, we
investigated the influence of solar radiation pressure on these orbits. For
this analysis, we considered that the area-to-mass ratio equals 0.01 and 0.1.
We also performed a spacecraft lifetime analysis considering the physical and
orbital characteristics of the 2017YE5 system and investigated the behavior of
a spacecraft in the vicinity of this system. We analyzed direct and retrograde
orbits for different values of Jacobi's constant. This study investigated
orbits that survive for at least six months, not colliding or escaping the
system during that time. We also analyze the initial conditions that cause the
spacecraft to collide with $M_1$ or $M_2$, or escape from the system. In this
work, we take into account the gravitational forces of the binary asteroid
system and the solar radiation pressure (SRP). Finally, we calculated optimal
bi-impulsive orbital maneuvers between the collinear Lagrangian points. We
found a family of possible orbital transfers considering times of flight
between 0.1 and 1 day.
