This paper presents a new type of orbit insertion by combining ballistic capture and aerocapture for a spacecraft with capsule configurations. The spacecraft starts from a very distant region from the target body, follows a ballistic capture trajectory by using multi-body dynamics, attains certain periapsis conditions, and performs a single or multiple aerocapture maneuvers for a low orbit around the target. Ballistic capture transfers are constructed by a straightforward algorithm, i.e., manipulating two sets of initial conditions. Aerocapture is utilized to further decelerate the spacecraft. By controlling the aerodynamic lift and drag forces, post-exit targeting conditions are achieved. Aerocapture trim maneuvers are imparted, if necessary, at the apoapsis to aim the next periapsis conditions when at least two aerocapture passes are required. A semi-analytical prediction algorithm is used to estimate the atmospheric diving conditions with a prescribed aerocapture times. A testing case around Mars has proved a substantial mass saving from that of a conventional Hohmann transfer with moderate flight time and flexible insertion period.