A novel Mars orbit insertion strategy that combines ballistic capture and aerobraking is presented. Mars ballistic capture orbits that neglect aerodynamics are first generated, which are distilled from properly computed stable and unstable sets by using an already-established method. A small periapsis maneuver is implemented at first close encounter to better submit the post-capture orbit to the aerobraking process. An ad-hoc patching point marks the transition from ballistic capture to aerobraking, from which an exponential model simulating Mars atmosphere and a box-wing satellite configuration is considered. A series of apoapsis trim maneuvers are then computed by targeting a prescribed pericenter dynamic pressure. The aerobraking duration is estimated by using a simplified two-body model. A yaw angle tuning cancels inclination deflections due to out-of-plane perturbation from the Sun. A philosophy combining in-plane and out-of-plane dynamics is proposed to achieve the required semi-major axis and inclination simultaneously. Numerical simulations indicate that the developed method is more efficient in terms of fuel consumption, insertion safety, and flexibility than state-of-the-art insertion strategies.