#	Burn time	DV	Dt	a
M1P	2018-12-03 17:00:00.000	228.3	28.887	7.90
M2P	2018-12-05 17:00:00.000	396.4	49.951	7.94
M3P	2018-12-07 17:00:00.000	396.5	49.943	7.94
M4P	2018-12-09 17:00:00.000	206.0	26.106	7.89
M5P	2018-12-11 17:00:00.000	203.8	25.842	7.89
M6P	2018-12-13 17:00:00.000	204.8	25.957	7.89
M7P	2018-12-15 17:00:00.000	197.6	25.015	7.90

The table shows the spacecraft maneuvers executed during this phase.

Official website page: NASA'S OSIRIS-REx Spacecraft Arrives at Asteroid Bennu

The graph shows the arrival trajectory of the spacecraft and the first overflight of the Bennu north pole after the M1P maneuver in the Bennu-centric mean ecliptic and equinox of J2000 reference frame.
The popup label shows the date, the radius vector (km) and the spacecraft speed (mm/s).

Since Bennu rotation is retrograde and its pole orientation is nearly perpendicular to the ecliptic plane (see: The Design Reference Asteroid for the OSIRIS-REx Mission Target (101955) Bennu, page 24), the north pole is towards the -Z axis direction.

Before reaching Bennu, two small corrective maneuvers were performed:

Burn time	DV	Dt	a
2018-11-30 16:45:29.000	10.7	1.611	6.66
2018-11-30 17:14:31.000	10.9	1.617	6.76

Here's the spacecraft trajectory during this phase in the Bennu-centric mean ecliptic and equinox of J2000 reference frame.

The Bennu Sun-North reference frame is better suited to highlight the particular geometry of the passes.

In this non-inertial reference frame, the s/c speed (shown by the popup label) is slightly different from the one shown in the previous graph (whose reference frame is inertial).