[2] Since the second stage does not have the possibility of re-activation to form the final orbit of the spacecraft being launched, it includes a detachable orbital launch unit "AM" (aggregate module) operating on high-boiling fuel dinitrogen tetroxide + UDMH "heptyl".

[7][8] In the configuration of the first stage of "Angara-1.2", the URM-1 additionally includes: a block of controllable gas nozzles operating on gas extracted after the RD-191 turbopump engine unit; aerodynamic rudders for roll control; an intermediate compartment for connection to the second stage.

[9] In the first test launch, Angara-1.2PP used a non-standard rocket configuration, with the URM-2 unit of the Angara-A5 carrier with a diameter of 3.6 m as the second stage and without an aggregate module.

[13] To form the target orbit of the spacecraft on the Angara-1.2 a detachable aggregate module (upper stage) is used, operating on a high-boiling fuel pair dinitrogen tetroxide + UDMH or its foreign equivalent MON+MMH.

The aggregate module is equipped with low-thrust engines developed at NIIMash (Sverdlovsk region)[14] — four 11D458 with a thrust of 40 kgf (390 N; 88 lbf) and fourteen orientation and stabilization engines 17D58E with a thrust of 1.3 kgf (13 N; 2.9 lbf) each.