Angara-1.2

The design of the Angara-1.2 launch vehicle
Function	Small-lift launch vehicle
Manufacturer	Khrunichev
Country of origin	Russia
Size
Height	42.2 m (138 ft)
Diameter	2.9 m (9 ft 6 in)
Mass	~171.5 t (378,000 lb)[1]
Stages	2
Capacity
Payload toLEO
Altitude	200 km (120 mi)
Mass	3,500 kg (7,700 lb)[1]
Payload toSSO
Mass	2,400 kg (5,300 lb)
Payload toLEO
Altitude	1,500 km (930 mi)
Mass	1,600 kg (3,500 lb)
Associated rockets
Family	Angara
Launch history
Status	Active
Launch sites	Plesetsk,Site 35
Total launches	5
Success(es)	5
First flight	9 July 2014
Last flight	21 August 2025(most recent)
First stage –URM-1
Powered by	1 ×RD-191
Maximum thrust	1,920 kN (430,000 lbf)
Specific impulse	310.7 s (3.047 km/s)
Burn time	214 seconds
Propellant	LOX /RP-1
Second stage –URM-2
Powered by	1 ×RD-0124A
Maximum thrust	294.3 kN (66,200 lbf)
Specific impulse	359 s (3.52 km/s)
Burn time	424 seconds
Propellant	LOX /RP-1
[edit on Wikidata]

Angara-1.2 is a Russian two-stagesmall-lift launch vehicle designed to launch a payload of up to 3.5 t (7,700 lb) intolow Earth orbit and up to 2.4 t (5,300 lb) into asun-synchronous orbit. The height of the Angara-1.2 is about 41.5 m (136 ft), the launch mass of the rocket is about 171.5 t (378,000 lb). It is part of theAngara family of launch vehicles.

The Angara-1.2 rocket has two stages running oncryogenic fuel, the fuel is kerosene of the RG-1 naphthyl brand, and the oxidizer is liquid oxygen.^[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 fueldinitrogen tetroxide + UDMH "heptyl".^[3][4]

The first stage of the Angara-1.2 is auniversal rocket module, similar to those used on the first and second stages of theAngara-A5 heavy carrier.^[5] The module is a complete structure consisting of oxidizer and fuel tanks and an engine compartment, has a diameter of 2.9 m and a length of 25.1 m.^[6] The URM-1 is equipped with a closed-circuit liquid rocket engineRD-191, created at NPO Energomash based on theRD-170 engine used on the first stages ofZenit andEnergia launch vehicles and working on a kerosene-oxygen fuel pair.^[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; anintermediate 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 theAngara-A5 carrier with a diameter of 3.6 m as the second stage and without an aggregate module. The flight followed asuborbital trajectory with an inseparable payload layout.^[9]

In the standard configuration, the second stage of the Angara-1.2 differs from the URM-2 module,^[10] it carries a smaller fuel reserve and has the same diameter as the URM-1 — 2.9 m. Like the URM-2 module for Angara-A5, the second stage of Angara-1.2 runs on an oxygen-kerosene fuel pair and uses theRD-0124Aclosed cycle engine created at KBHA based on the RD-0124 engine used on theSoyuz-2 launch vehicles and having a record value ofspecific impulse for "kerolox" engines.^[11][12] The RD-0124A engine has a number of design differences from the RD-0124 and an extended operating time.^[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 pairdinitrogen tetroxide +UDMH or its western name equivalentMON+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 fourteenorientation and stabilization engines 17D58E with a thrust of 1.3 kgf (13 N; 2.9 lbf) each.^[3]

Thepayload fairing of the Angara-1.2 consists of two flaps, its shell has a three-layer cellular structure. An aggregate module, a payload adapter and a spacecraft are placed under the fairing. The fairing has a diameter of 2.9 meters and a total length of 9.2 m. A total volume of about 25 m³ can be used to place the payload under the fairing.

Launches of launch vehicles of the Angara family are carried out from Site 35 of thePlesetsk Cosmodrome. It is planned to create a launch complex at theVostochny Cosmodrome.^[6]

The Angara family rockets are manufactured by thePolyot production association, the Omsk branch of theKhrunichev, the parent company is engaged in the production of the aggregate module for Angara-1.2. Serial production of the Angara family of rockets was planned to begin in 2023,^[15] and in September 2022 it was announced that the start of serial production would be postponed to 2024.^[16]

Launches of the Angara 1.2 launch vehicle are carried out from the Site 35 at the Plesetsk Cosmodrome. The first flight of the Angara-1.2 launch vehicle in its standard configuration took place on April 29, 2022.^[17]

As of July 2025^[update], in total, 4 rocket launches were carried out in the Angara-1.2 modification, all of them were successful.

• Angara-1.2pp – Russian rocket mission
• Angara A5 – Russian heavy-lift launch vehicle
• Naro-1 – South Korea's first carrier rocket, used from 2009 to 2013

• Space launch vehicles of Russia
• Expendable space launch systems

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