# Angara-1.2

"Angara-1.2" is a Russian two-stage small-lift launch vehicle designed to launch a payload of up to 3.5 tons into low Earth orbit and up to 2.4 tons into a sun—synchronous orbit. The height of the "Angara-1.2" is about 41.5 m, the launch mass of the rocket is about 171 tons. It is part of the Angara family of launch vehicles.

## Description

The Angara-1.2 rocket has two stages running on cryogenic fuel, the fuel is kerosene of the RG-1 naphthyl brand, and the oxidizer is liquid oxygen. 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".

### First Stage

The first stage of the Angara-1.2 is a universal rocket module, similar to those used on the first and second stages of the Angara-A5 heavy carrier. 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. The URM-1 is equipped with a closed-circuit liquid rocket engine RD-191, created at NPO Energomash based on the RD-170 engine used on the first stages of Zenit and Energia launch vehicles and working on a kerosene-oxygen fuel pair.
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.

### Second Stage

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. The flight followed a suborbital trajectory with an inseparable payload layout.
In the standard configuration, the second stage of the Angara-1.2 differs from the URM-2 module, 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 the RD-0124A closed cycle engine created at KBHA based on the RD-0124 engine used on the Soyuz-2 launch vehicles and having a record value of specific impulse for "kerolox" engines. The RD-0124A engine has a number of design differences from the RD-0124 and an extended operating time.

### Aggregate module

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) — 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.

### Fairing

The payload 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 m$^3$ can be used to place the payload under the fairing.

## Launch sites

Launches of launch vehicles of the Angara family are carried out from Site 35 of the Plesetsk Cosmodrome. It is planned to create a launch complex at the Vostochny Cosmodrome.

## Production

The Angara family rockets are manufactured by the Polyot production association, the Omsk branch of the Khrunichev, 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, and in September 2022 it was announced that the start of serial production would be postponed to 2024.

## Launches

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. In total, 3 rocket launches were carried out in the Angara-1.2 modification, all of them were successful.
| Date/time (UTC) | Date/time (UTC) | Configuration | Serial number | Launch pad | Outcome |
| Date/time (UTC) | Date/time (UTC) | Payload | Separation orbit | Operator | Function |
| Remarks ||||
| 29 April 2022 19:55:22 | 29 April 2022 19:55:22 | Angara-1.2 | 71602 | Plesetsk, Site 35/1 | Failure |
| 29 April 2022 19:55:22 | 29 April 2022 19:55:22 | Kosmos-2555 (EO MKA №2) | SSO | VKS | Reconnaissance |
| Maiden flight of Angara 1.2. No orbit-raising activities were detected from Kosmos-2555 following deployment, indicating a possible spacecraft failure. Re-entered May 18, 2022 after not attempting to raise its orbit. ||||
| 15 October 2022 19:55:15 | 15 October 2022 19:55:15 | Angara-1.2 | 71603 | Plesetsk, Site 35/1 | Success |
| 15 October 2022 19:55:15 | 15 October 2022 19:55:15 | Kosmos-2560 (EO MKA №3) | SSO | VKS | Reconnaissance |
| Kosmos 2560 decayed from orbit 10 Dec 2022 01:54 UTC, also quite soon after launch. Some suspect this was due to spacecraft failure. ||||
| 17 September 2024 07:01:00 | 17 September 2024 07:01:00 | Angara-1.2 | 71604 | Plesetsk, Site 35/1 | Success |
| 17 September 2024 07:01:00 | 17 September 2024 07:01:00 | Kosmos-2577 (OO MKA №1) Kosmos-2578 (OO MKA №2) | SSO | VKS | Reconnaissance |
| 16 March 2025 10:50 | 16 March 2025 10:50 | Angara-1.2 | 71605 | Plesetsk, Site 35/1 | Success |
| 16 March 2025 10:50 | 16 March 2025 10:50 | Kosmos-2585 (Strela-3M №19) Kosmos-2586 (Strela-3M №20) Kosmos-2587 (Strela-3M №21) | LEO | VKS | Communication |
| Future Launches ||||||
| April 2025 | April 2025 | Angara-1.2 | | Plesetsk, Site 35/1 | Planned |
| April 2025 | April 2025 | Kosmos-2588 (OO MKA №3) Kosmos-2589 (OO MKA №4) | SSO | VKS | Reconnaissance |