SPACE LAUNCH REPORT Soyuz NK-33A (132KC First Stage) Launch Vehicle Flight History by Variant/Year (2013-Present) by Ed Kyle, Last Update 02/09/2024 L(F) = Number of Launches(Number of Failures) Soyuz Soyuz Soyuz Soyuz Soyuz Soyuz Orbital 2-1v 2-1v Totals Volga Year L(F) L(F) L(F) L(F) L(F) L(F) L(F) ------------------------------------------------------------------ 2010 - - - - - - - 2011 - - - - - - - 2012 - - - - - - - 2013 1(0) - - - - - 1(0) 2014 - - - - - - - 2015 1(1) - - - - - 1(1) 2016 - - - - - - - 2017 1(0) - - - - - 1(0) 2018 - 1(0) - - - - 1(0) 2019 2(0) - - - - - 2(0) 2020 - - - - - - - 2021 - 1(0) - - - - 1(0) 2022 2(0) - - - - - 2(0) 2023 - 2(0) - - - - 2(0) 2024 - 1(0) - - - - 1(0) ------------------------------------------------------------------ Soyuz Soyuz Soyuz Soyuz Soyuz Soyuz Orbital 2-1v 2-1v Totals Volga Year L(F) L(F) L(F) L(F) L(F) L(F) L(F) ------------------------------------------------------------------ Subor - - - - - - - Orbit 7(1) 5(0) - - - - 12(1) Total 7(1) 5(0) - - - - 12(1) ------------------------------------------------------------------- Footnotes: SOYUZ 2-1V FAILURE LIST DATE VEHICLE ID PAYLOAD MASS(t) SITE ORBIT ------------------------------------------------------------------ 12/05/15 Soyuz 2-1v/Volga 002 Kanopus ST ~0.440 PL 43/4 [EEO] ------------------------------------------------------------------ [1] Kanopus ST did not separate from Volga after reaching planned LEO/S. Secondary radar calibration sphere did separate. Volga restarted to drop with Kanopus ST to elliptical orbit on December 6. Fell out of orbit after about two days. One of four clamps on Volga failed to open. ------------------------------------------------------------------ Soyuz 2.1v Vehicle Configurations ------------------------------------------------------------------ LEO(S) Configuration Height GLOW (tonnes) (1)200 km x 51.6 deg (3)835 km x 98.7 deg ================================================================== Soyuz 2.1v 2.85 t (1) 2.1v S1 + 2-1b S2 44.0 m 157 t Soyuz 2.1v/ 1.40 t (3) Soy 2.1v + Volga S3 44.0 m 160 t Volga ================================================================== Soyuz 2.1v Vehicle Components ------------------------------------------------------------------ Soyuz-2-1b Soyuz 2-1v Volga PLF Blok I Stage 1 Stage 3 Stage 2 =================================================================== Diameter 2.66 m 2.95 m 2.72-3.2 m Length 6.7 m 1.025 m Mp (tonnes) 22.79/22.83 t 119 t 0.3-0.9 t Total Mass 25.2/25.3 t 1.1-1.7 t Engine RD-0124 NK-33A + RD-0110R steering Engine Mfgr Kuznetsov + KBKhA Thrust (SL) 154+24.35 t Thrust (Vac) 30 t 167+27.86 t 0.3 t ISP (SL) 297/261.1 s ISP (Vac) 359 s 331/298.7 s 307 s Burn Time 270 s 250 s No. Engines 1 (4 chmbr) 1 fixed + 4 chmbr steering Fuel Kerosene Kerosene UDMH Oxidizer LOX LOX N2O4 ================================================================== Soyuz 2.1v Launch History (2013-Present) ------------------------------------------------------------------ DATE VEHICLE ID PAYLOAD MASS(t) SITE ORBIT ------------------------------------------------------------------ 12/28/13 Soyuz 2-1v/Volga 001 Aist 0.2? PL 43/4 LEO 12/05/15 Soyuz 2-1v/Volga 002 Kanopus ST 0.440 PL 43/4 [EEO] 06/23/17 Soyuz 2-1v/Volga 003 Kosmos 2519 PL 43/4 SSO 03/29/18 Soyuz 2-1v 004 Kosmos 2525 0.2 PL 43/4 LEO 07/10/19 Soyuz 2-1v/Volga 005 Kosmos 2535-38 PL 43/4 SSO 11/25/19 Soyuz 2-1v/Volga 006 Kosmos 2542 PL 43/4 SSO 09/09/21 Soyuz 2-1v 007 Kosmos 2551 PL 43/4 SSO 08/01/22 Soyuz 2-1v/Volga 008 Kosmos 2558 PL 43/4 SSO 10/21/22 Soyuz 2.1v/Volga 009 Kosmos 2561/62 PL 43/4 SSO 03/29/23 Soyuz 2.1v 010 Kosmos 2568 PL 43/4 SSO 12/27/23 Soyuz 2.1v 011 Kosmos 2574 PL 43/4 SSO 02/09/24 Soyuz 2.1v 012 Kosmos 2575 PL 43/4 SSO ------------------------------------------------------------------ [F02] Primary payload did not separate from Volga after reaching LEO/S. Secondary radar calibration sphere did separate. Volga burned to drop to elliptical orbit with Kanopus ST on December 6. Fell out of orbit after about 2 days. One of four clamps on Volga failed to open. [F08] 20:25 UTC. 435x 55 km x 97.3 deg. Possible NROL 87 follower. [F11] 0703 UTC. Kosmos 2574. [F12] 0704 UTC. 348 x 361 km x 96.76 deg. Kosmos 2575. Same orbit as Kosmos 2574 from 12/27/23. ------------------------------------------------------------------ SPACE LAUNCH REPORT SOYUZ 2.1v by Ed Kyle Soyuz 2-1v is a serial-stage small payload launch vehicle derived from the R-7 family. It dispenses with the four strap-on first stage booster rockets that have powered R-7 since its original development. The first stage is newly developed except for the top portion of the upper LOX tank, which is borrowed from the Soyuz 2-1b core stage. A single, fixed NK-33A main engine is augmented by an RD-0110R steering engine that uses four single-axis pivoting nozzles. The second stage is the same as the existing Soyuz 2-1b third stage. A new, optional "Volga" third stage will be used to insert payloads into higher-altitude low earth orbits. Volga will be based on a propulsion module for existing satellites. It will have a hypergolic propulsion system using UDMH fuel and N2O4 oxidizer. Soyuz 2-1v will lift 2.85 tonnes to a 200 km x 56.8 deg orbit from Baikonur, 2.8 tonnes to a 200 km x 62.8 deg orbit from lesetsk. With the Volga third stage, it will lift 1.4 tonnes to an 835 km x 98.7 deg sun-synchronous orbit from Plesetsk. TsSKB Progress will build Soyuz 2-1v at its Samara plant. The rocket will launch from existing, modified pads at Plesetsk and Baikonur Cosmodromes. It will also fly from the new Vostochny Cosmodrome in Eastern Russia. To interface Soyuz 2-1v with existing launching equipment, eight supports were installed on the first stage. Four forward supports connect to booms on the pad while four aft supports connect to guiding systems on the pad. Soyuz 2-1v Inaugural Launch Success Russia's Soyuz 2-1v, a new small satellite launch vehicle, achieved success during its inaugural launch from Plesetsk Cosmodrome on December 28, 2013. The two stage rocket, topped by a multiple-restart capable Volga third stage for orbit trim maneuvers, carried the 50 kg Aist satellite and two lightweight SKRL-765 radar calibration spheres into a roughly 600 x 625 km x 82.42 deg orbit following a 12:30 UTC liftoff from Site 43 Pad 4. The first two stages lifted Volga and its payloads into an initial roughly 260 x 600 km x 82.43 deg transfer orbit. Volga fired at apogee to circularize the orbit. Spacecraft separation occurred at about 14:10 UTC. Soyuz 2-1v stands 44 meters tall and weighs about 157 tonnes at liftoff. It uses the existing Soyuz 2-1b third stage as a second stage. The first stage is newly developed except for the top portion of the upper LOX tank, which is borrowed from the oyuz 2-1b core stage. A single chamber NK-33A staged combustion LOX/kerosene engine, augmented by a four-chamber RD-0110R steering engine, powers the first stage. At liftoff, the engines combine to produce more than 179 tonnes of sea level thrust. About 88% of the total thrust is produced by the NK-33A, an engine originally created as part of the Soviet Union's N1 lunar rocket program during the 1970s. The first stage kerosene tank and the lower part of the LOX tank are 2.66 meters in diameter, fatter than the old Soyuz core's 2.15 meters diameter. The common upper tank section still flares out to 2.95 meters in diameter, allowing both Soyuz launcher types to share launch pad equipment. The first stage burns for about 250 seconds. The Blok I second stage, which is also powered by a staged combustion LOX/kerosene engine, burns for about 270 seconds. Soyuz 2-1v can lift 2.85 tonnes to a 200 km x 51.6 deg orbit from Baikonur, or 1.4 tonnes to an 835 km sun synchronous orbit from Plesetsk. Soyuz 2-1v plans call for the NK-33A engine to be replaced by a more powerful Energomash RD-193 engine derived from the RD-191 Angara engine, which in turn was derived from the RD-170/180 family that power Zenit and Atlas 5 rockets. The decision to use RD-193 rather than restarting long-shelved NK-33A production will also likely affect the Orbital Sciences Antares rocket, which is currently using up a dwindling stock of refurbished NK-33 engines. References: Soyuz User's Manual, Starsem, April 2001 http://www.npoenergomash.ru/eng/engines/rd107/ Jonathan's Space Report Launch Vehicle Database "http://www.planet4589.org/space/lvdb/index.html" Gunter's Space Page "http://www.skyrocket.de/space" RussianSpaceWeb "http://www.russianspaceweb.com" SpaceFlightNow "http://www.spaceflightnow.com" NasaSpaceFlight "http://www.nasaspaceflight.com" TsSKB Progress "http://www.samspace.ru"