SPACE LAUNCH REPORT Soyuz 5 Launch Vehicle Flight History by Variant/Year (2026-Present) by Ed Kyle, Last Update May 1, 2026 L(F) = Number of Launches(Number of Failures) Soyuz-5 Suborb TOTALS Year L(F) L(F) L(F) L(F) L(F) L(F) L(F) ------------------------------------------------------------------ 2020 - - - - - - - 2021 - - - - - - - 2022 - - - - - - - 2023 - - - - - - - 2024 - - - - - - - 2025 - - - - - - - 2026 1(0)* - - - - - 1(0)* ------------------------------------------------------------------ Soyuz-5 Suborb TOTALS L(F) L(F) L(F) L(F) L(F) L(F) L(F) ------------------------------------------------------------------ Suborb 1(0) - - - - - 1(0) Orbit - - - - - - - Total 1(0) - - - - - 1(0) ------------------------------------------------------------------ Footnotes: * Suborbital Test Soyuz-5 Configurations ------------------------------------------------------------------ Configuration ================================================================== Soyuz-5 2 Stage Soyuz-5 ================================================================== Soyuz-5 Capabilities ------------------------------------------------------------------ LEO GTO GEO Earth Height GLOW Payload Payload Payload Escape (meters) (t) (tonnes) 1500 m/s (t) Payload 200 km x to GEO* C3=0 51.6 deg (tonnes) (tonnes) ================================================================== Soyuz-5 2-Stg 17.0 -- -- -- 58.39 m 526 t -65.3 m -531 t ================================================================== *GEO: Geosynchronous Earth Orbit Vehicle Components ------------------------------------------------------------------ Soyuz-5 Soyuz-5 Soyuz-5 Soyuz-5 Stg 1 Stg 2 PLF PLF ================================================================== Dia (m) 4.1 m 4.1 m 4.1 m 5.2 m Len (m) 37.14 m 7.77 m 11.4 m 18.3 m Mp (t) 363 t 59 t GLOW (t) 390.7 t 64.9 t Engine RD-171MV RD-0124MS Mfgr Energomash CADB Fuel Kero Kero Oxidizer LOX LOX T(SL t) 739 t T(Vac t) 816 t 60 t ISP(SL s) 309 s ISP(Vac s) 337 s 359 s Tburn (s) 179 s 393 s No. Eng 1 2 ================================================================== Soyuz-5 Launch Log Proton Failure Details Proton Flight Summary by Year DATE VEHICLE ID PAYLOAD MASS(t) SITE ORBIT ------------------------------------------------------------------ 04/30/26 Soyuz-5 F1 GMM TB 45/1 SUB ------------------------------------------------------------------ NOTES [F1] Inaugural 2-Stage Soyuz-5 test flight with dummy payload on suborbital flight aimed toward Pacific Ocean impact. Abbreviations * Sites TB = Tyuratam/Baikonur ** Orbits LEO = Low Earth Orbit ISS = LEO to ISS EEO = Elliptical Earth Orbit FTO = Failed to Orbit GEO = Geosynchronous Orbit GTO = Geosynchronous Transfer Orbit HCO = Heliocentric (Solar) Orbit MEO = Medium Earth Orbit PAD = On-pad incident. SUB = Suborbital TLI = Trans Lunar Injection Brackets [..] around orbit abbreviation indicate launch vehicle failure and show improper orbit achieve, or show failure to orbit. SOYUZ-5 Soyuz-5 is a new launch vehicle designed to use the retired Zenit-2/3 series facilities at Baikonur. The new rocket uses the Zenit-2/3 first stage engine (RD-171MV with some improvements) but replaces the old Ukrainian-built 3.9 meter diameter structures with 4.1 meter diameter tanks made using Proton tooling. The 4.1 meter-diameter second stage is powered by a pair of RD-0124MS engines similar to those used by Soyuz 2.1b and Angara. The rocket uses kerosene and LOX propellants. An initial suborbital test flight on April 30 2026 used a two-stage Soyuz-5 with a dummy payload. Future Soyuz-5 versions may add a third stage (likely DM-SL or Fregat) to provide GTO capability. References Jonathan's Space Report Launch Vehicle Database "http://www.planet4589.org/space/lvdb/index.html" Encylopedia Astronautica "http://www.astronautix.com/" Gunter's Space Page "http://www.skyrocket.de/space" NasaSpaceFlight "www.nasaspaceflight.com"