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| Yenisei (rocket) | |
|---|---|
| Name | Yenisei |
| Country | Russia |
| Manufacturer | RSC Energia |
| Height | 60–70 m |
| Diameter | 4.1 m |
| Stages | 2–3 |
| Status | Development |
Yenisei (rocket) is a Russian heavy-lift launch vehicle concept developed for crewed lunar and deep-space missions. Conceived by RSC Energia and promoted within Roscosmos strategic planning, the project aimed to provide an alternative to existing launchers for Luna-25, Luna-26, and follow‑on lunar architecture missions. The design drew on heritage from Angara (rocket family), Proton (rocket), and the N1 and Soyuz (rocket family), while interfacing with spacecraft like the Orion (spacecraft), Federation (spacecraft), and proposed lunar landers.
Yenisei's development traces to strategic shifts after the Soviet Union dissolution and the modernization drives undertaken by Roscosmos State Corporation and RSC Energia during the 2010s. Early conceptual studies involved specialists from TsNIIMash, TsENKI, and the Keldysh Center, leveraging technologies matured in programs such as Angara (rocket family), Proton (rocket), Soyuz-2, and the cancelled Rus-M. Political endorsements from the Russian Federation Ministry of Defence and the Government of Russia influenced funding trajectories, echoing earlier decisions like those behind Vostok modernization and the Mir successor proposals. International observers compared Yenisei to heavy-lift projects including Space Launch System, Falcon Heavy, and Long March 9.
Yenisei was envisaged as a two- or three-stage heavy launcher with a core diameter around 4.1 m and modular strap-on boosters similar in concept to Angara-A5. Propulsion concepts referenced the RD-0124 family and newer high-performance engines developed by NPO Energomash and Khrunichev State Research and Production Space Center, with staged combustion cycles akin to those of RD-170 and RD-180. Propellants considered included RP-1/liquid oxygen and liquid hydrogen/liquid oxygen for upper stages, paralleling choices in Ariane 5, Delta IV Heavy, and H-II. Structural materials and avionics drew on experience from Energia (rocket) and Buran programme components, while guidance systems were to be supplied by firms descended from Lavochkin Association instrumentation programs. Payload fairing and separation technology referenced heritage from Proton-M and Soyuz-ST.
Proposed configurations ranged from a minimal two-stage heavy variant to a three-stage heavy variant with an expendable upper stage for translunar injection, enabling missions like crewed lunar flybys and cargo delivery to cis-lunar stations similar to concepts involving Lunar Gateway and International Space Station. Configurations envisaged strap-on booster clusters comparable to Angara-A5 boosters, and a hydrogen-fueled upper stage analogous to Block DM and Centaur capabilities. Variants included a cargo-optimized launcher for large modules used in architectures inspired by Mir and the International Space Station, and a crew-rated configuration integrating escape systems similar to Soyuz (spacecraft) launch escape towers.
As a concept, Yenisei entered preliminary design reviews and mockup testing at RSC Energia and affiliated centers like TsNIIMash and the Keldysh Center. Ground tests examined structural loads, engine test-firing campaigns referenced techniques used for RD-180 and RD-170 testbeds, and scale-model vibration testing followed practices from Energia (rocket) test programs. No orbital flights occurred; milestones paralleled those of other national heavy-lift projects during prototype phases, such as the early flight campaigns of Angara and the developmental timeline of Space Launch System.
Yenisei was intended to support crewed lunar sorties, long‑duration deep-space cargo shipments, and assembly of large space infrastructures, enabling delivery of modules comparable in size to Zvezda (ISS module), Zarya, and proposed lunar landers derived from Lunar Lander concepts. Payload roles included translunar injection for spacecraft like Federation (spacecraft) and cargo for lunar bases modeled after proposals from Roscosmos and international partners. Concepts invoked cooperation with lunar science initiatives such as Luna-Glob and sample-return missions reminiscent of Luna 16 and Chang'e missions. Civilian and dual-use scenarios paralleled cargo roles performed by Proton-M and heavy-lift tasks undertaken historically by Energia (rocket).
Key industrial participants listed in public plans included RSC Energia, NPO Energomash, Khrunichev, TsSKB-Progress, and scientific institutes such as TsNIIMash and the Keldysh Center. International contractor analogues and potential partners cited in analyses included aerospace firms involved with Arianespace, NASA, JAXA, and commercial entities comparable to SpaceX for subsystem procurement and launch services integration. Technology exchanges referenced earlier cooperation episodes like the International Space Station program and export relationships with nations including India, China, and members of the European Space Agency.
Official status moved between conceptual design and preliminary development, with program funding and prioritization subject to shifts in Russian strategic planning and competing projects such as the Angara (rocket family) modernization. Future planning scenarios envisaged further design maturation, detailed testing programs, and potential flight qualification campaigns contingent on commitments from Roscosmos leadership and the Government of Russia. Program trajectories remain influenced by international sanctions, domestic industrial capacity carried by firms like NPO Energomash and Khrunichev, and broader initiatives in lunar exploration exemplified by Artemis program comparisons and bilateral frameworks involving China National Space Administration and European partners.
Category:Proposed space launch vehicles of Russia