CE-7.5
CE-7.5 is ISRO's indigenous staged-combustion cryogenic engine for the GSLV Mk II CUS/GS3 upper stage. ISRO specifies liquid oxygen/liquid hydrogen propellants, 75 kN nominal maximum thrust, and an 814 s burn time; the existing GSLV family and GSLV Mk II configurations retain one CE-7.5 in the third stage.
Identity
- Domains
- spaceflight
- Identity Level
- model
- Kind
- liquid-rocket-engine
- Name
- CE-7.5
- Status
- active
Details
- Description
- CE-7.5 is ISRO's indigenous staged-combustion cryogenic engine for the GSLV Mk II CUS/GS3 upper stage. ISRO specifies liquid oxygen/liquid hydrogen propellants, 75 kN nominal maximum thrust, and an 814 s burn time; the existing GSLV family and GSLV Mk II configurations retain one CE-7.5 in the third stage.
- Developers
- Manufacturers
- Propellants
- liquid hydrogenliquid oxygen
- Rocket Specs
- Burn Time S
- 814
- Cycle
- staged-combustion
- Vacuum Thrust Kn
- 75
Links
- Official Url
- https://www.isro.gov.in/GSLV_CON.html
Assets & Meta
- Creation Time
- July 29, 2026 at 08:31:26 UTC
- Updated Time
- August 15, 2026 at 05:36:19 UTC
Other
- Sources
- Accessed Date
- 2026-08-14
- Note
- ISRO identifies CE-7.5 as India's first cryogenic engine, developed by the Liquid Propulsion Systems Centre for the GSLV Mk II cryogenic upper stage, and specifies staged combustion, LOX/LH2, 75 kN nominal maximum thrust, and 814 s burn time.
- Publisher
- Indian Space Research Organisation
- Title
- Geosynchronous Satellite Launch Vehicle Mark II
- Accessed Date
- 2026-08-14
- Note
- ISRO's indigenous cryogenic-stage mission page identifies the CUS main engine and steering-engine arrangement and reports 73.55 kN nominal vacuum stage thrust; this contextual stage figure is retained as source context without replacing the CE-7.5 engine's 75 kN field.
- Publisher
- Indian Space Research Organisation
- Title
- Indigenous Cryogenic Engine and Stage