SCE-200

SCE-200
Power Head Test Article (PHTA) for SCE-200
Country of originIndia
DesignerLPSC, ISRO
ManufacturerGodrej & Boyce[1][2]
ApplicationMain engine
StatusUnder Development
Liquid-fuel engine
PropellantLOX / RP-1
Mixture ratio2.65[3]
CycleStaged combustion
Configuration
Chamber1
Performance
Thrust, vacuum2,030 kN (460,000 lbf)[4]
Thrust, sea-level1,820 kN (410,000 lbf)[4]
Throttle range60% to 105% [3]
Chamber pressure18 MPa (2,600 psi)[3]
Specific impulse, vacuum335 seconds (3.29 km/s)
Specific impulse, sea-level299 seconds (2.93 km/s)
Mass flow640 kg/s [5]
Dimensions
Dry mass~2700 kg

The SCE-200 (also referred as Semi-Cryogenic Engine-200) is a 2 MN thrust class liquid rocket engine, being developed to power Indian Space Research Organisation's (ISRO) existing LVM3 and upcoming heavy and super heavy-lift launch vehicles. It is being developed by the Liquid Propulsion Systems Centre (LPSC) of ISRO, and is expected to have first flight in 2020s.

Burning liquid oxygen (LOX) and RP-1 kerosene in an oxidizer-rich staged combustion cycle,[6] the engine will boost payload capacity of LVM3 replacing current L110 stage powered by 2 Vikas engines. It is also expected to power ISRO's upcoming Next Generation Launch Vehicle (NGLV)[7] rockets (previously planned as ULV) as well as ISRO's future reusable rockets based on RLV technology demonstrations.[8][9][10][11][12]

The engine in September 2019 reportedly had become ready to begin testing in Ukraine and enter service no earlier than 2022. The use of engine of India's first human spaceflight, hence was ruled out by ISRO. By November 2022, SCE-200 had neared completion of its qualification tests. The Semi-Cryogenic Engine and Stage Test Facility at the ISRO Propulsion Complex Mahendergiri was preparing for ground tests now that the SCE-200 had reached the final stages of development.[13]

  1. ^ M Ramesh. "Godrej Aerospace to make semi-cryogenic engines". The Hindu Business Line.
  2. ^ "Archived copy" (PDF). Archived from the original (PDF) on 8 December 2015. Retrieved 2 November 2015.{{cite web}}: CS1 maint: archived copy as title (link)
  3. ^ a b c "Semi-cryogenic Propulsion". VSSC.gov.in. Retrieved 24 April 2019.
  4. ^ a b Cite error: The named reference iitten-20150506 was invoked but never defined (see the help page).
  5. ^ "Launch Vehicles and Propulsion System" by Dr. V. Narayanan. Event occurs at 46 min. 10 sec.
  6. ^ K. N. Jayachandran; Arnab Roy; arthasarathi Ghosh. "Numerical investigations on Direct Contact Condensation (DCC) of oxygen vapor at the inlet duct to the main LOX pump in a staged combustion cycle based rocket engine" (PDF). Cryogenic Engineering Centre and Department of Aerospace Engineering, Indian Institute of Technology Kharagpur.
  7. ^ "ISRO readies plan for next generation launch vehicle". The Hindu. 8 June 2023. ISSN 0971-751X. Retrieved 17 July 2023.
  8. ^ Cite error: The named reference isro-ar2013 was invoked but never defined (see the help page).
  9. ^ "Government of India, Department of Space, Annual Report 2015 - 2016" (PDF). 26 May 2016. Archived from the original (PDF) on 13 December 2016.
  10. ^ Raj, Gopal (5 June 2017). "ISRO's heaviest rocket is ready but is it enough for the load that lies ahead?". The Ken. Retrieved 5 June 2017.
  11. ^ "Post successful launch of India's heaviest rocket, ISRO sets its eyes on 10-tonne class payload launcher". NewIndianExpress. Retrieved 7 June 2017.
  12. ^ "Annual Report 2016 -2017 (English) - ISRO". www.isro.gov.in. Archived from the original on 13 February 2018. Retrieved 13 February 2018.
  13. ^ Rajwi, Tiki (26 February 2024). "ISRO's Semi-Cryogenic Engine and Stage Test Facility at Mahendragiri". The Hindu. ISSN 0971-751X. Retrieved 18 August 2024.