ISRO's engines : Designs , Components & Prototypes.
- Thread starter Gautam
- Start date
ISRO seems to be in beast mode, planning to initiate the LME 1100 engine hot testing activity to commence this year, which means a lot to the confidence of ISRO in the Indian private industries. We may see the 1st test flight of NGLV in 3 years.
Preparing for inflight re-ignition - Vacuum ignition trial of Cryogenic engine with Multi-element Igniter conducted successfully
February 8, 2025
On February 7, 2025, ISRO successfully carried out the ignition trial of the indigenous CE20 cryogenic engine powering the upper stage of LVM3, with a multi-element igniter under vacuum conditions, which simulates the engine ignition in the vacuum condition of space. This test was carried out in the High-Altitude Test Facility at ISRO Propulsion Complex, Mahendragiri, Tamil Nadu. During this test, the ignition of the engine Thrust Chamber was carried out with a multi-element igniter in vacuum, under the tank pressure conditions that are expected to prevail at the time of restarting the cryogenic engine in flight. The performance of the engine and the facility during the test was normal and as expected.
Restarting a cryogenic engine is inherently complex and as part of the studies related to the restart operation, ISRO is exploring the initiation of turbopumps in bootstrap mode rather than the stored gas system. In this approach, both the thrust chamber and gas generator are expected to re-ignite under tank head conditions. ISRO has outlined a series of tests aimed at engine starts in bootstrap mode towards enhancing the capability for multiple cryogenic engine restarts during flight.
Previously, the engine ignition trial using multi-element igniter was carried out under ground conditions outside the vacuum chamber. The engine is already qualified to operate for thrust levels ranging from 19t to 22t in flight with single start and is qualified for Gaganyaan mission. The engine was developed by Liquid Propulsion Systems Centre of ISRO.
Preparing for inflight re-ignition - Vacuum ignition trial of Cryogenic engine with Multi-element Igniter conducted successfully
February 8, 2025
On February 7, 2025, ISRO successfully carried out the ignition trial of the indigenous CE20 cryogenic engine powering the upper stage of LVM3, with a multi-element igniter under vacuum conditions, which simulates the engine ignition in the vacuum condition of space. This test was carried out in the High-Altitude Test Facility at ISRO Propulsion Complex, Mahendragiri, Tamil Nadu. During this test, the ignition of the engine Thrust Chamber was carried out with a multi-element igniter in vacuum, under the tank pressure conditions that are expected to prevail at the time of restarting the cryogenic engine in flight. The performance of the engine and the facility during the test was normal and as expected.
Restarting a cryogenic engine is inherently complex and as part of the studies related to the restart operation, ISRO is exploring the initiation of turbopumps in bootstrap mode rather than the stored gas system. In this approach, both the thrust chamber and gas generator are expected to re-ignite under tank head conditions. ISRO has outlined a series of tests aimed at engine starts in bootstrap mode towards enhancing the capability for multiple cryogenic engine restarts during flight.
Previously, the engine ignition trial using multi-element igniter was carried out under ground conditions outside the vacuum chamber. The engine is already qualified to operate for thrust levels ranging from 19t to 22t in flight with single start and is qualified for Gaganyaan mission. The engine was developed by Liquid Propulsion Systems Centre of ISRO.
Vacuum ignition test of CE20 engine using multi element igniter at HAT facility
Preparing for inflight re-ignition - Vacuum ignition trial of Cryogenic engine with Multi-element Igniter conducted successfully
Development & Realization of 10-ton Propellant Mixer for Solid motors of ISRO
February 13, 2025
Department of Space has undertaken multiple initiatives towards indigenous development of critical technologies, materials and machinery as part of ‘Atmanirbharata in Space’. Realization of indigenous 10-ton vertical mixer is a true testament to India’s growing technological prowess, self-reliance and unwavering commitment to innovation.
Solid propulsion plays a crucial role in Indian Space Transportation Systems and vertical mixer is one of the critical equipment in solid motor production.Solid propellants are the backbone of rocket motors, and their production requires precise mixing of highly sensitive and hazardous ingredients.Towards increasing the production scale of solid motor segments,Satish Dhawan Space Centre SHAR, ISRO in collaboration with M/s Central Manufacturing Technology Institute (CMTI), Bangalore, a premier research and development organization under the Ministry of Heavy Industries, Government of India, has successfully designed and developed 10 ton Vertical Planetary Mixers for processing the solid propellants, which is a significant technological marvel.
The 10 ton vertical mixer is the world's largest solid propellant mixing equipment. The development involves collaboration with academia and industries and has successfully completed factory level acceptance tests. This high-capacity mixer will enable the productivity, quality and throughput improvement for the heavy solid motors production. The 10 ton vertical mixer is handed over to Director, SDSC SHAR by Director, CMTI in the presence of Secretary, DOS / Chairman, ISRO on 13th February, 2025 in CMTI, Bengaluru.
The 10 ton vertical mixer weighs about 150 tons with the length of 5.4 m, breadth of 3.3 m & height of 8.7 m. The system has multiple agitators which are hydrostatic driven and will be remotely operated using PLC based control system with SCADA stations.
Key features of 10-ton vertical mixer:
Director, CMTI handed over the 10-ton Vertical Mixer to Director, SDSC SHAR in the presence of Secretary, DOS / Chairman, ISRO
Development & Realisation of 10 ton Propellant Mixer for Solid motors of ISRO
February 13, 2025
Department of Space has undertaken multiple initiatives towards indigenous development of critical technologies, materials and machinery as part of ‘Atmanirbharata in Space’. Realization of indigenous 10-ton vertical mixer is a true testament to India’s growing technological prowess, self-reliance and unwavering commitment to innovation.
Solid propulsion plays a crucial role in Indian Space Transportation Systems and vertical mixer is one of the critical equipment in solid motor production.Solid propellants are the backbone of rocket motors, and their production requires precise mixing of highly sensitive and hazardous ingredients.Towards increasing the production scale of solid motor segments,Satish Dhawan Space Centre SHAR, ISRO in collaboration with M/s Central Manufacturing Technology Institute (CMTI), Bangalore, a premier research and development organization under the Ministry of Heavy Industries, Government of India, has successfully designed and developed 10 ton Vertical Planetary Mixers for processing the solid propellants, which is a significant technological marvel.
The 10 ton vertical mixer is the world's largest solid propellant mixing equipment. The development involves collaboration with academia and industries and has successfully completed factory level acceptance tests. This high-capacity mixer will enable the productivity, quality and throughput improvement for the heavy solid motors production. The 10 ton vertical mixer is handed over to Director, SDSC SHAR by Director, CMTI in the presence of Secretary, DOS / Chairman, ISRO on 13th February, 2025 in CMTI, Bengaluru.
The 10 ton vertical mixer weighs about 150 tons with the length of 5.4 m, breadth of 3.3 m & height of 8.7 m. The system has multiple agitators which are hydrostatic driven and will be remotely operated using PLC based control system with SCADA stations.
Key features of 10-ton vertical mixer:
- High-Capacity Mixing of propellant ingredients in a single batch
- Precision and Control for quality consistency & performance
- Safety and Reliability for handling highly hazardous materials
Director, CMTI handed over the 10-ton Vertical Mixer to Director, SDSC SHAR in the presence of Secretary, DOS / Chairman, ISRO
Development & Realisation of 10 ton Propellant Mixer for Solid motors of ISRO
Update on the SCE-200 from Dept. of Space Annual Report 2024-25:
Some info about the SC120 stage:
Some info about the SC120 stage:
ISRO's electric thruster project:
ISRO's hybrid propulsion project:
This is a very important project for DRDO too. Any progress made here will directly feed into DRDO's hybrid rocket project. If DRDO is successful in that project, it may result in a very long range BVR powered by such a hybrid rocket engine.
ISRO's hybrid propulsion project:
This is a very important project for DRDO too. Any progress made here will directly feed into DRDO's hybrid rocket project. If DRDO is successful in that project, it may result in a very long range BVR powered by such a hybrid rocket engine.
ISRO's electric thruster project:
ISRO's hybrid propulsion project:
This is a very important project for DRDO too. Any progress made here will directly feed into DRDO's hybrid rocket project. If DRDO is successful in that project, it may result in a very long range BVR powered by such a hybrid rocket engine.
ISRO's 3MN class Methalox engine. This is still a long time away:
Don't know why they use the cancelled J-2X as representative image.
Don't know why they use the cancelled J-2X as representative image.
Multiple restarts of Launch Vehicle Stages - ISRO successfully carried out ignition trial using Spark Torch Igniter
March 07, 2025
CUS steering engine ignition test
ISRO is developing Lox-Methane engine and stages for the Next Generation Launch Vehicle, which uses a reusable booster stage and two expendable upper stages. In this configuration, multiple restarts will be essential for the booster stage recovery as well as restarting the upper stage for mission flexibility. The Liquid Propulsion Systems Centre (LPSC) of ISRO is developing a spark torch igniter for the future LOX-Methane stages with the following advantages: multi-restart capability, higher ignition reliability and also cleaner combustion products.
On March 03, 2025, a demonstration model of the spark torch igniter was successfully tested using the GSLV Cryogenic Upper Stage vernier engine with gaseous oxygen & gaseous hydrogen as propellant. The test was conducted at Combustion Research Facility in LPSC and smooth ignition was obtained. The test was conducted for a total duration of 3 seconds and all engine parameters obtained during the test were normal & as expected. Subsequent tests are also planned to refine the performance.
Multiple restarts of Launch Vehicle Stages - ISRO successfully carried out ignition trial using Spark Torch Igniter
March 07, 2025
CUS steering engine ignition test
ISRO is developing Lox-Methane engine and stages for the Next Generation Launch Vehicle, which uses a reusable booster stage and two expendable upper stages. In this configuration, multiple restarts will be essential for the booster stage recovery as well as restarting the upper stage for mission flexibility. The Liquid Propulsion Systems Centre (LPSC) of ISRO is developing a spark torch igniter for the future LOX-Methane stages with the following advantages: multi-restart capability, higher ignition reliability and also cleaner combustion products.
On March 03, 2025, a demonstration model of the spark torch igniter was successfully tested using the GSLV Cryogenic Upper Stage vernier engine with gaseous oxygen & gaseous hydrogen as propellant. The test was conducted at Combustion Research Facility in LPSC and smooth ignition was obtained. The test was conducted for a total duration of 3 seconds and all engine parameters obtained during the test were normal & as expected. Subsequent tests are also planned to refine the performance.
Multiple restarts of Launch Vehicle Stages - ISRO successfully carried out ignition trial using Spark Torch Igniter
The only component now pending is the thrust chamber, which will be constructed at a height of three meters (9.8 feet) and will be tested combined with the SCE 200 engine that has already been tested.
F1 thrust chamber:
ISRO has released a tender for additive manufacturing of LME-1100's LOX exhaust casing - EProcurement
ISRO successfully conducted the flight acceptance hot test of CE20 Cryogenic Engine for LVM3-M6 Mission
March 14, 2025
On March 14, 2025, ISRO successfully conducted the flight acceptance hot testing of the cryogenic engine identified for the sixth operational mission of LVM3 launch vehicle (LVM-M6) at ISRO Propulsion Complex (IPRC), Mahendragiri. Cryogenic engines for every mission undergo hot testing as part of its acceptance for the flight. Hot tests for the indigenous cryogenic engine (CE20)used in the Cryogenic Upper Stage of LVM3 were so far performed at the High-Altitude Test (HAT) facility at IPRC, where vacuum conditions are simulated with complex installations, limiting the maximum hot test duration to 25s.
In the current test, the engine was tested for a longer duration of 100s for the first time using an innovative Nozzle Protection System under non-vacuum conditions. This test method significantly reduces the setup time and effort required for the flight acceptance testing of a cryogenic engine, which in turn helps faster delivery of cryogenic stages for space missions.
Performance of the CE20 engine met all the test objectives and the parameters were closely matching with the predictions during the entire duration of the test. Further, this engine will be integrated to the Cryogenic Upper Stage of the launch vehicle for the LVM3-M6 mission, which is scheduled during the second half of 2025.
ISRO successfully conducted the flight acceptance hot test of CE20 Cryogenic Engine for LVM3-M6 Mission
March 14, 2025
On March 14, 2025, ISRO successfully conducted the flight acceptance hot testing of the cryogenic engine identified for the sixth operational mission of LVM3 launch vehicle (LVM-M6) at ISRO Propulsion Complex (IPRC), Mahendragiri. Cryogenic engines for every mission undergo hot testing as part of its acceptance for the flight. Hot tests for the indigenous cryogenic engine (CE20)used in the Cryogenic Upper Stage of LVM3 were so far performed at the High-Altitude Test (HAT) facility at IPRC, where vacuum conditions are simulated with complex installations, limiting the maximum hot test duration to 25s.
In the current test, the engine was tested for a longer duration of 100s for the first time using an innovative Nozzle Protection System under non-vacuum conditions. This test method significantly reduces the setup time and effort required for the flight acceptance testing of a cryogenic engine, which in turn helps faster delivery of cryogenic stages for space missions.
Performance of the CE20 engine met all the test objectives and the parameters were closely matching with the predictions during the entire duration of the test. Further, this engine will be integrated to the Cryogenic Upper Stage of the launch vehicle for the LVM3-M6 mission, which is scheduled during the second half of 2025.
ISRO successfully conducted the flight acceptance hot test of CE20 Cryogenic Engine for LVM3-M6 Mission