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ISRO shares a detailed update on its LOX-Methane engine programme, the propulsion planned for the Next Generation Launch Vehicle (NGLV) and for the future heavy-lift vehicle for India's crewed lunar landing (target 2040). Why methane? - Clean combustion - Low maintenance, which helps reusability - Can be made on Mars from CO2 + water ice, which helps future Mars missions and human settlement LM20-TD: the demonstrator (2019–2020) - 20-tonne thrust technology demonstrator built from existing CE-20 cryogenic engine subsystems - Converted to LOX-CH4 by modifying the propellant flow control and engine start-up systems - Gas generator cycle, with thrust chamber, fuel-rich GG, LOX & fuel turbopumps, igniter, and a mixture ratio control valve with electric drive - Test sequence worked out with an in-house mathematical model - 1 cold flow + 5 hot tests at IPRC - Gave key data on chill-down, ignition, engine start, combustion and rotor-dynamics LME1100: the main engine (started 2023) - 1100 kN thrust, Gas Generator Cycle - Designed to be industry-friendly and cost-effective - Over 70% of components made by additive manufacturing (3D printing) with industry partners across India Gas Generator - 3D printed, in qualification tests at IPRC - Sub-scale GG tests worked out the ignition sequence with a spark torch igniter and tested the 3D-printed injector elements - First ignition test of the full-scale GG on October 9, 2026, with more tests planned Thrust Chamber - Sub-scale hot test campaign at IPRC - Proved the new manufacturing methods planned for the full-scale chamber - Settled the best injector configuration - Showed both oxidiser-rich and fuel-rich spark torch igniters working Turbopumps - LOX and methane turbopumps made by Indian industry - 3D-printed LOX pump impeller spin-tested at LPSC up to its rated speed - Seals and bearings in qualification at LPSC and IPRC - Cold flow tests of the integrated turbopumps ongoing at IPRC Ignition systems - GOX-GCH4 spark torch igniters, oxidiser-rich and fuel-rich - Semiconductor spark plug igniter (LPSC + VSSC + IIST) - Laser ignition, demonstrated with GOX-GH2 and GOX-GCH4 What's next - Integrated LME1100 engine ready by mid-2027, followed by a hot test series including different thrust throttling profiles - Design completed for a 2400 kN Full Flow Staged Combustion Cycle (FFSCC) engine, meant for a future human-rated heavy-lift launch vehicle for crewed lunar landing missions Source: #ISRO #LOXMethane #LME1100 #NGLV #IndianSpace

ISRO shares a detailed update on its LOX-Methane engine programme, the propulsion planned for the Next Generation Launch Vehicle (NGLV) and for the future heavy-lift vehicle for India's crewed lunar landing (target 2040). Why methane? - Clean combustion - Low maintenance, which helps reusability - Can be made on Mars from CO2 + water ice, which helps future Mars missions and human settlement LM20-TD: the demonstrator (2019–2020) - 20-tonne thrust technology demonstrator built from existing CE-20 cryogenic engine subsystems - Converted to LOX-CH4 by modifying the propellant flow control and engine start-up systems - Gas generator cycle, with thrust chamber, fuel-rich GG, LOX & fuel turbopumps, igniter, and a mixture ratio control valve with electric drive - Test sequence worked out with an in-house mathematical model - 1 cold flow + 5 hot tests at IPRC - Gave key data on chill-down, ignition, engine start, combustion and rotor-dynamics LME1100: the main engine (started 2023) - 1100 kN thrust, Gas Generator Cycle - Designed to be industry-friendly and cost-effective - Over 70% of components made by additive manufacturing (3D printing) with industry partners across India Gas Generator - 3D printed, in qualification tests at IPRC - Sub-scale GG tests worked out the ignition sequence with a spark torch igniter and tested the 3D-printed injector elements - First ignition test of the full-scale GG on October 9, 2026, with more tests planned Thrust Chamber - Sub-scale hot test campaign at IPRC - Proved the new manufacturing methods planned for the full-scale chamber - Settled the best injector configuration - Showed both oxidiser-rich and fuel-rich spark torch igniters working Turbopumps - LOX and methane turbopumps made by Indian industry - 3D-printed LOX pump impeller spin-tested at LPSC up to its rated speed - Seals and bearings in qualification at LPSC and IPRC - Cold flow tests of the integrated turbopumps ongoing at IPRC Ignition systems - GOX-GCH4 spark torch igniters, oxidiser-rich and fuel-rich - Semiconductor spark plug igniter (LPSC + VSSC + IIST) - Laser ignition, demonstrated with GOX-GH2 and GOX-GCH4 What's next - Integrated LME1100 engine ready by mid-2027, followed by a hot test series including different thrust throttling profiles - Design completed for a 2400 kN Full Flow Staged Combustion Cycle (FFSCC) engine, meant for a future human-rated heavy-lift launch vehicle for crewed lunar landing missions Source: #ISRO #LOXMethane #LME1100 #NGLV #IndianSpace

44,793 Aufrufe

We have got a cool 3d visualization of the Chandrayaan-5 rover deployment mechanism! The image is more than one year old. Wondering what progress has been made since then. 🇮🇳🇯🇵

We have got a cool 3d visualization of the Chandrayaan-5 rover deployment mechanism! The image is more than one year old. Wondering what progress has been made since then. 🇮🇳🇯🇵

16,839 Aufrufe

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ISRO shares a detailed update on its LOX-Methane engine programme, the propulsion planned for the Next Generation Launch Vehicle (NGLV) and for the future heavy-lift vehicle for India's crewed lunar landing (target 2040). Why methane? - Clean combustion - Low maintenance, which helps reusability - Can be made on Mars from CO2 + water ice, which helps future Mars missions and human settlement LM20-TD: the demonstrator (2019–2020) - 20-tonne thrust technology demonstrator built from existing CE-20 cryogenic engine subsystems - Converted to LOX-CH4 by modifying the propellant flow control and engine start-up systems - Gas generator cycle, with thrust chamber, fuel-rich GG, LOX & fuel turbopumps, igniter, and a mixture ratio control valve with electric drive - Test sequence worked out with an in-house mathematical model - 1 cold flow + 5 hot tests at IPRC - Gave key data on chill-down, ignition, engine start, combustion and rotor-dynamics LME1100: the main engine (started 2023) - 1100 kN thrust, Gas Generator Cycle - Designed to be industry-friendly and cost-effective - Over 70% of components made by additive manufacturing (3D printing) with industry partners across India Gas Generator - 3D printed, in qualification tests at IPRC - Sub-scale GG tests worked out the ignition sequence with a spark torch igniter and tested the 3D-printed injector elements - First ignition test of the full-scale GG on October 9, 2026, with more tests planned Thrust Chamber - Sub-scale hot test campaign at IPRC - Proved the new manufacturing methods planned for the full-scale chamber - Settled the best injector configuration - Showed both oxidiser-rich and fuel-rich spark torch igniters working Turbopumps - LOX and methane turbopumps made by Indian industry - 3D-printed LOX pump impeller spin-tested at LPSC up to its rated speed - Seals and bearings in qualification at LPSC and IPRC - Cold flow tests of the integrated turbopumps ongoing at IPRC Ignition systems - GOX-GCH4 spark torch igniters, oxidiser-rich and fuel-rich - Semiconductor spark plug igniter (LPSC + VSSC + IIST) - Laser ignition, demonstrated with GOX-GH2 and GOX-GCH4 What's next - Integrated LME1100 engine ready by mid-2027, followed by a hot test series including different thrust throttling profiles - Design completed for a 2400 kN Full Flow Staged Combustion Cycle (FFSCC) engine, meant for a future human-rated heavy-lift launch vehicle for crewed lunar landing missions Source: #ISRO #LOXMethane #LME1100 #NGLV #IndianSpace

ISRO shares a detailed update on its LOX-Methane engine programme, the propulsion planned for the Next Generation Launch Vehicle (NGLV) and for the future heavy-lift vehicle for India's crewed lunar landing (target 2040). Why methane? - Clean combustion - Low maintenance, which helps reusability - Can be made on Mars from CO2 + water ice, which helps future Mars missions and human settlement LM20-TD: the demonstrator (2019–2020) - 20-tonne thrust technology demonstrator built from existing CE-20 cryogenic engine subsystems - Converted to LOX-CH4 by modifying the propellant flow control and engine start-up systems - Gas generator cycle, with thrust chamber, fuel-rich GG, LOX & fuel turbopumps, igniter, and a mixture ratio control valve with electric drive - Test sequence worked out with an in-house mathematical model - 1 cold flow + 5 hot tests at IPRC - Gave key data on chill-down, ignition, engine start, combustion and rotor-dynamics LME1100: the main engine (started 2023) - 1100 kN thrust, Gas Generator Cycle - Designed to be industry-friendly and cost-effective - Over 70% of components made by additive manufacturing (3D printing) with industry partners across India Gas Generator - 3D printed, in qualification tests at IPRC - Sub-scale GG tests worked out the ignition sequence with a spark torch igniter and tested the 3D-printed injector elements - First ignition test of the full-scale GG on October 9, 2026, with more tests planned Thrust Chamber - Sub-scale hot test campaign at IPRC - Proved the new manufacturing methods planned for the full-scale chamber - Settled the best injector configuration - Showed both oxidiser-rich and fuel-rich spark torch igniters working Turbopumps - LOX and methane turbopumps made by Indian industry - 3D-printed LOX pump impeller spin-tested at LPSC up to its rated speed - Seals and bearings in qualification at LPSC and IPRC - Cold flow tests of the integrated turbopumps ongoing at IPRC Ignition systems - GOX-GCH4 spark torch igniters, oxidiser-rich and fuel-rich - Semiconductor spark plug igniter (LPSC + VSSC + IIST) - Laser ignition, demonstrated with GOX-GH2 and GOX-GCH4 What's next - Integrated LME1100 engine ready by mid-2027, followed by a hot test series including different thrust throttling profiles - Design completed for a 2400 kN Full Flow Staged Combustion Cycle (FFSCC) engine, meant for a future human-rated heavy-lift launch vehicle for crewed lunar landing missions Source: #ISRO #LOXMethane #LME1100 #NGLV #IndianSpace

indianspaceflight.in🇮🇳

44,793 Aufrufe • vor 18 Tagen

Exclusive: LPSC showed this video of the SE-2000 semi-cryogenic engine firing at the ISRO stall at BSX 2026, along with a 3D render of the LME-110. Thanks to Lokesh KR for standing there holding a phone up to the screen for 15 minutes to catch these few seconds. Please mind the quality. It is a screen recording off a TV, so there is glare, and you may spot shadow in a few frames. This is the only way it exists right now. Fifteen minutes of holding a phone up to a screen. That is what it takes for us to see our own engine work. ISRO could have released this themselves. They have the file, the render, all of it. Instead space nerds have to stand in an expo hall and record a TV. We have archived it here so it does not disappear. #ISRO #LPSC #SE2000 #SemiCryogenic #LME110

Exclusive: LPSC showed this video of the SE-2000 semi-cryogenic engine firing at the ISRO stall at BSX 2026, along with a 3D render of the LME-110. Thanks to Lokesh KR for standing there holding a phone up to the screen for 15 minutes to catch these few seconds. Please mind the quality. It is a screen recording off a TV, so there is glare, and you may spot shadow in a few frames. This is the only way it exists right now. Fifteen minutes of holding a phone up to a screen. That is what it takes for us to see our own engine work. ISRO could have released this themselves. They have the file, the render, all of it. Instead space nerds have to stand in an expo hall and record a TV. We have archived it here so it does not disappear. #ISRO #LPSC #SE2000 #SemiCryogenic #LME110

indianspaceflight.in🇮🇳

74,964 Aufrufe • vor 1 Monat

ISRO has successfully completed a series of Crew Module (CM)-Service Module (SM) Separation Tests for the Gaganyaan missions. Gaganyaan Orbital Module comprises of Crew Module (CM) and Service Module (SM) which are connected using a separation system. Electrical & fluid servicing between CM & SM is ensured through umbilical connections. These modules are integrated prior to the launch and function as a single integrated module from launch till the completion of the on-orbit phase of the mission. Prior to commencing re-entry into the earth’s atmosphere, the CM is separated from the SM. Separation of CM from SM involves multiple precisely sequenced separation events involving pyrotechnic devices and jettisoning systems. In order to validate the overall design adequacy of the separation system, a test setup was realized at Vikram Sarabhai Space Centre, Thiruvananthapuram, for simulating the overall CM-SM assembly with extensive instrumentation. The tests simulated the scenario of CM-SM separation involving the severing of several umbilical connections between CM & SM. Besides validating the design adequacy of the overall CM-SM separation systems, these tests have also demonstrated robustness and shock-survivability of various critical subsystems in the CM. These include various Avionics systems, Inertial Navigation Systems, Thermal Protection System in the Aft & Conical Heat Shield, Crew Module Deployable Umbilical Shield as well as pyrotechnic devices of Crew Module Uprighting System and Thermal & Humidity Control System. This provides necessary confidence in the functioning of the implemented CM-SM separation system for the upcoming 1st uncrewed Gaganyaan Mission (G1) mission which is targeted for launch in 2026. #ISRO #HLVM #GAGANYAAN

ISRO has successfully completed a series of Crew Module (CM)-Service Module (SM) Separation Tests for the Gaganyaan missions. Gaganyaan Orbital Module comprises of Crew Module (CM) and Service Module (SM) which are connected using a separation system. Electrical & fluid servicing between CM & SM is ensured through umbilical connections. These modules are integrated prior to the launch and function as a single integrated module from launch till the completion of the on-orbit phase of the mission. Prior to commencing re-entry into the earth’s atmosphere, the CM is separated from the SM. Separation of CM from SM involves multiple precisely sequenced separation events involving pyrotechnic devices and jettisoning systems. In order to validate the overall design adequacy of the separation system, a test setup was realized at Vikram Sarabhai Space Centre, Thiruvananthapuram, for simulating the overall CM-SM assembly with extensive instrumentation. The tests simulated the scenario of CM-SM separation involving the severing of several umbilical connections between CM & SM. Besides validating the design adequacy of the overall CM-SM separation systems, these tests have also demonstrated robustness and shock-survivability of various critical subsystems in the CM. These include various Avionics systems, Inertial Navigation Systems, Thermal Protection System in the Aft & Conical Heat Shield, Crew Module Deployable Umbilical Shield as well as pyrotechnic devices of Crew Module Uprighting System and Thermal & Humidity Control System. This provides necessary confidence in the functioning of the implemented CM-SM separation system for the upcoming 1st uncrewed Gaganyaan Mission (G1) mission which is targeted for launch in 2026. #ISRO #HLVM #GAGANYAAN

indianspaceflight.in🇮🇳

26,028 Aufrufe • vor 19 Tagen

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