The next generation Vikas engine developed by the Liquid Propulsion Systems Centre (LPSC) is being flown for the first time. LPSC director V Narayanan told Express that the improved engine would give a significant advantage in terms of enhancing payload capability. “Usually, the chamber pressure is 58 bar, but with the use of high-thrust Vikas engine, we will achieve 62 bar, which is a 6% increase in thrust that gives us 70 kgs of additional payload gain in this mission. Right now, we are going to use the high-thrust Vikas engine only in the second stage. Basically, we are validating it. For Chandrayaan-2 mission, we will be using five such engines aiming for a payload gain of around 250 kgs,” Narayanan said.
Narayanan said this would be the best way of mission planning and optimum utilisation of propellants. “All these new things are being done keeping lunar mission in the mind and ISRO’s bigger game plan to increase GSLV payload capability. For Chandrayaan-2, we are formulating a perfect combination. The four strap-ons and second stage will be boosted with high-thrust Vikas engines; cryogenic upper stage will be loaded with enhanced propellants of 15 tonnes instead of current 12.8 tonnes and will be operated with 9.5 tonne thrust compared to the present 7.5.”
QuoteThe next generation Vikas engine developed by the Liquid Propulsion Systems Centre (LPSC) is being flown for the first time. LPSC director V Narayanan told Express that the improved engine would give a significant advantage in terms of enhancing payload capability. “Usually, the chamber pressure is 58 bar, but with the use of high-thrust Vikas engine, we will achieve 62 bar, which is a 6% increase in thrust that gives us 70 kgs of additional payload gain in this mission. Right now, we are going to use the high-thrust Vikas engine only in the second stage. Basically, we are validating it. For Chandrayaan-2 mission, we will be using five such engines aiming for a payload gain of around 250 kgs,” Narayanan said.QuoteNarayanan said this would be the best way of mission planning and optimum utilisation of propellants. “All these new things are being done keeping lunar mission in the mind and ISRO’s bigger game plan to increase GSLV payload capability. For Chandrayaan-2, we are formulating a perfect combination. The four strap-ons and second stage will be boosted with high-thrust Vikas engines; cryogenic upper stage will be loaded with enhanced propellants of 15 tonnes instead of current 12.8 tonnes and will be operated with 9.5 tonne thrust compared to the present 7.5.”Source: http://www.newindianexpress.com/states/tamil-nadu/2018/mar/28/with-eye-on-lunar-mission-isro-to-test-high-thrust-vikas-engine-1793608.htmlISRO confirms that GSLV F-10 will be first fully upgraded GSLV. All four L40 strapons will have high thrust vikas engines and well as the second stage. The upper stage will have propellant loading increased to 15 tons and thrust of CE-7.5 engine will be increased from present 7.5 tons to 9.5 tons. Payload capability to GTO for GSLV has been increased by 70kg for GSLV F-08 mission to bring the GTO capability of GSLV up from 2.25 tons to 2.32 tons. With additional upgrades on GSLV F-10 mission later this year this will further boost GTO capability by 250 kg to bring GSLV GTO capability to 2.57 tons. In short: Current GSLV GTO capability: 2.25 tons GSLV F-08 GTO capability: 2.32 tons GSLV F-10 GTO capability: 2.57 tons ISRO final goal for GSLV : 3.25 tons to GTO
Just finished watching the televised launch of the Insat 3Dr on Gslv on Sept 8/2016. One of the Isro scientists mentioned that vehicle had an upgraded Cryogenic engine/ stage for the flight. So the C-12 has been uprated at least once. Any idea what kind of improvement was made then?
Umamaheswaran R., now Associate Scientific Secretary, ISRO, told me in October 2016 that GSLV-MkII can put 3.2 tonnes into an initial orbit of 180 km by 20,000 km.Yes. We enhanced the GSLV-MkII with high thrust engines and so on. With the enhancement, the number is 2.7 tonnes into GTO [geostationary transfer orbit]. Now, 3.2 tonnes has become 3.8 tonnes. And 22,000 km has become 37,000 km. This combination cannot be launched by GSLV-MkII.
The Indian Space Research Organisation (Isro), on Thursday said it has successfully completed the hot test of cryogenic engine for the GSLV-F11, which is scheduled to launch the GSAT-7A in November this year. A hot test is a ground test conducted to check for the safety and also whether or not all design parameters are met. Unlike a cold test where all the propellants are checked for, a hot test involves firing of the engine in test conditions.
The test, conducted at the Isro Propulsion Complex in Mahendragiri on August 27, was carried out for 200 seconds during which the engine operated in the nominal and 13% uprated thrust regimes."All the propulsion parameters during the test were found satisfactory and closely matched with predictions. For the first time, indigenously developed copper alloy is used in this engine," Isro said.The cryogenic engine will now be integrated with the propellant tanks, stage structures and associated fluid lines to realise the fully integrated flight cryogenic stage.
Rolling Mill LayoutCopper Alloy (Cu-0.5Cr-0.05Ti-0.05Zr) is an important and vital item required for cryogenic/semi-cryogenic engines for the realisation of thrust chamber inner shell and injector face plates of Cryogenic Upper Stage (CUS) engine for GSLV Mk-II, CE20 engine for GSLV Mk-III and Semi-Cryo (SC) stage. This is also required for the Steering Engines (SE) of CUS engine, Gas generator of CUS & CE20 engines, injectors, pre-burner and pyro components of SC engine.These projects require Copper Alloy plates, rods and forgings of various dimensions. For plates, thickness requirement range from 12 mm to 18 mm and width of 850 mm. Rods and forgings of this alloy are also required with diameters ranging from 30 mm upto 300 mm.
Vacuum Induction Melting Furnace 1000kgIndigenisation efforts were made through NFTDC, Hyderabad for CUS, CE20 and SC. Melt capacity was augmented to 1000 kg and plate rolling mill capable of 1500 mm width was established for meeting the project requirements. All required products using this alloy have been successfully realized for CUS, CE20 and Semi-Cryo projects. The hot test of the CUS engine using this copper alloy for 200 sec in the nominal and 13% uprated thrust regime was carried out at IPRC, Mahendragiri. This engine will power the cryogenic stage of GSLV Mk-II, which is scheduled to launch GSAT-7A in November this year.
Going over GSLV launch history you have to wonder why ISRO keeps this launch vehicle operational. Out of 15 launches there have been 6 failures of varying degrees putting the failure rate at almost 50%. Now they have LVM3 there is no reason to keep such a unreliable launch vehicle flying.
GSLV was the first launch vehicle of ISRO to fly liquid fueled strapons, first to have a cryogenic upper stage, first to employ hot staging and of course first to achieve the Geostationary Transfer Orbit (GTO).
Quote from: Angry_cat on 11/15/2023 03:40 amGoing over GSLV launch history you have to wonder why ISRO keeps this launch vehicle operational. Out of 15 launches there have been 6 failures of varying degrees putting the failure rate at almost 50%. Now they have LVM3 there is no reason to keep such a unreliable launch vehicle flying.<snip>I think if we view GSLV as more of a technology testbed of sorts we can have a more positive view of the entire GSLV program. GSLV was the first launch vehicle of ISRO to fly liquid fueled strapons, first to have a cryogenic upper stage, first to employ hot staging and of course first to achieve the Geostationary Transfer Orbit (GTO). First in something is always hard and prone to failure and hence why we should appreciate GSLV's various contributions to the Indian Launch Vehicle program.
Quote from: K210 on 11/18/2023 09:58 amGSLV was the first launch vehicle of ISRO to fly liquid fueled strapons, first to have a cryogenic upper stage, first to employ hot staging and of course first to achieve the Geostationary Transfer Orbit (GTO).The first payload sent into GTO was by PSLV, carrying METSAT 1 on 12 September 2002 (target orbit was 180x36,000 km according to the press kit). The previous GSLV Mk.I launch on 18 April 2001 had a performance shortfall and sent its payload into sub-GTO with a 32,000 km apogee.
Quote from: K210 on 11/18/2023 09:58 amQuote from: Angry_cat on 11/15/2023 03:40 amGoing over GSLV launch history you have to wonder why ISRO keeps this launch vehicle operational. Out of 15 launches there have been 6 failures of varying degrees putting the failure rate at almost 50%. Now they have LVM3 there is no reason to keep such a unreliable launch vehicle flying.<snip>I think if we view GSLV as more of a technology testbed of sorts we can have a more positive view of the entire GSLV program. GSLV was the first launch vehicle of ISRO to fly liquid fueled strapons, first to have a cryogenic upper stage, first to employ hot staging and of course first to achieve the Geostationary Transfer Orbit (GTO). First in something is always hard and prone to failure and hence why we should appreciate GSLV's various contributions to the Indian Launch Vehicle program.Think it is better for ISRO to phased out the GSLV Mk2 quickly. Since even the LVM3 appears to have an end date on the horizon.A future "LVM3" with semi-cryogenic core replacing the current hypergolic LVM3 core is a new vehicle even if ISRO stated otherwise.Unless maintaining the 2 low volume production lines is political expediency. ISRO should consolidated their near future launches with the LVM3 to reduce production infrastructure footprint and get scale of economy with more production volume.Interesting factoid - the strapped-on hypergolic boosters on the GSLV Mk2 have a longer burn time and higher ISP than the solid first stage.
How many launches remain for GSLV?
