ISRO Unified Launch Vehicle (ULV)

[Salo]

Три года назад:
http://www.isro.org/rep2010/citizens.htm

Semi Cryogenic Engine Development (SCED)
Semi-Cryogenic Engine development envisages the development of a high thrust engine producing 2000 kN (Vacuum) thrust with Liquid Oxygen and kerosene propellant combination for the Common Liquid Core in Unified Launch Vehicle (ULV). As part of semi-cryo engine development pre-project activities, five designs of single element pre-burner injector were realised and tested. Semi-cryo Project Report was prepared and clearance obtained. Conceptual design of the semi cryo engine has been completed

http://www.dare.co.in/news/others/semi-cryogenic-engine-technology-for-future-space-transportation-systems.htm

Semi cryogenic engine technology for future space transportation systems
Friday, 19 December 2008 00:00

The Union Cabinet approved development of Semi Cryogenic Engine technology at an estimated cost of Rs. 1,798 crores with a foreign exchange component of Rs. 588 crores. The objective is designing, fabricating and testing this advanced technology in India in six years time. This will be an important step towards self-reliance in advanced space transportation technology for India.

Storable liquid stages of PSLV and GSLV engines used presently release harmful products to the environment. The trend worldwide is to change over to eco-friendly propellants. Liquid engines working with cryogenic propellants (liquid oxygen and liquid hydrogen) and semi cryogenic engines using liquid oxygen and kerosene are considered relatively environment friendly, non-toxic and non corrosive. In addition, the propellants for semi-cryogenic engine are safer to handle & store. It will also reduce the cost of launch operations.

This advanced propulsion technology is now available only with Russia and USA. India capability to meet existing mission requirements. The semi cryogenic engine will facilitate applications for future space missions such as the Reusable Launch Vehicle, Unified Launch Vehicle and vehicle for interplanetary missions.

[Salo]

instml пишет 03.05.2013 20:40:58:
 ISRO Unified Launch Vehicle (ULV)
 http://forum.nasaspaceflight.com/index.php?topic=31827.0

ULV configurations (ULVs long term goal is to replace PSLV, GSLV & LVM MK3 with a LV having common core stages (semi-cryo stage (SC-160) & cryo stage (C25)) and solid boosters with variable fuel loading.

I am guessing that the large core is kerosene powered, and there is a small LH2 powered upper stage. If it's the reverse, that would be sad.

Yes, the large core/first stage is kerosene + LOX powered with 2000 kn thrust engine (1-2 engine, nos not confirmed). The engine is under development. Second stage would be LH2+LOX.

[Salo]

http://antariksh-space.blogspot.com/2013/01/isro-unified-launch-vehicle.html

Wednesday, January 2, 2013
ISRO Unified Launch vehicle
 
 

ISRO's Unified Modular Launch Vehicle conceptualizes a generic launch vehicle configuration to be able to meet the varying requirement from mission to mission by varying the propulsion system with considerable cost advantage. Unified Launch vehicle will use a common semi-cryogenic stage and will have the features of a world class expendable launch vehicle, with maximum GTO payload capability of 6t and maximum LEO payload capability of 15t. 

The development of Unified modular launch vehicle aims to reduce the number of propulsion modules for all the three types of launch vehicles (PSLV, GSLV MK2 & LVM3). This would mean that the core vehicle would be a standard configuration of cryogenic + semi-cryogenic stages and depending on the payload mass to be delivered in orbit, the solid strapon boosters with different propellant loadings could be added. Studies and developmental activities of ULV will be initiated in the 12th plan period. 

Antriksh's concept of ISRO ULV

Friday, May 3, 2013
ISRO Unified Launch Vehicle Update:
 
 

Here is a table that lists possible configurations of ISRO's under development Unified Launch Vehicle. ULV has been envisaged as having a common standard core stage comprising of a semi-cryogenic stage (SC160) and a cryogenic stage (C25). Solid strapons/boosters with variable propellant loading (S12, S60, S138, S200) would be added to the launch vehicle to achieve a particular payload range. By having a standard core stage design will help in further cutting down the launch cost.

Possible ULV configurations. (courtesy ISRO)

[Salo]

http://antariksh-space.blogspot.com/2012/06/isrosemi-cryogenic-engine-stage.html

Thursday, June 7, 2012
 ISRO Semi Cryogenic engine & stage development
 
ISRO Semi Cryogenic engine & stage development
 

In 2008, ISRO initiated a program to develop semi cryogenic engine technology to allow low cost access to space. The program aims to complete the engine design, fabrication and testing within 6 years. The goal is to develop an extremely efficient, high-pressure staged combustion cycle engine with a vacuum thrust of 2000 kN. The semi cryogenic engine uses a combination of liquid Oxygen and Kerosene (ISRO uses ISROSENE) as propellants which are eco-friendly and cost effective. Using this engine, a semi cryogenic stage will be developed that will constitute the core stage of ISRO's future launch vehicles (unified launch vehicle (ULV) and re-usable launch vehicles (RLV)).

ISRO has been using solid, hypergolic liquid and cryogenic propellants based stages in its satellite launch vehicles (SLV). ISROs workhorse polar satellite launch vehicle (PSLV) uses alternative solid and liquid propellant based stages where a total of four stages are used. ISRO has also developed cryogenic engine and based on it a cryogenic upper stage (CUS) for its geosynchronous satellite launch vehicle (GSLV MK2).  

Figure 1. Isro's semi cryogenic engine (from presentation of Dr. B.N. Suresh, (VSSC) ).

To bring down the cost of access to space, ISRO now plans to use semi cryogenic propellants based core stage in its future launch vehicles. Semi cryogenic engine has efficiency and cost advantages over engines that use solid and hypergolic liquid propellants. The specific impulse of semi cryogenic engine is higher than its solid and hypergolic counterparts, which means that it can lift a higher payload for the same propellant mass.  In addition, the propellants for semi-cryogenic engine are safer to handle & store, and are more eco friendly. When compared to cryogenic engine, semi cryogenic engine is less efficient, but its advantage lies in comparatively reduced engine design complexity and fuel handling cost.

ISRO has plans for a Semi Cryogenic Stage (SC160) with 160 ton propellant loading powered by the 2000 kN semi cryogenic engine to be used in place of L110 stage of GSLV Mk III. This will enhance the GTO payload capability from 4 T to 6 T. In the 12th FYP this stage development will be initiated.
 
 Updates:
 Annual report 2011-2012: Engine design, generation of fabrication drawing of sub systems and integration drawings have been completed. Preliminary Design Review of Engine Gimbal Control system have been completed and technical specification document of both Hydraulic Actuation System and Hydraulic Power System generated. Hypergolic igniter trials have been successfully demonstrated. Single element of pre burner and thrust chamber are realised. 3 tests have been completed for single element Semi cryo pre-burner injector.

http://antariksh-space.blogspot.com/2013/06/isro-semi-cryogenic-engine-update.html

Sunday, June 9, 2013
ISRO Semi-cryogenic engine update
Status of SC2000

The Preliminary Design Review (PDR) for Semi-cryogenic engine development has been completed. Preparation of fabrication drawings of subsystems have been completed.
A MOU has been signed with NFTDC for the realisation of copper alloy for Thrust chamber.
Single element Pre-Burner (PB) injector realised and injector spray charaterisation using PIV was carried out. Test facility for single element pre-burner commissioned at PRG facility, VSSC. Semi Cryo Test facility design by M/s Rolta has been completed.


Design of Semi Cryo Engine including heat exchanger and ejector is competed. Fabrication drawings and documents are generated based on the PDR and joint reviews. Configuration design of subscale engine is completed. Preliminary Design Review (PDR) of Hydraulic Actuation System
(HAS) and Hydraulic Power System (HPS) for Engine Gimbal control is completed and Technical specifications are finalized.

Single Element Pre-Burner injector element has been hot tested successfully. Ignition of LOX/Isrosene propellant with hypergolic slug igniter and flame holding, demonstration of safe handling of pyrophoric fluid TEA, validation of start sequence, characterization of injector elements and qualification of Hayness-214 material are the major achievements of the tests.

http://antariksh-space.blogspot.com/2013/06/isro-semi-cryogenic-engine-update_20.html

Thursday, June 20, 2013
ISRO Semi-cryogenic Engine update


ISRO's Semi-cryo Engine illustration. (credit ISRO)

 ISRO's Semi-cryogenic Engine specifications are following:

 Thrust (vacuum) - 2000 kN
 Isp (vacuum) - 3285 N-s/kg
 Chamber Pressure - 18 MPa
 Mixture Ratio - 2.65
 Thrust Throttling - 65-105 (% of nominal thrust)
 Engine gimbal - 8 degrees (in two planes)

[Salo]

Ноги у этого "индийского" двигателя явно растут из КБЮ - РД-810 во всей красе.

[Salo]

http://www.frontline.in/science-and-technology/in-mission-mode/article4945199.ece?homepage=true

What is the Unified Launch Vehicle of ISRO?

K. Radhakrishnan:
That comes later. Today, we have the GSLV, and GSLV–Mark III is being developed. Of course, we have plans for an experimental mission of GSLV–Mark III.
...
In semi-cryogenic engine development, we had one test of the single injector element of semi-cryogenics done, the first combustion. But we have a long way to go. There is a massive test facility to be created for testing the semi-cryogenic engine and the sub-systems. All this is in the early phase, I would say.

You asked about the Unified Launch Vehicle. It is a future expendable launch vehicle concept. It is modular in shape, comprising semi-cryogenics as booster, a cryogenics as upper stage and strap-ons of different magnitudes made of solid rockets. It can be S-200, S-139 or S-9, depending on the payload requirement. The ULV is slightly futuristic.

[Salo]

http://www.spacetechasia.com/the-way-forward-for-isros-launch-vehicles/

The way forward for ISRO's launch vehicles
By Raman Ponnappan -
July 24, 2018                                  
Indian Space Research Organisation (ISRO) launched their  heaviest launch vehicle to date, GSLV MK III, in June last year and are  in preparation for launching the second and last of the development  flights anytime this year. They also have very ambitious plans for their  next generation vehicle – the Unified Launch Vehicle, or ULV for short.


GSLV MK III is certainly very cost-effective at around US$60 million  per launch for an expendable vehicle. While other space powers are  barely able to reach that cost range for a reusable vehicle, it is a  remarkable achievement. The vehicle is very similar to the Ariane 5 in  terms of 2 strap-on solid boosters and having 2 liquid stages. But the  comparison stops there. In terms of capacity, Ariane 5 lifts 10.8 tons  to GTO whereas GSLV MK III can lift only 4 tons to GTO. What makes the  Ariane 5 lift more to GTO is its cryogenic core stage which provides the  major part of the propulsion.


It is quite true that GSLV MK III has a lower payload ratio than  vehicles in its class by other competitors. Such vehicles with large  strap-on boosters are used by other space enterprises only for their  heaviest payloads. Although the current payload capacity of the GSLV MK  III can be increased to some extent by expanding current stages to  higher propellant loads or by increasing the number of stages, ISRO does  not seem to want to take that route. They would rather wait for the  SCE-200 semi-cryogenic engine to be ready to increase the payload.


Modern space giants like SpaceX are able to use simple configurations  with no strap-on boosters and with only 2 stages on their Falcon 9 Full  Thrust to launch payloads of up to 8 tons to GTO. On the other hand,  ISRO will need at least 3 stages to launch 4 tons only because they do  not have powerful rocket stages with heavily clustered engines like  SpaceX. ISRO needs to develop powerful liquid core stages quickly. The  semi-cryogenic core stage with 2000kN thrust is not available until 2021  and more such powerful clustered stages are needed to reach payloads  above 8 tons to GTO. Based on current planning, this will take beyond  2021.


The GSLV MK III has a few weak links that would need to be ironed out  in order to have a large increase in payload capacity – its weak core  stage with a low thrust and specific impulse and the over-bearing solid  boosters which beyond a point will be more of a burden than a boon. ISRO  has certainly recognized this and the current L110 core will be  replaced by the semi-cryogenic SC200 stage by 2021. The SC200 stage is  based on a powerful engine and will help increase the payload by 50% to 6  tons.


If ISRO wants to increase the payload beyond that, they need to  rapidly develop new stages with multiple clustered semi-cryogenic or  cryogenic engines to replace the core stage. For instance, if they can  develop a cryogenic core stage that can provide a thrust of 750kN with a  specific impulse of 440 seconds on a propellant loading of 170 tons,  then GSLV MK III, too, will be able to lift 10 tons and more to GTO,  just like Ariane 5 which also has a cryogenic core and a similar  architecture.


This can be either as a single engine or as a 4-times clustering of  the CE20 engine. But considering the complexities and the cost of  clustering or developing new cryogenic engines, it would be better to  opt for a clustering of existing semi-cryogenic engines.


However since the specific impulse of the semi-cryogenic engines is  more than 100 seconds lower than cryogenic engines, an equivalent  semi-cryogenic stage will end up being a higher 5 times or 7 times  clustering of semi-cryogenic engines with a very high propellant load.  This results in the vehicles being heavier and the complexities could  also increase. Here, it is very crucial to make the right choice. The  agency seems to be planning for semi-cryogenic core stage rather than  cryogenic core stage. This may be a prudent choice given the direction  in which the other modern space enterprises are headed.


The solid strap-on boosters are adding more weight to the vehicle and  the thrust gained is not commensurate. They also have a very low  specific impulse, thereby not providing enough delta-v for the vehicle.  They should be replaced with new strap-on stages with multiple clustered  semi-cryogenic engines which will be able to provide higher specific  impulse and a lower vehicle mass. Until such clustered stages are  developed, they have to work only with solid boosters for the initial  boost.


As they develop their semi-cryogenic engines, another area that needs  to be worked on is the throttling of liquid engines. Although ISRO has  attempted some stop restart of the PSLV fourth stage for launching  satellites in different orbits, they ought to develop the new liquid  engines to support deep throttling. Throttling in the lower stages helps  in easing max Q pressures on the vehicle during the initial part of the  launch. Throttling of the upper stages also helps to provide the  vehicle with various orbit insertion capabilities. It also helps in  planetary descent.


The next generation ULV is ISRO's effort at unifying their launch  vehicles. Currently they have 3 launch vehicles – PSLV, GSLV MK II and  GSLV MK III for various payload classes. With the ULV, they plan to have  a single vehicle with many different stages from which a few can be  chosen to form a vehicle based on the requirements of the payload. This  way, they will be able to cover the full spectrum of payload  requirements with a single vehicle which can be put together as  required.


The SCE-200 semi-cryogenic engine and the CE-20 cryogenic engine are  still expected to be the core engines based on which the stages of the  ULV will be developed. Various ULV stages to cater for different thrusts  will be developed based on multiple clustering of these engines.


The agency has recognized the explosive need in the small satellite  launch market space and is planning to partner with the private industry  to service the low-end satellites (below 500kg) with a new vehicle  called the Mini PSLV and the payloads that are currently launched by  PSLV. This will not only increase the frequency of launches by these  vehicles, it will also give the agency more time to focus on their other  programs such as Reusable Launch Vehicle (RLV), air-breathing  propulsion and reusability of stages of existing vehicles.

[Salo]

http://www.b14643.de/Spacerockets_1/India/ULV/Description/Frame.htm

ULV

India will develops a new series of SLV, which will replace both the PSLV and GSLV. The ULV (Unified Launch Vehicle) marks the renunciation of India for N2O4/UDMH as propellant for space launch vehicle systems.

The ULV is a future expendable launch vehicle concept on base the GSLV MkIII design. It is modular in shape, comprising semi-cryogenics as core stage, a cryogenics as upper stage and strap-ons of different magnitudes made of solid rockets. It can be S-200, S-138 usw., depending on the payload requirement.

The various configurations of the ULV have an identical first and upper stage. The first stage (L-160) uses Kerosene/LOX. The used conceptual engine RD-810 (SCE-200 in India's project) from Yuzhnoye (Ukraine) with 200 t of thrust, is in development and should be ready in some years. The RD-810 engine is an licensed RD-120MN engine of Energomash. The CE-20 engine from the GSLV MkIII is used for the larger L-30 cryogenic  upper stage. Planned is a more powerful engine CE-60 with 600 kN thrust.

The smallest version of the ULV uses six S-13 booster and has a launch mass of 274 t. The payload is 1.5 t for GTO and 4.5 t for LEO.
The second version uses two S-60 booster and has a launch mass of 340 t. The payload is 3 t for the GTO or 10 t for LEO.
The third version uses two S-138 booster and has a launch mass of 560 t. The payload is 4.5 t for GTO and 12 t for LEO.
The most powerful variant is to use the S-200 booster of GSLV-Mk.3 and has a launch mass of 700 t. The payload is 6 t for GTO and 15 t for LEO.

[Старый]

300/335 секунд - мой любимый размер! Какое давление - не пишут?

[Salo]

http://www.b14643.de/Spacerockets_1/India/ULV/Description/Frame.htm

[Старый]

Как я понимаю один этот моторчик они поставят на Мк3 вместо двух Викасов и будем им Счастье. А если поставят два то Двойное Счастье.  

[Дмитрий В.]

Старый написал:
300/335 секунд - мой любимый размер! Какое давление - не пишут?

Около 180 атм

[Старый]

Дмитрий В. написал:
 Около 180 атм

Блин! Мой любимый размер! 

[Salo]

http://www.b14643.de/Spacerockets_1/India/ULV/Propulsion/engines.htm

[Старый]

Не понял. И им чтоли тоже хохлы движки подогнали?   

[Дмитрий В.]

Старый написал:
Не понял. И им чтоли тоже хохлы движки подогнали?    

По межправительственному соглашению от, емнип, 2012 года. Это уже давно не новость, в общем.

[Дмитрий В.]

Вот здесь точнее: https://en.wikipedia.org/wiki/SCE-200
Там и Роскосмос поучаствовал.

[Старый]

Дмитрий В. написал:
 

Старый написал:
Не понял. И им чтоли тоже хохлы движки подогнали?    

По межправительственному соглашению от, емнип, 2012 года. Это уже давно не новость, в общем.

Вот так вот, блин. Как наши подгоняют водородник так нарушение режима нераспространения и санкции. А как хохлы керосинку там всегда пожалуйста! 

[Salo]

https://www.quora.com/What-is-the-current-status-of-ULV-and-HLV-of-ISRO

What is the current status of ULV and HLV of ISRO?
Tirtha Chakrabarti (তীর্থ চক্রবর্তী), Rocket science is cute!
Updated Nov 18, 2018 · Upvoted by Manika Nagpal, former SRFP fellow (Indian Academy of Sciences) at Indian Space Research Organisation (2016) · Author has 677 answers and 1.3m answer views

ULV:

The concept:

The ULV or the Unified Launch Vehicle (also called 'modular vehicle') will be a kind of vehicle that will replace the currently active PSLV and GSLV rocket families by a single rocket. It will reduce manufacturing and various other cost of launch along with making the vehicle more powerful for heavier lifting than current vehicles.

Stages:

ULV will be a series of 3 to 4 expendable launch types and will feature common liquid 'Semi-Cryogenic core' as the first stage with variable fuel loading capabilities for all of its variants.

The Second stage will be equipped with a Cryogenic stage which will be highly configurable thus having the ability to satisfy various payload requirements of customers.

Engine:

ISRO currently has the CE-7.5 (cryogenic engine) which is being used in GSLV-mk2 and CE-20 engine which is under development (currently tested successfully) being used in GSLV-mk3.

Further developments are either in progress or planned such as the CE-60 and the CE-100 engines. The SCE-200 (the semi cryogenic engine) is under development and in an advanced stage of development. This will be used as the common liquid semi-cryogenic core.

Boosters:

The vehicle will mate solid propellant Strap-on boosters of different variations (S13, S60, S139, and S200) for the boost phase. Various of these boosters are used in PSLV, GSLV-mk2 and GSLV-mk3. Hence, by adjusting the fuel and power levels of the stages and boosters, a single launch vehicle can be used to launch various payload mass thus eliminating the requirement to have multiple launch vehicles, this is the sole aim of the ULV project.

Variants:

The variants will use various of these underdevelopment engines and boosters in various stages.

    The smallest variant of the ULV uses six S-13 boosters and has a launch mass of 274 tonnes. The payload capacity is 1.5 tonnes to Geosynchronous Transfer Orbit (GTO) and 4.5 tonnes to Low-Earth Orbit (LEO)
    The second variant uses two S-60 boosters and has a launch mass of 340 tonnes. The payload is 3 tonnes to GTO or 10 tonnes to LEO
    The third variant uses two S-138 booster and has a launch mass of 560 tonnes. The payload is 4.5 tonnes to GTO and 12 tonnes to LEO
    The most powerful variant is to use the S-200 booster of GSLV-Mk3 and has a launch mass of 700 tonnes. The payload is 6 tonnes to GTO and 15 tonnes to LEO

A potential heavy-lift variant (HLV) of the unified launcher capable of placing up to 9–10 ton class of spacecrafts into Geosynchronous Transfer Orbit would include:

    A larger dual S-250 solid strap-on boosters.
    A semi-cryogenic core stage with SCE-200 engine
    A semi cryogenic third stage with a CE-20 engine or new CE-50 engine
    A new fourth stage with cryogenic C10 engine

    HLV will come after ULV is achieved.

    For now GSLV-mk2 is active and it has to be gained reliability. In coming May it will be used for launching 'South Asian Satellite' [for various neighboring SAARC countries as a gift for improving international relation announced by PM Modi] (Edit- Launch successful) and Next year Mk2 will be used for 2nd moon mission.

    GSLV-mk3 is at advanced phase of development and will be used for satellite launch for the first time in coming June. If it succeeds, we will have another powerful launch vehicle in form of mk3. (Edit- Launch successful). It will also have to gain reliability. In around 2020, Mk3 may be used in 2nd Mars mission. Along with these, development work of the engines and boosters required for ULV are going on and has good progress. We may hope for our ULV in the next decade perhaps.

    (Edit- ISRO has recently announced that the Semi-Cryogenic engine is likely to be ready in 2019 and the stage in 2020. The first vehicle with this stage will fly for the first time in 2021 if everything goes right. That will be the 4th variant of ULV.)

[Salo]

https://www.thehindubusinessline.com/news/science/isro-moves-on-gears-up-to-test-semi-cryogenic-engine-in-ukraine/article29451601.ece#

ISRO moves on, gears up to test semi-cryogenic engine in Ukraine
M Ramesh Chennai | Updated on September 19, 2019 Published on September 19, 2019

ISRO has put its disappointment over the not-so-successful moonlanding behind it and has begun to look forward — to the next missions. On the cards is a clutch of launches, starting fr om PSLV 47 later this month. But the next big milestone is the testing of the semi-cryogenic engine — in Ukraine.

The semi-cryogenic engine is fully ready now, S Somnath, Director, Vikram Sarabhai Space Centre, Thiruvananthapuram, a unit of ISRO, told BusinessLine. When ready for operation, the semi-cryo will raise ISRO's carrying capacity from 4 tonnes to 6 tonnes, all the way up to the Geosynchronous orbit, 36,000 km above earth.

India and Ukraine signed, on June 2, 2005, a Framework Agreement for cooperation in the peaceful uses of outer space.

It is believed that this also involved transfer of blueprints for a rocket engine. Even the liquid propellant-fired Vikas engine, used in GSLV's lower (core) stage was first tested in France, recalls a former ISRO executive.
Technological leap

The ₹1,800-crore SCE-200, wh ere 200 refers to the number of tonnes of thrust it kicks, is a big technological leap. It is a very complex machine and its development is no less a technological challenge than Chandrayaan-2, say sources in ISRO.

The cryogenic engine that sits at the top of the GSLV rocket is a small one, of 20 tonnes of thrust, which is only slightly more than what a Pratt & Whitney 1000G engine, fitted onto a A320 aircraft, delivers.

After all, the cryogenic engine does not need to carry a very heavy load on its head — the heavy lifting is done by the lower stages of the rocket, which detach and fall into the sea after they expend themselves.

On the other hand, the semi-cryogenic engine, which is based on Ukrainian company KB Yuzhnoe's RD-810 engine design, will be located at the lower part of the rocket and is meant to do the heavy lifting. It generates a whopping 200 tonnes of thrust; the pressure inside its combustion chambers is about 190 times the atmospheric pressure that we feel on our bodies all the time.

The SCE-200 is good in another way too — its fuel is kerosene, kept in the tank at room temperature. (The oxidiser is liquid oxygen, kept in cryogenic conditions so that it remains liquid.)

Kerosene is a far 'greener' fuel than the unsymmetrical dimethyl hydrazine (UDMH) that is currently used in Indian rockets, which is also highly toxic and carcinogenic.