ISRO's new 'monster rocket'

[WUDA]

 

[Dharmachakra]

The semi-cryogenic engine project was sanctioned in 2009.But work has already been started before the sanctioning of the project. And its main sub-systems like gimbals pumps,.... were developed. It will source the common components from its cryogenic cousin. According to ISRO the first semi-cryo will be ready to deploy in 6 years after the sanctioning of the project which mean by 2015.

Various test facilities have already been in place. The reason it will take long gestation periods is, because its of 2 MN class engine.
UMLV was high on ISRO agenda. Parallel development works are on for the development of CUS-60 with design work on the drawing board and awaiting sanction from the GOI.

Even if we forget the cryogenic engine, SCE itself will propel the nation as a leading player in the space tech

For extra lift, all ISRO has to do is clustering of semi-cryos for boosters and first stage.The very same concept for heavy lift vehicle.

This is how I see the future of Indian space program:-
By 2013 GSLV-MKIII with CUS-25 flight tested
By 2015 development of SCE completed
By 2016 GSLV-MKIV with 4S200 boosters capable of launching 6t to GTO
By 2017 GSLV-MKIIISC with SCE-110 instead of existing L110 flight tested ( there by increasing the payload capability to 6t to GTO and 12t to LEO)
By 2018 GSLV-MKIIISC-XL with 4S200+SCE110+C25 capable of carrying 9t to GTO and 16t to LEO
By 2020 UMLV-MKI with 4 S230 + SC500 + C60 capable of carrying 15+tons to GTO and 31t to LEO
By 2023 UMLV-MKII with 8 S230 + SC800 + C60 capable of carrying 85t to LEO
By 2025 HLV-MKI with 4 SC460+SC800+ C100 capable of carrying 100t+ to LEO
By 2030 HLV-MKII with 8 SC460+SC800+ C100 capable of carrying 200t to LEO(we only need this configuration if planning to build a colony in space or a colony on Moon for transporting prefab structures and machinery for mining purposes and solar panels for power generation,.....

The Above is only when conventional UMLV is considered.

When the non-conventional part is taken into account,

By 2017 RLV becomes operational with regular flights to LEO.
By 2020 TSTO becomes operational
By 2025 SSTO becomes operational

THANK YOU guys for bearing me here

 

[Big Boss]

From ^^^^^^^^^^^ this to this VVVVVVVVVVVVVVVV

The journey has been phenomenal.

Our hard work, talent and dedication have brought our nation to this level.

Proud to be Indian.

 

[Varunastra]

from ^^^^^^ this,to vvvvvvv this

proud to be Indian

@bigboss-sorry for copying your idea mate but i thought this image shows a better comparison .CHEERS!

 

[Fireaxe888]

The Saturn V moon rocket weighed 3000 tons and could put 100 into low earth orbit (around 200 km up, not to be confused with GEO (around 35000 km), which is used for GPS and communication satellites because at that orbit a satellite will stay stationary over its part of the Earth's surface. Mass to GEO is a lot lower than to LEO.) The Space Shuttle orbiter could only launch into LEO and weighed 60 tons (the whole stack, boosters and all, weighed 2000 tons) but effective cargo (in the payload bay) was only 20. The European Ariane V, roughly the size of the GSLV III, can put around 15 tons into LEO and launches two satellites at a time.

The GSLV will have a lower mass to LEO but a similar one (around 6 tons) to GEO. It will weigh 600 tons.

It takes a lot of mass to put a little payload into orbit.

 

[harpoon]

Then

Now

All I can say is:

 

[subincb]

The semi-cryogenic engine project was sanctioned in 2009.But work has already been started before the sanctioning of the project. And its main sub-systems like gimbals pumps,.... were developed. It will source the common components from its cryogenic cousin. According to ISRO the first semi-cryo will be ready to deploy in 6 years after the sanctioning of the project which mean by 2015.

Various test facilities have already been in place. The reason it will take long gestation periods is, because its of 2 MN class engine.
UMLV was high on ISRO agenda. Parallel development works are on for the development of CUS-60 with design work on the drawing board and awaiting sanction from the GOI.

Even if we forget the cryogenic engine, SCE itself will propel the nation as a leading player in the space tech

For extra lift, all ISRO has to do is clustering of semi-cryos for boosters and first stage.The very same concept for heavy lift vehicle.

This is how I see the future of Indian space program:-
By 2013 GSLV-MKIII with CUS-25 flight tested
By 2015 development of SCE completed
By 2016 GSLV-MKIV with 4S200 boosters capable of launching 6t to GTO
By 2017 GSLV-MKIIISC with SCE-110 instead of existing L110 flight tested ( there by increasing the payload capability to 6t to GTO and 12t to LEO)
By 2018 GSLV-MKIIISC-XL with 4S200+SCE110+C25 capable of carrying 9t to GTO and 16t to LEO
By 2020 UMLV-MKI with 4 S230 + SC500 + C60 capable of carrying 15+tons to GTO and 31t to LEO
By 2023 UMLV-MKII with 8 S230 + SC800 + C60 capable of carrying 85t to LEO
By 2025 HLV-MKI with 4 SC460+SC800+ C100 capable of carrying 100t+ to LEO
By 2030 HLV-MKII with 8 SC460+SC800+ C100 capable of carrying 200t to LEO(we only need this configuration if planning to build a colony in space or a colony on Moon for transporting prefab structures and machinery for mining purposes and solar panels for power generation,.....

The Above is only when conventional UMLV is considered.

When the non-conventional part is taken into account,

By 2017 RLV becomes operational with regular flights to LEO.
By 2020 TSTO becomes operational
By 2025 SSTO becomes operational


THANK YOU guys for bearing me here

Dont think Cryo engine and semi cryo have anything to do with each other. Semi cryo is developed for stage 1 and 2 and cryogenic engine for third stage. Cryo for GSLV mark 3 static will start mostly after the success of GSLV mark 2 and 2013 is extremely doubtful. Semi cryogenic research is slow but should catch up pace after Mark 3 .

 

[ptltejas]

Better to search for nuke engines

30000kg liquidfuel =1kg urenium.
Though need care it may be set with big space suttle like design and to launch from any island

Better to search for nuke engines

30000kg liquidfuel =1kg urenium.
Though need care it may be set with big space suttle like design and to launch from any island

 

[Dharmachakra]

The Saturn V moon rocket weighed 3000 tons and could put 100 into low earth orbit (around 200 km up, not to be confused with GEO (around 35000 km), which is used for GPS and communication satellites because at that orbit a satellite will stay stationary over its part of the Earth's surface. Mass to GEO is a lot lower than to LEO.) The Space Shuttle orbiter could only launch into LEO and weighed 60 tons (the whole stack, boosters and all, weighed 2000 tons) but effective cargo (in the payload bay) was only 20. The European Ariane V, roughly the size of the GSLV III, can put around 15 tons into LEO and launches two satellites at a time.

The GSLV will have a lower mass to LEO but a similar one (around 6 tons) to GEO. It will weigh 600 tons.

It takes a lot of mass to put a little payload into orbit.

The thing with the satellite launch vehicles is, we cant compare the SLV`s of different countries by mass.

One of the primary reason being different launch locations.And some are optimized for LEO launches and others for GEO and lunar circular orbits.

When someone compare the mass of the launch vehicle, it depends on what kind of technology is going into the vehicle. For example the liquid fueled ones have high specific impulse compared to similar sized solid fueled ones.
And if one concentrates on liquid fueled ones, again there are hypergolics, semi-cryogenics and cryogenics with increasing specific impulse and complexities and costs.

Then again the type of combustion they opt for comes into account. Its all about ones capability and their desired goals.
IF you want a really high performance rocket, then you have to go with all cryo stage,which means so much of added complexity.And an all solid stage will be really low on performance compared to its cryo cousin,but is relatively cheaper.Hence to get somewhere in between will be the hypergolics or semi-cryogenics.

ISRO heavy lift vehicle weighs ~3000Tons and puts a solid 100T into LEO.And this is when using the semi-cryo boosters and primary.IF solid fueled boosters like GSLV MKIII, then the total mass will go upwards for same P/L.

Dont think Cryo engine and semi cryo have anything to do with each other. Semi cryo is developed for stage 1 and 2 and cryogenic engine for third stage. Cryo for GSLV mark 3 static will start mostly after the success of GSLV mark 2 and 2013 is extremely doubtful. Semi cryogenic research is slow but should catch up pace after Mark 3 .

Not necessarily.
Most of the heavy launch vehicles use pure cryo as their core stage.And also use cryo for upper stage. And the booster stages generally are either semi-cryo or solid propellant.

All cryo stage launch vehicle will be ultimate performance one, but the costs will skyrock.So US/USSR use semi-cryo as booster while all other stages as cryo for their heavy launch vehicles.

the C-20 sometimes referred as C-25 (becos of the amount of propellant it carries) will undergo ground testing soon. ISRO just dont want to take a chance with sending cryo stage along on the first ever flight of MKIII.Hence they decided to fly the MKIII minus the cryo stage to validate all other systems and configuration.While in the mean time sometime later this year GSLV-MKII with C-12.

The actual plan was having the semi-cryo core stage for GSLV-MKIII. But given our project management skills, they separated both into two diff projects just to speed-up MKIII development. ITs like LCA tejas with Kaveri

Once MKIII gets a sucessfull flight and once the SCE development completes, then the MKIII with SCE will be tested which makes it GSLV-MKIIISC?

To make a point here, the future of Indian space program is completely dependant on the semi-cryogenic engine technology. As you see,right from UMLV MKI,MKII,HLV,TSTO and possibly SSTO are all dependant on the semi-cryogenic engine. Any delay in this engine development will put a weight in the development of successive launch vehicles, hence SCE was being prioritised as of today.

Also one can understand this by looking at the specs of SCE,its an astounding 2MN thrust
For HLV config, each booster having a 4SCE cluster takes the first stage thrust to an astounding 32MN comparable to Saturn first stage.

The need of the day is, put more money and manpower into the SCE project to speed it up. Once fully operational, then we have to mass produce the engines atleast 10-15 engines/month

The only reason is, ISRO is adopting an UMLV family with extreme commonality of expendable systems. From GSLV-MKIII through the final beacon SSTO, we can use the same semi-cryo with different cluster configurations.

Ofcourse, upgrades and improvements can be applied by passage of time.

 

[Inqhilab]

From ^^^^^^^^^^^ this to this VVVVVVVVVVVVVVVV

The journey has been phenomenal.

Our hard work, talent and dedication have brought our nation to this level.
Proud to be Indian.

 

[Inqhilab]

 

[IND151]

Indeed, if GSLV III will test successfully it will boost India space capability greatly.




There is nothing wrong with truss, it is just one of the interstage design. Truss helps save a lot of weight.

i wasn't saying truss is not good

anyway thanks for weight saving info

 

[IND151]

Then

Now

All I can say is:

the first pic made me remember a story

in early days ISRO guys used to operate in an old church lacking roofs [/B]

all guys used to complain about this to Sir V Sarabhai but he refused to built roof and said that working while observing nature is good

one day during a meeting a pigeon did....(you know what) on table near Sarabhai and then only church got roof

in those days (late 60s) ISRO was building rockets having weight of 10-15 KG

 

[IND151]

double post

 

[The enlightened]

Can some knowledgable chap please take some time to explain to me how this is a monster rocket?
Especially when NASA had built a rocket 5 times as big as this 40 years ago.