ISRO Conducts Functional Qualification Test of GSLV Mk-3 S200 Separation Sy

[arp2041]

ISRO is making steady progress towards the debut launch in April 2014 of its GSLV Mk-3 launcher, which will be capable of inserting a 10 ton spacecraft in low earth orbit.

It recently tested the separation system of the S200 strap on motors of the launchers from the core vehicle.

The first stage of the GLSV Mk-3 consists of two 200 ton, S200 solid rocket motors, strapped around the 110 ton restartable core liquid propellant second stage (L-110) using two Vikas engines.

The separation system consists of two joints viz fore end joint and aft end joint, which attaches the L110 stage of the core with S200 motors. The thrust developed by the S200 motors are transferred to the core vehicle through the fore end joint while the aft joint takes care of the lateral loads.

The S200 separation system is used to dump the two spent S200 motors at about 145 seconds after take off allowing the second stage to kick in.

The third stage of the GSLV Mk-3 would be an ISRO developed cryogenic rocket motor with a propellant loading of 25 ton (C-25).

The first flight of the Mk-3 will be a sub-orbital flight test, sans the cryogenic third stage.

ISRO Conducts Functional Qualification Test of GSLV Mk-3 S200 Separation System

 

[Dillinger]

ISRO is making steady progress towards the debut launch in April 2014 of its GSLV Mk-3 launcher, which will be capable of inserting a 10 ton spacecraft in low earth orbit.

It recently tested the separation system of the S200 strap on motors of the launchers from the core vehicle.

The first stage of the GLSV Mk-3 consists of two 200 ton, S200 solid rocket motors, strapped around the 110 ton restartable core liquid propellant second stage (L-110) using two Vikas engines.

The separation system consists of two joints viz fore end joint and aft end joint, which attaches the L110 stage of the core with S200 motors. The thrust developed by the S200 motors are transferred to the core vehicle through the fore end joint while the aft joint takes care of the lateral loads.

The S200 separation system is used to dump the two spent S200 motors at about 145 seconds after take off allowing the second stage to kick in.

The third stage of the GSLV Mk-3 would be an ISRO developed cryogenic rocket motor with a propellant loading of 25 ton (C-25).

The first flight of the Mk-3 will be a sub-orbital flight test, sans the cryogenic third stage.

ISRO Conducts Functional Qualification Test of GSLV Mk-3 S200 Separation System

Got any information on the cryo-third stage? Whats the status on that, any tests done yet?

 

[BlueDot_in_Space]

Got any information on the cryo-third stage? Whats the status on that, any tests done yet?

subsystem level tests, like turbo pumps, thrust chamber etc done. hopefully by end of this year engine integration and cold & hot tests will be completed.

 

[IND151]

ISRO is making steady progress towards the debut launch in April 2014 of its GSLV Mk-3 launcher, which will be capable of inserting a 10 ton spacecraft in low earth orbit.[probably with 4 boosters.]

It recently tested the separation system of the S200 strap on motors of the launchers from the core vehicle.

The first stage of the GLSV Mk-3 consists of two 200 ton, S200 solid rocket motors, strapped around the 110 ton restartable core liquid propellant second stage (L-110) using two Vikas engines.

The separation system consists of two joints viz fore end joint and aft end joint, which attaches the L110 stage of the core with S200 motors. The thrust developed by the S200 motors are transferred to the core vehicle through the fore end joint while the aft joint takes care of the lateral loads.

The S200 separation system is used to dump the two spent S200 motors at about 145 seconds after take off allowing the second stage to kick in.

The third stage of the GSLV Mk-3 would be an ISRO developed cryogenic rocket motor with a propellant loading of 25 ton (C-25).

The first flight of the Mk-3 will be a sub-orbital flight test, sans the cryogenic third stage.

ISRO Conducts Functional Qualification Test of GSLV Mk-3 S200 Separation System

Thanks for info

ISRO is making steady progress towards the debut launch in April 2014 of its GSLV Mk-3 launcher, which will be capable of inserting a 10 ton spacecraft in low earth orbit.

probably with 4 boosters.

I think GSLV Mk3 can insert 7200 KG payload in LEO and if we assume the boosters produce 40% of total power(20% for 1 booster), 1 booster can produce enough power for carrying 1400 kg payload

Which means adding 2 more boosters will incerase the payload carrying capacity by 2800KG

Thus 7,200 KG+2, 800 KG =10,000 KG

Note:these calculations are result of my guesswork and assumed 10,000 kg payload(conformed by OP)

@sancho @ANTIBODY @Penguin @Capt.Popeye @Safriz> please tell whether my guess is right or not

 

[BlueDot_in_Space]

Thanks for info




probably with 4 boosters.

I think GSLV Mk3 can insert 7200 KG payload in LEO and if we assume the boosters produce 40% of total power(20% for 1 booster), 1 booster can produce enough power for carrying 1400 kg payload

Which means adding 2 more boosters will incerase the payload carrying capacity by 2800KG

Thus 7,200 KG+2, 800 KG =10,000 KG

Note:these calculations are result of my guesswork and assumed 10,000 kg payload(conformed by OP)

@sancho @ANTIBODY @Penguin @Capt.Popeye @Safriz> please tell whether my guess is right or not

LVM3's payload projection under current configuration is: 10 ton (10,000 kg) to LEO and 4-5 ton (4000-5000 kg) to GTO

Now possible modifications and corresponding payload gain:

1) cryo stage twice restart capability, 500 kg gain
2) composite S200 boosters (currently marginal steel is used), 20%-40% weight savings will result into similar payload gain
3) Semi-cryo core stage (replace L110 with cryostage), 14-15 ton to LEO, 6-6.5 ton to GTO
4) Improvement in solid propellant grains will improve payload

We need to keep in mind that initial PSLV payload capacity was 800 kg that has increased to 1800 kg as of today. So one can also hope to see something similar with LVM3

 

[IND151]

LVM3's payload projection under current configuration is: 10 ton (10,000 kg) to LEO and 4-5 ton (4000-5000 kg) to GTO

Now possible modifications and corresponding payload gain:

1) cryo stage twice restart capability, 500 kg gain
2) composite S200 boosters (currently marginal steel is used), 20%-40% weight savings will result into similar payload gain
3) Semi-cryo core stage (replace L110 with cryostage), 14-15 ton to LEO, 6-6.5 ton to GTO
4) Improvement in solid propellant grains will improve payload

We need to keep in mind that initial PSLV payload capacity was 800 kg that has increased to 1800 kg as of today. So one can also hope to see something similar with LVM3

Thanks for info