DRDO, PSU and Private Defence Sector News

[AMCA]

Isn't she a beauty?
View attachment 25398
The 450kg nozzleless booster used in SFDR will most probably end up being used in separate XR-SAM project instead. The SFDR will have its own variants.

Looks Good...........................................

 

[Arihant Roy]

Isn't she a beauty?
View attachment 25398
The 450kg nozzleless booster used in SFDR will most probably end up being used in separate XR-SAM project instead. The SFDR will have its own variants.

From where did you get the 450 kg figure for the booster? The entire missile with the booster probably weighs 450 kgs but I don't think the missile weighs more than 400 kgs.

The XRSAM will have a fatter diameter booster. The missile in all probability is going to be based on AAD.

 

[Kshithij]

Isn't she a beauty?
View attachment 25398
The 450kg nozzleless booster used in SFDR will most probably end up being used in separate XR-SAM project instead. The SFDR will have its own variants.

Just look at the diameter of the missile and diameter of the white pole of the shed nearby. Both are roughly at the same distance from the camera. I would say that SFDR is a thin missile. Akash missile is much thicker than SFDR and it weighs 720kg. You are saying that just the booster of SFDR weighs 450kg. That does not appear logical

 

[NeXoft007]

Just look at the diameter of the missile and diameter of the white pole of the shed nearby. Both are roughly at the same distance from the camera. I would say that SFDR is a thin missile. Akash missile is much thicker than SFDR and it weighs 720kg. You are saying that just the booster of SFDR weighs 450kg. That does not appear logical

SFDR weighs 250 kg and the booster weighs 450 kg.

 

[Arihant Roy]

SFDR weighs 250 kg and the booster weighs 450 kg.

Can you post the supporting documents? I guess you have got the weights from the tender issued by DRDO to supply the ground based launcher. I guess that's the max weight of missiles to be tested from the launcher. The booster in no way weighs anywhere close to 450 kgs.

 

[NeXoft007]

Another pic of SFDR-TD

 

[NeXoft007]

Can you post the supporting documents? I guess you have got the weights from the tender issued by DRDO to supply the ground based launcher. I guess that's the max weight of missiles to be tested from the launcher. The booster in no way weighs anywhere close to 450 kgs.

Sure it does, when the booster have both oxidizer and fuel inside it. The propellant is of heavier density to propel it to Mach 3.

Btw, that black booster isn't the nozzleless booster, it's Ground Launch Booster (GLB). The actual Nozzleless booster is inside the SFDR which isn't jettisoned and it's first-of-its-kind in India, unlike Akash Missile which jettisons its booster after 4 seconds.

The main reason of using dedicated booster was the nozzleless booster wasn't powerful enough to propel SFDR to Mach 3 from zero velocity and sea altitude

 

[ezsasa]

Sure it does, when the booster have both oxidizer and fuel inside it. The propellant is of heavier density to propel it to Mach 3.

Btw, that black booster isn't the nozzleless booster, it's Ground Launch Booster (GLB). The actual Nozzleless booster is inside the SFDR which isn't jettisoned and it's first-of-its-kind in India, unlike Akash Missile which jettisons its booster after 4 seconds.

The main reason of using dedicated booster was the nozzleless booster wasn't powerful enough to propel SFDR to Mach 3 from zero velocity and sea altitude

just curious...

in the production variant of this tech, how does ground launch and air launch take place for the initial boost?

 

[NeXoft007]

just curious...

in the production variant of this tech, how does ground launch and air launch take place for the initial boost?

Please be more specific, I can't even understand what are you trying to say.

 

[ezsasa]

Please be more specific, I can't even understand what are you trying to say.

The Ground Launch Booster that is seen in the pic, i am assuming that will not be there in production variant of this SFDR based missile. what will replace GLB?

 

[sthf]

We have the pictures now

Wallah!!!!

That is one hell of a sight. Thanks bro.

 

[abingdonboy]

Isn't she a beauty?
View attachment 25398
The 450kg nozzleless booster used in SFDR will most probably end up being used in separate XR-SAM project instead. The SFDR will have its own variants.

So any clarity on SDFR’s role? AAM?BVRAAM?

Or is it just a TD for XRSAM and a separate AAM project (Desi Meteor )?

 

[Kshithij]

So any clarity on SDFR’s role? AAM?BVRAAM?

Or is it just a TD for XRSAM and a separate AAM project (Desi Meteor )?

It was mentioned that the sole purpose was to test the ducted motor and its ability. Other tests will be done afterwards. So, it is a TD for use in future homing missile projects like SAM/AAM

 

[Vorschlaghammer]

A throttleable ducted rocket (TDR) is a variation of a solid propellant ram jet (RC) for which the fuel mass flow rate of the solid propellant can be controlled. This is realized in such a way that the propellant has an oxygen deficient formulation which produces fuel rich combustion products within the gas generator, which will be exhausted into the ram combustor. There, these products will be further combusted with the incoming air provided by the air intakes (AI). For a TDR it is very important to model the internal aerodynamics, including the two combustion processes within the gas generator and the ram combustor, very accurately as a significant part of the operational regime can not be covered by ground tests. Therefore, the complete TDR will be here subcategorized into its main components, which can be tested individually. These sub-models will be merged into a complete system afterwards. The overall performance prediction can then be given by modeling, with a limited number of flight tests used to validate the model under real conditions.

Meteor

https://en.wikipedia.org/wiki/Meteor_(missile)

The propulsion sub-system (PSS) is a Throttleable Ducted Rocket (TDR) with an integrated nozzleless booster, designed and manufactured by Bayern-Chemie. TDR propulsion provides a long range, a high average speed, a wide operational envelope from sea level to high altitude, a flexible mission envelope via active variable thrust control, relatively simple design, and logistics similar to those of conventional solid-fuel rocket motors.

The PSS consists of four main components: a ramcombustor with integrated nozzleless booster; the air intakes; the interstage; and the sustain gas generator. The PSS forms a structural component of the missile, the gas generator and ramcombustor having steel cases. The propulsion control unit electronics are mounted in the port intake fairing, ahead of the fin actuation subsystem.

The solid propellant nozzleless booster is integrated within the ramcombustor and accelerates the missile to a velocity where the TDR can take over. The reduced smoke propellant complies with STANAG 6016.

The air intakes and the port covers which seal the intake diffusors from the ramcombustor remain closed during the boost phase. The intakes are manufactured from titanium. The interstage is mounted between the GG and the ramcombustor and contains the Motor Safety Ignition Unit (MSIU), the booster igniter, and the gas generator control valve. The gas generator is ignited by the hot gases from the booster combustion which flow through the open control valve. The gas generator contains an oxygen deficient composite solid propellant which produces a hot, fuel-rich gas which auto-ignites in the air which has been decelerated and compressed by the intakes. The high energy boron-loaded propellant provides a roughly threefold increase in specific impulse compared to conventional solid rocket motors. When it enters service it will yield a no-escape zone more than three times greater than that of the current AIM-120 AMRAAM used by Eurofighter Typhoon-equipped airforces.

Thrust is controlled by a valve which varies the throat area of the gas generator nozzle. Reducing the throat area increases the pressure in the gas generator which increases the propellant burn rate, increasing the fuel mass flow into the ramcombustor. The mass flow can be varied continuously over a ratio greater than 10:1.

The Meteor PSS will be able to cope with high incidence and limited sideslip angles during manoeuvres but not negative incidences or large amounts of sideslip.

 

[NeXoft007]

The Ground Launch Booster that is seen in the pic, i am assuming that will not be there in production variant of this SFDR based missile. what will replace GLB?

Nothing. GLB could possibly find its utility in other SAM. It won't be there in SFDR BVRAAM.

 

[darshan978]

Well some interesting inside info about DRDO for last few years ..I was very sceptical for some reason the kind of articles which were getting published about DRDO as suddenly an organization which can pull miracles ..Looks like all this was done to get Extension for DRDO Chief Christoper ..Hope MoD kicks him out and also kicks his chellas and bring some competitive and non partisan people into DRDO






https://twitter.com/writetake/status/1001329536527515648

such guys i would call then termite, anti national selfish and dumb aholes

 

[Arihant Roy]

According to Mr Pubby, the test of SFDR was only partially successful. The booster stage performed without a hitch whereas the second stage failed to activate.

That is the ducted ramjet didn't even start operation.

https://m.economictimes.com/news/de...ccess-in-ramjet-test/articleshow/64423073.cms


Mr Manu Pubby is the official bearer of bad news it seems. How come he only gets to know that the missiles haven't performed as planned? And what about the credibility of the Govt report that the missile performed flawlessly??


Then there are multiple flaws in this article.

First, Meteor doesn't have a range of 300km.its somewhere north of 150-160 kms.

Secondly, Manu Pubby has improperly identified the nozzle less booster. He had said the booster failed to detach from the missile. Yet again he says that the nozzle less booster has performed meticulously. He doesn't know that the nozzle less booster that has been mentioned in the press release is inside the missile itself. It accelerates the missile to a sufficient speed before the ram jet engages. Unless the ground launch booster detaches from the missile after the launch there is no way in hell that the nozzle less booster will activate.

But the govt press release said the technology of nozzle less booster has been successfully tested. So either Drdo is lying OR Mr Pubby has no idea as to what he is saying

 

[Kshithij]

Yes, if one had read carefully, the article posted by @Prashant12 said:

“It was a booster phase test of the missile and the mission was a major milestone for the strategic missile programme. The nozzle less booster and SFDR were tested successfully. We can now master the technology which will boost several next-generation weapon systems,”

It was apparently only the test of nozzle less booster and not the SFDR itself. This makes sense as testing is done for every stage separately so as to be able to identify the problem easily. I guess, many of us missed this in excitement.

 

[Arihant Roy]

See, in the article it is stated that the nozzle less booster was tested successfully .

Now again it is said that the booster did not separate from the SFDR.
There are two boosters. The nozzle less booster is inside the SFDR . The booster you see in the pic isn't the nozzle less booster. Unless the booster seen in the pic detaches from the missile, the solid fuelled nozzle less booster inside the missile wouldn't start.

So for the nozzle less booster to perform successfully the other booster has to detach from the SFDR .but here the article mentions the booster didn't separate from the SFDR.

 

[cyclops]

GaN MMICs for X-Band radars on DRDO newsletter.