Ghatak and Rustom Indigenous UAV Programs

Photon Vish said:
H

Hammer for anti-ship ?

May be against OPV or under light ships but against frigate or greater ? Not at all.

We need 2*AMC mk2 dry engine based ghatak for anti ship.
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I am impressed! You mean this Ghatak to be used as an anti ship missile !!
With 2 engines I assume you imply near hypersonic kinetics..... and direct impact, like a m829 sabot?
 
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Rune said:
Lol Hammers can easily achieve mission kill against any frig/destroyer.
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Yeah, good luck going to the release range of hammer without being hammered by enemy SAM.

You need to achieve radar lock on warship to release the hammer, and if u are able to track ship then so she will.

And then SAM will chase you faster than you can go cold.

And if enemy is China(CBG), then even launching brahmos is hard, without being hit by enemy a2a in return (KJ-600 AWACS ).
AllStirFry said:
I am impressed! You mean this Ghatak to be used as an anti ship missile !!
With 2 engines I assume you imply near hypersonic kinetics..... and direct impact, like a m829 sabot?
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I have many impressive ideas😉, but world does not care about it 😔.
 
Barcid said:
We don't need a separate drone for anti ship. Ghatak will be able to carry both NASM MR and future Nirbhay based long range ashm
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Yeah we need, infact a bigger ghatak will be beneficial to IAF more than current ghatak if they thinks that China is bigger threat than Pakistan.

And obv for navy, ghatak even with NASM MR is very insufficient (and we dont even know if it can even fit it as 1100kg is maximum payload of ghatak , spreaded in 2 IWB.
 
Photon Vish said:
Yeah we need, infact a bigger ghatak will be beneficial to IAF more than current ghatak if they thinks that China is bigger threat than Pakistan.

And obv for navy, ghatak even with NASM MR is very insufficient (and we dont even know if it can even fit it as 1100kg is maximum payload of ghatak , spreaded in 2 IWB.
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The Ghatak if it can handle 2 600KG bomb can handle 2 NASM-MR. 2 NASM-MR is pretty decent. After all its not meant to be a heavy fighter, it cant carry like 6 of them. Its meant to support precision A-G and A-A in highly contested environments.

Is it confirmed that the ghatak has 2 seperate bays? where? the L&T EUAV might not even the the final form of the ghatak. Its called experimental for a reason.
 
lmaoxd said:
The Ghatak if it can handle 2 600KG bomb can handle 2 NASM-MR. 2 NASM-MR is pretty decent. After all its not meant to be a heavy fighter, it cant carry like 6 of them. Its meant to support precision A-G and A-A in highly contested environments.
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Max payload is 1100kg. Most probably it will exclude pylons, as a2g and a2a have different pylons.

So at max, it should be able to only take 2*500kg glide bombs.
lmaoxd said:
Is it confirmed that the ghatak has 2 seperate bays? where? the L&T EUAV might not even the the final form of the ghatak. Its called experimental for a reason.
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It's theoretically impossible to have single weapon bay with engine in center which feeds air with an serpentine air intake.

Engine will occupy all the volume on center, while side will have good volume.
 
Photon Vish said:
Max payload is 1100kg. Most probably it will exclude pylons, as a2g and a2a have different pylons.

So at max, it should be able to only take 2*500kg glide bombs.

It's theoretically impossible to have single weapon bay with engine in center which feeds air with an serpentine air intake.

Engine will occupy all the volume on center, while side will have good volume.
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IC then idk. it might not be able to carry the NASM MR But I think they could modify the bay enough for give it another 50kg per bay. Idk. lets see
 
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Gautam said:
Mini Ghatak will have 2 variants with CCA capabilities:
View attachment 53699
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AI Feasibility Study: Using Twin NJ-50s for Variant-2​

This assessment evaluates the feasibility of powering the 200 kg All-Up Weight (AUW) flying wing drone using two NJ-50 (50 kgf) static thrust micro-turbojet engines.

Code: 
                              +---------------------------------------+
                              |         AUW: 200 kg (~1,962 N)        |
                              +-------------------+-------------------+
                                                  |
                                                  v
                              +---------------------------------------+
                              |Twin Engine Thrust: 2x 500 N = 1000 N  |
                              |            (T/W = ~0.51)              |
                              +-------------------+-------------------+
                                                  |
           +--------------------------------------+--------------------------------------+
           |                                      |                                      |
           v                                      v                                      v
+-----------------------+              +-----------------------+              +-----------------------+
| Strategic Performance |              | Internal Volume Alloc |              | Struct & Yaw Integ.    |
| - Meets >5 km ceiling |              | - Fuel mass: ~60 kg   |              | - Twin 175mm ducts    |
| - Sustains >0.4 M     |              | - Payload & Avionics: |              | - Yaw control via     |
| - Handles 2.5g turns  |              |   ~118 kg             |              |   differential thrust |
+-----------------------+              +-----------------------+              +-----------------------+

Performance Metrics & Flight Envelope
  • Thrust-to-Weight Ratio (T/W): The twin engines yield 1000 N of combined static thrust. At an AUW weight force of 1962 N, T/W ≈ 0.51. This ratio provides sufficient power for unassisted ground roll/catapult launch, high climb rates, and operating above the >5 km altitude target.
  • Maneuverability (2.5 g): Induced drag increases exponentially during pull-up and banking maneuvers. A T/W of 0.51 provides the excess thrust necessary to prevent rapid airspeed decay when pulling 2.5 g.
  • Maximum Speed (>0.4 M): The combined static thrust offsets parasitic and wave drag at high subsonic speeds (cruising at Mach 0.4 requires approximately 136 m/s at sea level).

Weight Budget and Specific Fuel Consumption (SFC)
  • Propulsion System Weight: 2 x 5.5 kg = 11 kg dry engine weight. Including starters, accessories, and dual fuel pumps, total propulsion unit weight is ≈ 15 to 18 kg (~9% of total AUW).
  • Fuel Requirements & Endurance: At maximum continuous thrust (1000 N combined), the fuel consumption rate calculated using the 0.12 kg/N·h SFC specification is 120 kg/h. At cruise settings (≈ 400 N total thrust required), burn rate drops to ≈ 48 kg/h.
  • Range Realization: Carrying 60 kg of fuel (30% of total AUW) provides approximately 1.25 hours of cruise endurance. At Mach 0.4 (≈ 490 km/h airspeed), a range exceeding 600 km is feasible if operating at high altitudes (>5 km) where lower ambient density decreases fuel burn.

Integration & Aerodynamic Considerations
  • Package Integration: With a 175 mm maximum diameter, twin engines fit directly within the central root thickness of a 2.6 m wingspan flying wing without creating excessive nacelle drag.
  • Flight Control Advantage: Tailless flying wings lack a conventional rudder. Placing two engines off-center allows the Flight Control Computer (FCC) to use differential thrust for active yaw stabilization and roll-yaw decoupling.
 
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