PA MLRS, Self Propelled and towed artillery [BM-11, Fatah-I GMLRS, Fatah-II] - News, Updates & Discussions
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Michael
VIP Member
I have a question:
What is the approximate equipment rate of fire adjustment drones in the Pakistan artillery units?
Currently, all artillery units of the PLAGF are equipped with fire adjustment drones, with an equipment rate of 100% ------ excluding individual-carried mortars.
Bilal
THINK TANK: CONSULTANT
Pretty sure it’s 100% or approaching that. The UAVs being used are Scout and Ranger being offered by GIDS.
Last edited:
Intervention-06
Registered Member
Why Pakistani SH-15 are not equipped with rooftop machine gun ?
Bilal
THINK TANK: CONSULTANT
Not needed. It’s not supposed to be near the front line.
Intervention-06
Registered Member
And against drone threats? **** I have sleepless nights after seeing the Ukraine-Russian Drone warfare - don’t want to know what Indians are preparing for the next round.
Samurai
Registered Member
At 0:47 you guys can see the airburst warheads exploding right before impact and the munitions are spreading. This is different from what we saw in the Fatah-IV test, where it was totally incendiary. So does PA has this kind of airburst warheads in its inventory just like in the video? In comparison I think airburst's spread is wider than the incendiary one.
avx._4884
Registered Member
View attachment 203604
Pakistan officially states the range of the FATAH-1 Guided Multiple Launch Rocket System (GMLRS) as 140 kilometers. This is the accepted and publicly confirmed operational range. However, published military specifications often represent the validated combat envelope rather than the absolute aerodynamic or kinematic capability of a missile.
This analysis does not claim access to classified information, nor does it suggest that the official figure is inaccurate. Instead, it is an engineering exercise using publicly available information, established rocket performance equations, and comparisons with broadly similar systems to estimate the missile's potential upper-bound kinematic performance.
Publicly Known Characteristics
Based on official imagery and publicly available information, the FATAH-1 is estimated to have the following characteristics:
Since detailed specifications have not been publicly disclosed, several engineering assumptions are necessary.
Step 1 – Estimated Propellant Mass Fraction
Modern 300 mm guided rockets typically devote approximately 62–68% of their launch mass to solid propellant.
Assuming:
The resulting Mass Ratio is calculated as 770 divided by 270, which is approximately 2.85. These values are estimates intended to represent a plausible modern tactical rocket configuration.
Step 2 – Specific Impulse
Modern composite solid propellants generally achieve a specific impulse of approximately 250 seconds. The corresponding effective exhaust velocity is found by multiplying specific impulse by standard gravity (250 multiplied by 9.81), which equals approximately 2450 meters per second. This is consistent with contemporary aluminized HTPB-based solid rocket motors.
Step 3 – Ideal Delta-V
Applying the Tsiolkovsky Rocket Equation, the ideal velocity increment (Delta-V) equals the effective exhaust velocity multiplied by the natural logarithm of the Mass Ratio. Fusing our parameters (2450 multiplied by the natural log of 2.85) yields an ideal Delta-V of approximately 2565 meters per second.
This represents the rocket's ideal velocity increment under vacuum conditions. Actual flight performance is lower because of gravity losses, atmospheric drag during powered flight, and energy expended on guidance and trajectory corrections. Applying representative losses typical of tactical solid rockets suggests a burnout velocity on the order of 2.0 to 2.3 kilometers per second.
Step 4 – Aerodynamic Considerations
The rocket equation alone cannot determine maximum range. Actual range depends on numerous undisclosed factors, including the aerodynamic drag coefficient, ballistic coefficient, burnout altitude, burnout flight angle, thrust profile, guidance corrections, atmospheric density, and structural flight limits.
A simple vacuum ballistic calculation would substantially overestimate range because atmospheric drag dominates the flight of large artillery rockets. Without a detailed six-degree-of-freedom trajectory model incorporating these parameters, the missile's maximum range cannot be calculated directly from Delta-V alone.
Step 5 – Estimated Upper-Bound Kinematic Range
Although an exact trajectory solution is not possible using publicly available data, comparison with modern guided rockets of similar size, estimated propulsion performance, and expected aerodynamic efficiency suggests that a maximum kinematic range on the order of approximately 175 to 185 kilometers appears physically plausible under favorable conditions. This estimate represents a theoretical upper-bound engineering assessment rather than a verified operational capability.
Why Is the Official Range 140 km?
Several engineering and operational factors can explain why the officially published range is lower than an estimated physical maximum.
1. Accuracy
Beyond the validated engagement envelope, Circular Error Probable (CEP) generally increases. Official specifications typically reflect the range at which required accuracy is consistently achieved.
2. Standard Combat Payload
Operational range is generally quoted using the standard service warhead rather than reduced-payload developmental configurations.
3. Reliability Margin
Operating below absolute aerodynamic limits reduces structural stress, improves reliability, and ensures consistent performance across varying environmental conditions.
4. Operational Qualification
Military range specifications typically represent the envelope that has been fully tested, validated, and accepted for operational use. They do not necessarily define the missile's absolute physical limit.
Comparison
The estimated range fits reasonably within the expected performance envelope of a modern 300 mm guided rocket employing contemporary composite solid propellant technology.
Conclusion
Based on first-principles rocket analysis, reasonable assumptions regarding propulsion performance, and comparison with analogous guided rocket systems, a maximum kinematic range on the order of 175–185 km appears physically plausible for a missile with the estimated characteristics of the FATAH-1.
Because critical parameters such as drag coefficient, thrust profile, structural limits, and guidance algorithms remain undisclosed, this figure should be regarded as an engineering estimate rather than a calculated or verified performance value.
The officially published 140 km range remains the only confirmed operational capability. This analysis is intended solely as an open-source engineering assessment based on publicly available information and should not be interpreted as evidence of undisclosed performance.
Constructive feedback, alternative calculations, or additional publicly available data from those with expertise in aerospace engineering, propulsion, or external ballistics are welcome.
Pakistan officially states the range of the FATAH-1 Guided Multiple Launch Rocket System (GMLRS) as 140 kilometers. This is the accepted and publicly confirmed operational range. However, published military specifications often represent the validated combat envelope rather than the absolute aerodynamic or kinematic capability of a missile.
This analysis does not claim access to classified information, nor does it suggest that the official figure is inaccurate. Instead, it is an engineering exercise using publicly available information, established rocket performance equations, and comparisons with broadly similar systems to estimate the missile's potential upper-bound kinematic performance.
Publicly Known Characteristics
Based on official imagery and publicly available information, the FATAH-1 is estimated to have the following characteristics:
| Diameter | 300 mm |
| Estimated Length | 7.3 to 7.6 meters |
| Estimated Launch Mass | 720 to 820 kg |
| Propulsion | Single-stage solid rocket motor |
| Guidance | INS and GNSS guidance with terminal corrections |
| Official Operational Range | 140 kilometers |
Since detailed specifications have not been publicly disclosed, several engineering assumptions are necessary.
Step 1 – Estimated Propellant Mass Fraction
Modern 300 mm guided rockets typically devote approximately 62–68% of their launch mass to solid propellant.
Assuming:
| Launch Mass | 770 kg |
| Propellant Mass | 500 kg |
| Dry Mass | 270 kg |
The resulting Mass Ratio is calculated as 770 divided by 270, which is approximately 2.85. These values are estimates intended to represent a plausible modern tactical rocket configuration.
Step 2 – Specific Impulse
Modern composite solid propellants generally achieve a specific impulse of approximately 250 seconds. The corresponding effective exhaust velocity is found by multiplying specific impulse by standard gravity (250 multiplied by 9.81), which equals approximately 2450 meters per second. This is consistent with contemporary aluminized HTPB-based solid rocket motors.
Step 3 – Ideal Delta-V
Applying the Tsiolkovsky Rocket Equation, the ideal velocity increment (Delta-V) equals the effective exhaust velocity multiplied by the natural logarithm of the Mass Ratio. Fusing our parameters (2450 multiplied by the natural log of 2.85) yields an ideal Delta-V of approximately 2565 meters per second.
This represents the rocket's ideal velocity increment under vacuum conditions. Actual flight performance is lower because of gravity losses, atmospheric drag during powered flight, and energy expended on guidance and trajectory corrections. Applying representative losses typical of tactical solid rockets suggests a burnout velocity on the order of 2.0 to 2.3 kilometers per second.
Step 4 – Aerodynamic Considerations
The rocket equation alone cannot determine maximum range. Actual range depends on numerous undisclosed factors, including the aerodynamic drag coefficient, ballistic coefficient, burnout altitude, burnout flight angle, thrust profile, guidance corrections, atmospheric density, and structural flight limits.
A simple vacuum ballistic calculation would substantially overestimate range because atmospheric drag dominates the flight of large artillery rockets. Without a detailed six-degree-of-freedom trajectory model incorporating these parameters, the missile's maximum range cannot be calculated directly from Delta-V alone.
Step 5 – Estimated Upper-Bound Kinematic Range
Although an exact trajectory solution is not possible using publicly available data, comparison with modern guided rockets of similar size, estimated propulsion performance, and expected aerodynamic efficiency suggests that a maximum kinematic range on the order of approximately 175 to 185 kilometers appears physically plausible under favorable conditions. This estimate represents a theoretical upper-bound engineering assessment rather than a verified operational capability.
Why Is the Official Range 140 km?
Several engineering and operational factors can explain why the officially published range is lower than an estimated physical maximum.
1. Accuracy
Beyond the validated engagement envelope, Circular Error Probable (CEP) generally increases. Official specifications typically reflect the range at which required accuracy is consistently achieved.
2. Standard Combat Payload
Operational range is generally quoted using the standard service warhead rather than reduced-payload developmental configurations.
3. Reliability Margin
Operating below absolute aerodynamic limits reduces structural stress, improves reliability, and ensures consistent performance across varying environmental conditions.
4. Operational Qualification
Military range specifications typically represent the envelope that has been fully tested, validated, and accepted for operational use. They do not necessarily define the missile's absolute physical limit.
Comparison
| System | Diameter | Official Range |
| M30 GMLRS | 227 mm | 84 km |
| ER GMLR | 227 mm | 150 km |
| A-100 | 300 mm | 100 km |
| FATAH-1 | 300 mm | 140 km |
| FATAH-1 (Estimated Upper-Bound Kinematic Potential) | 300 mm | 175 to 185 km (Estimated) |
The estimated range fits reasonably within the expected performance envelope of a modern 300 mm guided rocket employing contemporary composite solid propellant technology.
Conclusion
Based on first-principles rocket analysis, reasonable assumptions regarding propulsion performance, and comparison with analogous guided rocket systems, a maximum kinematic range on the order of 175–185 km appears physically plausible for a missile with the estimated characteristics of the FATAH-1.
Because critical parameters such as drag coefficient, thrust profile, structural limits, and guidance algorithms remain undisclosed, this figure should be regarded as an engineering estimate rather than a calculated or verified performance value.
The officially published 140 km range remains the only confirmed operational capability. This analysis is intended solely as an open-source engineering assessment based on publicly available information and should not be interpreted as evidence of undisclosed performance.
Constructive feedback, alternative calculations, or additional publicly available data from those with expertise in aerospace engineering, propulsion, or external ballistics are welcome.
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