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At a glance
Agni-IIIlarger figure on 0 of 3
DF-31larger figure on 3 of 3
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Length
Single source17 m[source]
Length
Single sourceConfiguration
| Specification | Agni-III | DF-31 |
|---|---|---|
| Speed | — | Up to 8.16 km/s (Mach 25)[source] |
| Type | Intermediate-range ballistic missile[source] | Intercontinental ballistic missile[source] |
| Place of origin | India[source] | People's Republic of China[source] |
| In service | Active[source] | 2006 (DF-31), 2007 (DF-31A), 2017 (DF-31B)[source] |
| Used by | Strategic Forces Command |
21.6 m (70 ft 10 in)[source]
Warhead weight
Single source2,490 kg[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
People's Liberation Army Rocket Force[source] |
| Designer | Defence Research and Development Organisation[source] | — |
|---|
| Manufacturer | Bharat Dynamics Limited[source] | Academy of Rocket Motors Technology (ARMT)[source] |
|---|
| Unit cost | ₹ 250 million (US$3 million) – ₹ 350 million (US$4 million)[source] |
|---|
| Warhead | Conventional, thermobaric , nuclear[source] | 425 kilotonnes of TNT (1,780 TJ)[source] |
|---|
| Engine | Multi-stage solid-propellant[source] | Solid-fuel rocket[source] |
|---|
| Propellant | Hydroxyl-terminated polybutadiene[source] | — |
|---|
| Flight altitude | > 450 km[source] | Up to 1,200 km (750 mi)[source] |
|---|
| Guidance system | Mid-course: RLG - INS + multi- GNSS Terminal: IIR homing, radar scene matching, ARH[source] | Astro-inertial guidance with BeiDou Navigation Satellite System[source] |
|---|
| Steering system | Flex-nozzle thrust vectoring (first and second stage)[source] | — |
|---|
| Accuracy | 40 m CEP[source] | 100 m CEP for silo launched and 150–300 m for TEL-launched.[source] |
|---|
| Launch platform | 8 × 8 transporter erector launcher Rail mobile launcher[source] | Silo, 8 axle TEL[source] |
|---|