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At a glance
DF-31larger figure on 1 of 2
UGM-133 Trident IIlarger figure on 1 of 2
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Length
Single source21.6 m (70 ft 10 in)[source]
Length
Single sourceConfiguration
| Specification | DF-31 | UGM-133 Trident II |
|---|---|---|
| Type | Intercontinental ballistic missile[source] | SLBM[source] |
| Place of origin | People's Republic of China[source] | United States[source] |
| In service | 2006 (DF-31), 2007 (DF-31A), 2017 (DF-31B)[source] | 1990–present[source] |
| Used by | People's Liberation Army Rocket Force[source] | United States Navy Royal Navy |
44 ft 6.6 in (13.579 m)[source]
Operational; DF-31
Single sourceOperational; DF-31A
Single source7,200–8,000 km (4,500–5,000 mi) (DF-31) 13,200 km (8,200 mi) (DF-31A)[source]
Operational; Full load (8x Mk5/W88)
Single sourceOperational; Full load (8x Mk5/W88) Reduced load (4x Mk5/W88)
Single sourceBars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Manufacturer | Academy of Rocket Motors Technology (ARMT)[source] | Lockheed Martin Space[source] |
|---|
| Unit cost | $30.9 million (1987 USD) ($87.6 million in 2025 dollars)[source] |
|---|
| Warhead | 425 kilotonnes of TNT (1,780 TJ)[source] | United States 1–8 Mk-5 RV / W88 (475 kt) or 1–12 Mk-4 RV/ W76-0 (100 kt) or 1–12 Mk-4A RV/ W-76-1 (90 kt) or Mk-7 RV/ W93 (planned) Single or multiple W76-2 (5–7 kt) United Kingdom Mk-4A RV/Holbrook (100 kt) Mk-7 RV/ A21 Astraea (planned)[source] |
|---|
| Engine | Solid-fuel rocket[source] | Three solid-fuel rocket motors; first & second stage – Thiokol / Hercules solid-fueled rocket; third stage – United Technologies Corp. solid-fueled rocket[source] |
|---|
| Flight altitude | Up to 1,200 km (750 mi)[source] | — |
|---|
| Guidance system | Astro-inertial guidance with BeiDou Navigation Satellite System[source] | MK 6 astro-inertial guidance[source] |
|---|
| Accuracy | 100 m CEP for silo launched and 150–300 m for TEL-launched.[source] | 100 m[source] |
|---|
| Launch platform | Silo, 8 axle TEL[source] | Ballistic missile submarine[source] |
|---|
| Produced | — | 1983[source] |
|---|
| Propellant | — | NEPE-75 : Nitrate ester , plasticized polyethylene glycol -bound HMX , aluminum , ammonium perchlorate[source] |
|---|
| Steering system | — | Single movable nozzle actuated by a gas generator[source] |
|---|
Full load (8x Mk5/W88): 4,100 nmi (4,700 mi; 7,600 km) Reduced load (4x Mk5/W88): 6,220 nmi (7,160 mi; 11,520 km)[source]