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ForceTally · AI-generated illustration · Not a photograph · AI-generated · OpenAI output terms · Source ↗ · Modified
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At a glance
Hwasong-18larger figure on 1 of 1
R-36 (missile)larger figure on 0 of 1
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
estimated
Single source25 m (82 ft) (estimated)[source]
Length
Single sourceConfiguration
| Specification | Hwasong-18 | R-36 (missile) |
|---|---|---|
| Type | Intercontinental ballistic missile[source] | Intercontinental ballistic missile[source] |
| Place of origin | North Korea[source] | Soviet Union[source] |
| In service | 2023–present[source] | 1966–1979 (original variant) 1988–present (R-36M2 Voevoda variant)[source] |
| Used by | Korean People's Army Strategic Force[source] | Russian Strategic Rocket Forces |
R-36-O
Single source18,900 mm (740 in) - (R-36-O) 32,200 mm (1,270 in)[source]
three stage solid fuel rocket motor 100 tf (
Single sourcethree stage solid fuel rocket motor 100 tf (980 kN)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Manufacturer | North Korea[source] | Factory: Yuzhny Machine-Building Plant Developer: Yuzhnoye Design Office[source] |
|---|
| Produced | 2023–present[source] | — |
|---|
| No. built | Unknown[source] | — |
|---|
| Warhead | nuclear weapon , possibly MIRV[source] | Depending on variant (see variants). Newest (R-36M2), 10 × 550–750 kiloton MIRV warheads with a large amount of decoys and other penetration aids . Originally (R-36), 1 × 8–20 megaton warhead.[source] |
|---|
| Propellant | solid fuel[source] | N 2 O 4 / UDMH[source] |
|---|
| Flight altitude | 6,648 km (4,131 mi) (lofted trajectory)[source] | — |
|---|
| Launch platform | 9-axle transporter erector launcher[source] | Silo[source] |
|---|
| Hangul | 화성포-18형[source] | — |
|---|
| Hanja | 火星砲18型[source] | — |
|---|
| Lit. | Mars Artillery Type 18[source] | — |
|---|
| RR | Hwaseongpo-18hyeong[source] | — |
|---|
| MR | Hwasŏngp'o-18hyŏng[source] | — |
|---|
| Designed | — | From 1962[source] |
|---|
| Unit cost | — | $7,000,000[source] |
|---|
| Engine | — | Two or three (R-36MUTTKH and R-36M2) liquid fueled rocket stages First Stage: 1x RD-251 (R-36) 1x RD-251P (R-36P) 1x RD-251M (R-36-O) 1x RD-264 (R-36M) 1x RD-264 (R-36MUTTKh and R-36M2) Second Stage: 1x RD-252 (R-36) 1x RD-252 (R-36P) 1x RD-0228 (R-36M) 1x RD-0255 (R-36MUTTKh) 1x RD-0255 (R-36M2) Third Stage: 1x RD-864 (R-36MUTTKh) 1x RD-869 (R-36M2)[source] |
|---|
| Guidance system | — | Inertial, autonomous[source] |
|---|
| Accuracy | — | 220–1,300 m CEP[source] |
|---|