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BBallistic missiles
At a glance
K-5 (ballistic missile)larger figure on 1 of 1
Rampage (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
Configuration
| Specification | K-5 (ballistic missile) | Rampage (missile) |
|---|---|---|
| Type | SLBM[source] | — |
| Place of origin | India[source] | Israel[source] |
| In service | Under development[source] | — |
| Designer | Defence Research and Development Organisation[source] | Elbit Systems , Israel Aerospace Industries[source] |
| Warhead | 2,000 kg (4,400 lb ) nuclear war-head |
Diameter
Single source306 mm (1.004 ft)[source]
Operational; Operational range
Single sourcerange of around
Single source5,000–8,000 km (3,100–5,000 mi)[source]
range of around 5,000–6,000 km (3,100–3,700 mi)[source]K-5 (ballistic missile) · Description · It is planned to have a range of around 5,000–6,000 km (3,100–3,700 mi).
Operational; Operational range
Single source150–250 km (93–155 mi)[source]
Warhead weight
Single source150 kg (330 lb)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
Multi- EFP[source] |
| Engine | Solid-fuelled[source] | Solid-propellant rocket[source] |
|---|
| Launch platform | Arihant-class submarines , S5-class submarines[source] | F-16 , F-15 , F/A-18E/F , Eurofighter Typhoon , IAI Kfir , Sukhoi Su-30MKI , SEPECAT Jaguar , MiG-29K[source] |
|---|
| Role | submarine-launched ballistic missile[source] | — |
|---|
| Source measurement | The K-5 is a submarine-launched ballistic missile. The missile consists of three separate stages and uses solid rocket propellant . It is planned to have a range of around 5,000–6,000 km (3,100–3,700 mi). The missile will be able to carry a payload weighing two tonnes. It is being developed to match the range of the Agni-V missile. It will be equipped on the Arihant-class submarines code named S4 .[source]K-5 (ballistic missile) · Description; only the objects and conditions stated in this passage On 12 September 2025, the Advanced Centre for Energetic Materials (ACEM) in Nashik conducted a static firing test of the second-stage motor developed under Project K5. The motor is a 10-tonne-class solid-propellant design measuring approximately 2.68 metres in length and 2.4 metres in diameter. Its composite motor case uses T700 carbon-fibre reinforcement with Epofine resin, while the propellant grain employs a nine-fin finocyl configuration of HD 1.3 composite propellant. The motor incorporates a pyrogen ignition system and a submerged, thrust-vectoring nozzle actuated by two electromechanical actuators.[source]K-5 (ballistic missile) · Development / Static testing of the second stage motor; only the objects and conditions stated in this passage The test was intended to characterise the motor's ballistic performance and verify the operation and safety margins of its major subsystems. Instrumentation comprising more than 250 measurement channels was used to acquire test data. The nozzle was commanded through approximately ±2° of movement, with actuator operation beginning 10 seconds after ignition. The recorded pressure and thrust profiles were reported to be consistent with pre-test predictions, indicating the expected motor performance during the static firing.[source]K-5 (ballistic missile) · Development / Static testing of the second stage motor; only the objects and conditions stated in this passage The motor was manufactured using a newly established 50-tonne-capacity cast-cure installation at ACEM, which employs hopper-based continuous casting for large propellant grains. The successful processing and subsequent firing provided a demonstration of the facility's capability for larger-class solid motors and was also the first reported test of this motor type at ACEM's refurbished static-test facility.[source]K-5 (ballistic missile) · Development / Static testing of the second stage motor; only the objects and conditions stated in this passage | — |
|---|
| Country of origin | India[source]Inventory Origin column; table 1, row 5, cell 2; revision 1373427941; retrieved 2026-10-02 | — |
|---|
| Used by | — | Israeli Air Force Indian Air Force Indian Navy[source] |
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| Detonation mechanism | — | Radio proximity fuze , Blast fragmentation[source] |
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| Propellant | — | Solid fuel[source] |
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| Flight altitude | — | 3,000–40,000 ft (910–12,190 m)[source] |
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| Guidance system | — | INS + Altimeter + GPS + Two-way Datalink[source] |
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| Accuracy | — | 10m CEP[source] |
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| Manufacturer | — | תעש מערכות ו אלביט מערכות מפעל מלמ של התעשייה האווירית[source]Named manufacturer organization |
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