Iranian Shahab-1 / North Korean Scud-B
By © Charles P. Vick, 2005, ALL RIGHTS RESERVED
Feb. 27, 2007
| Specifications | |
|---|---|
| Design Bureau OKB | Makayev |
| Engine OKB | Isayev (KBKhM) |
| Engine Designation | 9D21 (R-11-30) Open Cycle, liquid Propellant rocket Engine. |
| Range (km) | 285-330 (300) |
| Minimum Range (km) | 50 |
| CEP (m) | 450 |
| CEP (m) for 50 km | 180 m in range 100 min azimuth |
| CEP (m) for 300km) | 610 m in range 35 min azimuth |
| Max. Altitude (km) | 24 km (to 50km): 86 km (up to 300km) |
| Diameter (m) | 0.855 |
| Height (m) | 11.184 (11.64-11.37 Depending on warhead size) |
| Span across fins (m) | 1.8 |
| Launch Weight - Mass (kg) | 5,862-5,950 |
| Body Material | Duplex low grade Stainless steel 1.9 mm thick |
| Stage Mass (kg) | 4,846 -4,873 – 4,877 |
| Dry Weight Mass (kg) | 1,100-1,110 minus Warhead (1,060 – 1,091 – 1,187 Actual figures) |
| Mass with Warhead (kg) | 2,076 |
| Flight Avionics Mass (kg) | 180 |
| Guidance | Strap-down inertial |
| Thrust (kg f) | 13,160 Effective 13,300-13,380 Actual |
| Thrust/Weight=gee's | 2.2-2.3 |
| Steering | Rotating vanes in the exhaust gas jet. (-4 to -5 sec Isp. loss) |
| Engine Mass (kg) | 120 |
| Thrust Chambers | 1 |
| Stages | 1 |
| Burn Time (sec) | 62-64-(65) |
| Flight Time (sec.) | 165 for 50 km; 313 for 300 km |
| Isp. (sec.) | 226 Effective at SL Due to steering vanes loss of 4-5 seconds Isp. |
| Isp. (sec.) Actual | 230 |
| Isp. (sec) Vac. | 264 |
| Max Velocity (m/sec.) | 1,500 |
| Velocity at Apogee (m/sec.) | 1,130 |
| Velocity of Impact (m/sec.) | 800 |
| Launch Preparation (min.) | 90 |
| Fuel | TM-185 20% Gasoline 80% Kerosene |
| Fuel Mass (kg) | 852 |
| Oxidizer | AK-27I 27% N204 (Nitrogen Tetroxide) 70% HN03 (IHN03) Nitric Acid wit Iodium Inhibitor |
| Oxidizer Mass (kg) | 2,919 |
| Propellant mass (kg) | 3,771-3,760 (gross) |
| Warhead (kg) | 987 – 1,000 |
| HE Nuclear Warhead (kg) | 1,016 |
| Chemical Warhead (kg) | 985 |
| HE – Frag Warhead (kg) | 989 |
Notes
SL - Sea Level, Vac. Vacuum, Isp. Specific Impulse 1. Based on Russian Scud-B users manuals data.
Disclaimer
The opinions and evaluations stated here in are only the authors and cannot be construed to reflect those of any Government agency, company, institute or association. It is based on public information, circumstantial evidence, informed speculation, declassified U.S. intelligence community documents, official Iranian, Pakistani and North Korean government documents and histories, oral histories, interviews and engineering analysis. As with all data regarding the Iranian, Pakistani and North Korean strategic space and ballistic missile programs, this analysis is subject to revision--and represents a work in progress.
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