Nodong-1 - Technical Specifications
By (c) Charles P. Vick, 2004, ALL RIGHTS RESERVED
Senior Fellow Space Policy, Globalsecurity.org
NO-DONG-A, GHAURI-II, & SHAHAB-3, TECHNICAL DATA
|
Design Bureau OKB |
Makayev heritage |
|
Engine OKB |
Isayev (KBKhM) heritage, open cycle operation |
|
Engine Designation |
Scud heritage? |
|
Type |
MRBM |
|
Range (km) |
1,600-1,540-1,500*-1,400-1,350* |
|
CEP (m) |
190* (1) |
|
Diameter (m) |
1.32-1.35* |
|
Height (m) |
15.895-16 * |
|
Span across fins (m) |
~ 2.74 |
|
L. W. (kg) |
15,592,-15,742,-15,852-16,250* |
|
Stage Mass (kg) |
15,092 ** |
|
D. W. (kg) |
2,180** 2,156** |
|
Guidance |
Strap-Down to Inertial with GPS |
|
Thrust (kg f) |
Effective 26,051 (-709)** Actual 26,760 - 26,600** |
|
Thrust Chambers |
1* |
|
Thrust/Weight =Launch gee’s |
1.64 - 1.6 |
|
Steering |
Four rotating vanes in the exhaust gas jet. (-4 to -5 sec. Isp. Loss) |
|
Thrust Chambers |
1* |
|
Stages |
1* |
|
Burn Time (sec.) |
110-112 ** (2) |
|
Flight Time (sec.) |
|
|
Cut Off Velocity (m/sec.) |
~3,700-3,8,00 |
|
Isp. (sec.) |
Effective 226 – SL*** (3) Actual 230 –SL Effective 264 –vac.*** (4) |
|
Fuel |
TM-185 *** 20% Gasoline, 80% Kerosene |
|
Oxidizer |
AK-27I*** 27% N2O4 + 73% HNO3 with Iodium inhibitor Nitrogen Tetroxide & Nitric Acid |
|
Mass Prop. (kg) |
12,912** |
|
HE Nuclear Warhead (kg) |
650-500 |
|
Warhead (kg) |
500-650-760*-987-1,158* (All types) |
Notes:
* All of the No-dong performance data came from Iran
and Pakistan data released publicly that has allowed a
more through analysis of the actual missile performance.
** Based on comparative Russian data and rocket
equations derived analysis results.
*** Known propellant performance and details.
SL – Sea Level, Vac. Vacuum, Isp. Specific Impulse
1. Not excepted. Expected to be several 1,000 meters until
Aug. 2004 introduction of Inertial GPS based guidance
package with Chinese help.
2. Also based on other referenced information & discussions.
3. Due to vanes steering drag, Loss of 4-5 sec.
4. Losses at altitude amounting to perhaps 3-4 sec. vac.
Disclaimer
The opinions and evaluations stated here in are only the author= s 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.
