Find a Security Clearance Job!

Weapons of Mass Destruction (WMD)


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.