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Weapons of Mass Destruction (WMD)


Taep'o-Dong-2 (TD-2)Design Evolution, Shahab-5, A,B, C/6

By © Charles P. Vick, 2005, ALL RIGHTS RESERVED

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.

Configuration Years TD-2, 2A
1994 (LRICBM)
TD-2A, 2A1
1997-98
SAT. Launcher
TD-2B
 2000
SAT. Launcher
TD-2C/TD-3
2001-2004
SAT. Launcher
Designation TD-2 TD-2A TD-2B TD-2C/TD-3
Taep'o-dong - series Taep'o-dong-2 Taep'o-dong-2A Taep'o-dong-2B Taep'o-dong-2C/3
Shahab - series Shahab-5 Shahab-5A Shahab-5B Shahab-5C
Launch point 40-degrees-51 minutes-17 seconds North 129 degrees-39 minutes-58 seconds East
Overall System
Type LRICBM LRICBM, Space booster ICBM, Space booster FRICBM, Space booster
Range (km) 3,500-6,400 5,632-6,700* 6,700-11,250* 10,000-12,000 + (15,000?)*
Stages 2, & 3 3 3 3
Satellite mass (kg) 100 +? 250* 250-550* Up to 550*
Warhead mass (kg) *, (5) 1st. gen. 1,158-760 -850 2nd. gen. 900-750 (760) 3rd.  gen. 650-500 3rd or 4th  gen. 650-240(300-200)
Total burn time (sec) 222 250, 256 317 341**
Mi Mass initial (kg)
2 stages
3 stages

~72,203.5
~72,027.5

~71,682.5
~72,050.


~77,840.25


~78,349.50
CEP (m)        
Final Velocity (m/sec.)       7,927.8-8980.for ICBM & 7,825-7,925 for orbital missions. 9,500-10,500 dv total with losses
Thrust/weight = gee's ~1.44 - 1.45 ~1.45 ~1.34 ~1.37
Diameter (m) 2.0 - 2.2 2.0 - 2.2 2.0 - 2.2 2.0 - 2.2
Height (m)
2 stages
3 stages

~33.37
~35.81

------
~35.81

------
~33.83


~35.8
Span across fins (m) ~4.41 ~4.42 ~4.42 ~4.42
Guidance (1) Inertial Inertial Inertial Inertial
Stage-1
Diameter (m) 2.0 -2.2 2.0 - 2.2 2.0 - 2.2 2.0 - 2.2
Height (m) ~17.83 ~17.8 ~17.8 ~19 -  logistic limits dimension
Mi Mass initial (kg) ~55,848. ~55,856. ~55,898. ~56,237.
Mf Mass final (kg)
2 stages
3 stages

~20,079.5
~19,903.5

~19,558.5
~19,926

--------
~26,649.75

?
~27,164.
Dry weight (kg) ~3,340. stage only. ~3,532. with 184 - 192 kg. inter-stage ~3,340. stage only. 3,532. with 192  - 200 kg. inter-stage ~3,340. stage only. 3,532. with 212 kg.  inter-stage ~4,000 stage only (4,125-4,415) with a 212 kg. inter-stage = 4,212.
Guidance Inertial inertial inertial Inertial
Thrust actual (kgf)** ~107,040. 107,040. 107,040. 107,400.
Thrust eff (kgf) Actual** 100 mt. plus ~104,257. 100 mt. plus 104,257. 100 mt. plus 104,257. 100 mt. plus 107,400.
Thrust/weight = gee's ~1.44 - 1.45 ~1.45-1.5 ~1.34 ~1.37
Steering (3) Four rotating vanes in the exhaust gas jet. (-4 to -5 sec. Isp. Loss) Four gimbaled mounted vernier rocket nozzles
Thrust chambers 4 4 4 4 main 4 verniers
dt Burn time (sec)** 112 112 112 ~130
Isp. Actual sea level SL (sec) *** 230** 230** 230** 269**
Isp eff. sea level SL (sec)*** 226** 226** 226** 269**
Isp spread (sec)*** 230-254** 230-254*** 230-254** 269-296**
Fuel** TM-185 20% Gasoline, 80% Kerosene TM-185 20% Gasoline, 80% Kerosene TM-185 20% Gasoline, 80% Kerosene UDMH
Oxidizer** AK-27I 27% N2O4 + 73% HNO3 with Iodium inhibitor Nitrogen Tetroxide & Nitric Acid AK-27I 27% N2O4 + 73% HNO3 with Iodium inhibitor Nitrogen Tetroxide & Nitric Acid AK-27I 27% N2O4 + 73% HNO3 with Iodium inhibitor Nitrogen Tetroxide & Nitric Acid IRFNA
Mp Mass of Propellants (kg) ~52,124. ~52,124. ~52,124. ~52,025.
Stage-2
Inter-stage mass )kg) 100 100 125 125
Diameter (m) 1.35 1.35 1.5 1.5
Height (m) stages ~15.54 12.95 10.82 10.82
Mi Mass initial (kg)**
1 Stage only
2 Staging, 2 stages
3 stages

15,192.
~16,335.5
~16,179.5

15,192.
~15,834.5
~16,194.


~19,106.50
~21,982.25


~19,106.50
~21,982.25
Mf Mass final (kg)**
1 Stage only
2 Staging, 2 stages

~3,537.5
~3,381.5

~2,871.5
~3,176.


~4,768.75


~4,845.
Dry weight (kg) 2,294 with 100 kg. inter-stage=2,304. 2,294 with 100 kg. inter-stage =2,394. ~2,146.75 +200 = 2346.75 inter-stage ~2,346.75 including the inter-stage
Burn out wt (kg) ~3,537.5 ~3,381.5 2,871.5, 3,176. ~4,768.75 ~4,845. 250 kg shroud dropped during 2nd. stage burn
Guidance inertial inertial inertial Inertial
Thrust actual (kgf)** ~32,031.72 ~32,031.72 - 29,600. 29,600.
Thrust effective kgf  **                            -~31,198.90 ~31,198.90 29,600. 29,600.
Thrust average overall (kg) n/a   29,600. 29,600.
Step-throttle thrust levels Step-1 (kgf) Step-2 (kgf) Although step-throttling was used by North Korea for the TD-1 attempted satellite launch that both stretched the range and the altitude in addition to achieving the required velocity it is not believed to have been designed into the TD-2 hardware.
Steering (4)** Four rotating vanes in the exhaust gas jet. (-3 to -4 sec. Isp. Loss) Four rotating vanes in the exhaust gas jet. (-3 to -4 sec. Isp. Loss) Four gimbaled mounted vernier rocket nozzles Four gimbaled mounted vernier rocket nozzles
Total burn time (sec)** 110 110 180 180
Spin up time (sec) ? ?    
Coast time (sec) ? ?    
Isp spread (Sec)*** 258 - 271** 258 - 271** 282-298** 288-298**
Isp eff Vac. (sec)*** 264** 264** 296** 296**
Isp Vac. (sec)*** 264** 264** 296** 296**
Fuel** TM-185 20% Gasoline, 80% Kerosene TM-185 20% Gasoline, 80% Kerosene UDMH UDMH
Oxidizer** AK-27I 27% N2O4 + 73% HNO3 with Iodium inhibitor Nitrogen Tetroxide & Nitric Acid AK-27I 27% N2O4 + 73% HNO3 with Iodium inhibitor Nitrogen Tetroxide & Nitric Acid IRFNA IRFNA
Mp Mass propellants (kg)** 12,798. 12,798. ~16,760.50 ~16,760.50
Mp Burn -1 See note See note See note See note
Mp Burn -2 See note See note See note See note
Flight Time (Sec)        
Minus shroud fairing at time Mass (kg) Time (sec) Warhead only 165 - 220 250 250
Stage-3
Description Identifiable Chinese Solid Motors using spin up technology prior to staging separation
Configuration Three stages Three stages Three stages Three stages
Diameter (m) 1.3 1.98 1.98 1.98
Height (m) 5.18 5.03 5.03 5.03
Satellite mass (kg) 100  + Up to 250* 250-550* Up to 550*
Mp Mass propellant Liquid or Solid (kg) Solid motor 200kg Solid motor 200-462 Solid motor 1,589. - 1,804. Liquid RCS & 1,588. Solid motor + 77.27 (19.31 structure + 57.96 propellant, bus storable propellant and maneuvering pkg.=1,665.25
Propellant type Solid-A Solid-A, A1 Solid-B Combination Bus  
Fuel/Oxidizer Solid motor Solid motor Solid motor Solid motor and Storable propellants
Burn time (sec) 28 28, 34 25, 28 25
Isp Actual (sec) 288 288-289 289 289
Dry Weight mass (kg) 22 22, 63 246 246+77.27=323.25 with bus storable propellant and maneuvering pkg.
Thrust Actual Vac. (kgf) 2,057.-2,064 3,869.82 18,354.89 18,354.89
Mi Mass initial (kg) ~987.5 ~477.5 - 782. ~2,422. ~2,498.28
Mf Mass final (kg) ~787.5 ~277.5, 320. ~833. ~910.27
Adapter mass (kg) 5.5 5.5, 7.0 37 37
Shroud mass (kg) 165 165-200-220 250 250 - dropped during 2nd. stage burn
Payload - Satellite  (kg)              -- Warhead (kg) Orbit Insertion Apogee, Perigee (km) 100-+ 1,150 - 760 Up to 250* 250-550* Up to 550* Up to 650*
Inclination (degrees) 40.8 - 41 40.8 - 41 40.8 - 41 40.8 - 41
Period (sec) ?      
Guidance Inertial Inertial Inertial Inertial-with GPS input at launch only


Notes

* All of the No-dong performance data came from Chinese, North Korea, Iran and Pakistan data released publicly that has allowed a more through analysis of the actual missile performance and open source data input from Israel, CIA & DIA etc.

** Based on comparative Russian data and rocket equations derived analysis results.

*** Known propellant performance and details. SL - Sea Level, Vac. Vacuum, Isp. Specific Impulse, ~ approximately
1. 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.
5. Nuclear Warhead Mass by Generation of Development.

Generation, Mass Range (Kg.)
1st Gen. 1,158-850 * 1,158 Iran, North Korea
2nd Gen. 900 -- 750 760 * Pakistan, North Korea
3rd. Gen. 750 -- 500 650 * North Korea, Iran
4th Gen. 500 -- 400
5th. Gen. 450 -- 240

*This is based on the 1st, 2nd. & 3rd. generation nuclear warheads of Pakistan.



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