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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