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Weapons of Mass Destruction (WMD)


Paekdosan-1, Taep'o-dong-1 (TD-1)

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

3-23-07

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.

Specifications
U. S. Designation TD-1, Taep'o-dong-1
Designation Taep'o-dong-1
North Korean Name Paekdosan-1*
Launch Point 40 degrees, 51 min., 17 sec. North 129 degrees, 39 min., 58 sec. East
Overall System
Type IRBM
Range (km) 2,000
Stages 2, 3
Satellite Payload range (kg) 55-85
Mass Warhead (kg) 650-850-1,150
Total Burn time (sec.) 293*
Mass Initial gross (kg) 20,700 (20,615 satellite)
CEP (m) ?
Satellite Injection Alt. (km) 239.2*
Injection Range (km) 587.9*
Final Velocity (m/sec.) 8,980*
Diameter (m) 1.35*
Height (m) 26.52
Span across fins (m) ~2.74
Stage-1
Diameter (m) 1.35 body dia.*
Height (m) ~13.41
Mass Initial Mi (kg) 15,100 - 15,192 stage only*
Mi 850 kg warhead
Mi 1,150 kg warhead
Mi 50-85 kg satellite
1.21,220
2.21,522
3.20,615
Mf 1,150 kg warhead
Mf 850 kg warhead
Mf 50-85 kg satellite
1. 8,308
2. 8,610
3. 7,687
Dry weight (kg) 1,766.+100. = 1,866.
Guidance Inertial
Thrust Actual (kgf) 32,262 up rated**
Thrust Effective (kg f) 31,702 up rated**
Thrust/Weight = g's 1.54
Steering Four rotating vanes in the exhaust gas jet. (-4 to -5 sec. Isp. Loss)
Thrust Chambers 1
Burn Time (Sec.) 94 - 95*
Isp. Actual S. L. (sec.) 230*
Isp. Effective S.L. (sec.) 226*
Isp. spread (sec) 230-264-268*
Fuel TM-185 *** 20% Gasoline, 80% Kerosene
Oxidizer AK-27I*** 27% N2O4 + 73% HNO3 with Iodium inhibitor Nitrogen Tetroxide & Nitric Acid
Mass propellant (kg) 13,326.
Staging down range & Alt. (km) 19.5 down range & 35.9 altitude*
Down range impact (km) 25.3*
Materials Duplex - Low grade stainless Steel DLGSS*
Stage-2
Scud-B stage body with SAM-2 two setting step throttled Engine
Diameter, Height (m) 0.855 body dia.*
Height (m) ~8.99
Mass Initial (kg) 5,437.76 for satellite
Inter stage (kg) ~108
Mi (kg) 5,422.76 for satellite
Mi stage only (kg) 4,846 - 4873 (4,788 +75) Stage only 4,956
Mi (kg) 1. 6,027.76
2. 6,327.76
3. 5,422.76 satellite
Mf (kg) 1,491.76
Mf (kg) 1. 2,265.76
2. 2,556.76
3. 1,491.76 satellite
Mass Dry Weight (kg) 1,100 - 1,110 + 75 inter-stage
Guidance Inertial
Thrust average (kg f) 5,997.25 for 166 sec.*
Step throttle - two settings

8,354.57-8,378.45 (8,300 Kg f class)* First setting & 5,000 kg f second setting*

Thrust effective step-1 (kg f) 5,000 - 5,010
Burn times total (sec) 166* (171-172 total)
Burn-1 (sec.) 49*
Burn-2 (sec.) 117*
Coast spin up (sec.) 6*
Isp. Spread Actual vac. 258 - 268 - 271*
Isp. Effective vac. 263 - 264*
Fuel TM-185 * 20% Gasoline, 80% Kerosene
Oxidizer AK-27I* 27% N2O4 + 73% HNO3 with Iodium inhibitor Nitrogen Tetroxide & Nitric Acid
Mass Propellant Mp (kg) 3,771*
Mp Burn-1 (kg) 1,555*
Burn-2 (kg) 2,216*
Burnout weight (kg) 1,185
Flight Time (Sec.) 172* (266) 166 sec. burn total*
Minus Shroud at +95 sec.* (kg) (144 sec.) 49 seconds * 130 - 160*
Staging down spin up prior to 3rd stage
range & altitude (km) separation 450.5 & 449 down range*
Down range impact (km) 1,464*
Stage-3
(Identifiable Chinese Solid Motor) plus satellite
Diameter (m) ~1.14 shroud body dia.
Height (m) ~3.96
Satellite mass (kg) 55 - 85
Mass of Propellant (kg) 196.66
Propellants Solid Motor
Burn time (sec.) 25-27-28
Burn failure at (sec.) 25 *of 27/28 total observed (27 sec. to orbit after separation from second stage) burn de-orbited the satellite and solid motor or apparently something exploded in the process. Immediately before staging from the second stage the solid motor third stage must utilize a series of small solid motors to spin up the third stage while the 2nd. Stage also starts the spin up and satellite combination and also properly align itself for the orbit insertion firing while rotating about its center of gravity. There may also have been a small solid motor inside of the base of the satellite. The satellite is said to have been observed in space for 25 seconds after separation from the third stage if that is the correct interpretation of the events but clearly one or any number of these required processes went wrong catastrophically de-orbiting the third stage and satellite. The third stage firing was clearly observed. What actually went wrong is unclear from the available public information. There were parts of a debris field that did fly further down range and reenter. However the former DCI R. James Woolsey during the Clinton Administration has suggested that the Taep'o-dong-1 third stage never ignited during testimony on capital hill.
Start of burn (sec.) 266 sec. *
Isp. Actual (sec.) vac. 280*
Dry Weight Mass (kg) 19.6 - 23
Thrust Actual (kg f) vac. 2,039.43*
Mass initial Mi (kg) 216.26 stage only
Mass Final mf (kg) 110-10
Adapter (kg) 20.5
Payload (kg) 55-85
Start down range alt (km) 204
Orbit insertion down- range & altitude (km) 587.9 & 239.2*
Down range impact (km) 2,973*
Orbit data (km) 218.82 - 6,978.2 *
Period (min. & sec.) 165 mins 5 sec.*
Inclination (degrees) 40.8 - 41
Down range impact (km) 1,100 Variously estimated between 2,000-2,200-2,672-2,896 km. These are mathematical modeling estimates for 50-100-700 kg pay load or less. As the weapon pay load mass Down range within the nose cone air frame becomes smaller the warhead depending on a number impact of highly technical issues can become quite unstable during reentry above certain velocities. The nose cone airframe mass does exact a fixed payload penalty from the total payload mass available for the weapons payload mass.
Impact point unknown
Satellite Kwangmyongsong-l Payload (estimated data)
The satellite's structural design is a sub scale mathematical model version of the Chinese China-1 satellite which is apparently readily available in the public realm.
Diameter (m) 0.5-0.6
Length (m) 0.5-0.6
Mass (kg) 50-60
Frequency 27 Mhz.
Shroud jettisoned at 95 sec. 143 - 144*
Guidance Spin Stabilized
Total Package (kg) 481.76- 466.76
War head Mi. (kg) 1. 850 1. 1,071.76
2. 1,150 2. 1,371.76
3. 55-85 3. 306.76 Sat. minus shroud
4. 481.76
M final flight (kg) 1. 875.10
2. 1,175.10
3. 110.10

Notes :
North Korean satellite failed to insert its self into orbit due to solid motor rupture 25 seconds into burn effectively de-orbiting itself. See the No-dong-A and Scud-B data for further background input. *All of the known No-dong-A, & Taep'o-dong-1 performance data came from North Korean, Chinese, Iranian and Pakistan data released publicly that has allowed a more through analysis of the actual missile performance. **Based on comparative Russian data, rocket equations derived analysis results or known propellant performance and details.




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