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Iraqi homemade Al-Samoud SRM
(Saddam Hussein's tactical LP surface-to-surface
missile)
Norbert Brügge, Germany
In 1993, Iraq began developing liquid-propellant
ballistic missiles with a declared range of 150 kilometres. A number
of static tests of missile engines were conducted. In October 1997,
Iraq carried out its first declared flight test of a Al-Samoud
(I) missile.
Al-Samoud was based on elements
of the Soviet S-75 "Dvina-M" surface-to-air missile (SAM). Iraqi homemade
Al-Samoud-II
evolved from original Al-Samoud (I)
liquid-engine missile, which had
a smaller diameter and less range than the Al-Samoud-II. The Al-Samoud-II
diameter was increased to 760 mm from the 500 mm of the original Al-Samoud.
The Al-Samoud-II missile program, begun in 2001. Thrust regulators,
gas generators and air pressure regulators are among other S-75 (SAM)
components, to be incorporated into the Al-Samoud SRM. S-75 autopilots
and other guidance and control items, such as gyroscopes, accelerometers,
inertial equipment and software were also imported or developed for
use with the Al-Samoud system.
Al-Samoud-II is a liquid fuel rocket with an oxidizer such as red fuming
Nitric Acid mix (AK-20K) and fuel such as hydrocarbons (TG-02). The
rocket motor of the Al-Samoud is a origin of the Isayev
S2.720 motor used in the second stage of the Soviet S-75 "Dvina-M".
The Isayev S2.720 liquid propellant engine burns a hypergolic
propellant mix. The oxidizer is either AK-20K fuming Nitric Acid melange
depending on the motor variant, comprising ~80% Nitric Acid and ~20%
N2O4 with an inhibitor additive. The fuel is TG-02, comprising 50% Isomeric
Xylidine, 48.5% Triethylamine and 1.5% Diethylamine. The S2.720
engine produce a thrust rate about 3,500 kp (7.700 lbf) thrust. |
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Al-Samoud (I)
Al-Samoud-II
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20 documented flight tests of Al-Samoud-II
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|
Fuel (TG-02) |
Oxidizer (AK-20K) |
Total |
Mix |
Burn time |
|
Vol. (l) |
= Vol. (kg) |
Vol. (l) |
= Vol. (kg) |
(kg) |
(kg) |
(sec) |
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23.08.2001
|
344 |
293.78 |
555 |
959.60 |
1,253.37 |
3.27 |
|
|
26.09.2001
|
357 |
304.88 |
613.5 |
1,060.74 |
1,365.62 |
3.48 |
|
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11.10.2001
|
381 |
325.37 |
612 |
1,058.15 |
1,383.52 |
3.25 |
|
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06.11.2001
|
376 |
321.10 |
611.5 |
1,057.28 |
1,378.39 |
3.29 |
|
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07.11.2001
|
375 |
320.25 |
604.5 |
1,045.18 |
1,365.43 |
3.26 |
|
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29.12.2001
|
369 |
315.13 |
600 |
1,037.40 |
1,352.53 |
3.29 |
|
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09.01.2002
|
370 |
315.98 |
600 |
1,037.40 |
1,353.38 |
3.28 |
|
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10.01.2002
|
367 |
313.42 |
596 |
1,030.48 |
1,343.90 |
3.29 |
|
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31.01.2002
|
367 |
313.42 |
600.5 |
1,038.26 |
1,351.68 |
3.31 |
|
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14.03.2002
|
370 |
315.98 |
598 |
1,033.94 |
1,349.92 |
3.27 |
|
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11.04.2002
|
370 |
315.98 |
604 |
1,044.32 |
1,360.30 |
3.31 |
|
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10.05.2002
|
398 |
339.89 |
632 |
1,092.73 |
1,432.62 |
3.21 |
|
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06.06.2002
|
386 |
329.64 |
636 |
1,099.64 |
1,429.29 |
3.34 |
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17.06.2002
|
387 |
330.50 |
632 |
1,092.73 |
1,423.23 |
3.31 |
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18.07.2002
|
376 |
321.10 |
612 |
1,058.15 |
1,379.25 |
3.30 |
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23.07.2002
|
376 |
321.10 |
620 |
1,071.98 |
1,393.08 |
3.34 |
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25.08.2002
|
375 |
320.25 |
607 |
1,049,50 |
1,369.75 |
3.28 |
80 |
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25.08.2002
|
375 |
320.25 |
614 |
1,061.61 |
1,381.86 |
3.31 |
82.4 |
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30.10.2002
|
375 |
320.25 |
612 |
1,058.15 |
1,378.40 |
3.30 |
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16.11.2002
|
374 |
319.40 |
612 |
1,058.15 |
1,377.54 |
3.31 |
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S2.720 engine test
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Al-Samoud test stand
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Missile |
Engine |
Thrust s.l. |
Isp s.l. |
Thrust vac |
Isp vac |
Propellant |
Burn time |
Flow rate |
Total Imp (vac) |
|
kN |
N*s/kg |
kN |
N*s/kg |
- |
tons |
sec |
t/sec |
MN*sec |
|
Al-Samoud (short) |
S2.720 |
34.3 |
2285 |
38.5 |
2569 |
TG-02/AK-20K
|
0.825 |
55 |
0.0150 |
2.12 |
|
Al-Samoud (long) |
S2.720 |
34.3 |
2285 |
38.5 |
2569 |
TG-02/AK-20K
|
1.020 |
68 |
0.0150 |
2.62 |
|
Al-Samoud-II |
S2.720 |
34.3 |
2285 |
38.5 |
2569 |
TG-02/AK-20K
|
1.380 |
82 |
0.0150 |
3.55 |
|
Vernier
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4.16
|
4.72
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0.0018 |
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Al-Samoud-II
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Al-Samoud motor
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Damaged Iraqi engine S2.720
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Rear of Al-Samoud-II
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Upper end of Fuel tank without
gyroscope plate
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