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Al-Samoud (I)
Al-Samoud-II
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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-75M "Volchov" 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-75M (SAM) components, to be
incorporated into the Al-Samoud SRM. S-75M 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 (T-02).
The rocket motor of the Al-Samoud is a origin of the Isayev S2.720M
motor used in the second stage of the Soviet S-75M "Volchov".
The Isayev S2.720M
liquid propellant engine burns a hypergolic propellant mix. The oxidiser
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 engines produce a thrust rate between 2,075
kp and 3,500 kp (4,575 lbf and 7,715 lbf) thrust. |
