Contents
Content
Norbert Brügge, Germany
Contents:
R-11 (8A61)
R-11M (8K11, Scud-A)
R-11MU
R-11M propulsion
Revised: 01.06.2015
R-17 (8K14, Scud-B)
R-17M (8K14M, Scud-C)
R-17 VTO
R-17 propulsion
Iranian Shahab-1 & -2
Iranian Qiam-1
Iraqi Al-Hussein / Al-Hijarah / Al-Abbas
R-17MU (8K14MU, Scud-D)
North Korean Hwasong-X
Rear of a Scud-B missile without jet vanes
Comparison between Scud-B and Scud-D
R-11M (Scud-A)
Hwasong-5
Shahab-2
R-17 (Scud-B)
Al-Hussein-1
R-17M
(Scud-C
Al-Abbas
Hwasong-6
R-17MU
(Scud-D
Qiam-1
Length total
10.604 m
11.164 m
10.944 m
12.264 m
13.244 m
11.166 m
11.166 m
10.500 m
12.406 m
Length without control unit/
warhead
7.441 m
7.444 m
7.444 m
8.764 m
9.740 m
7.894 m
7.894 m
7.894 m
9.134 m
Diameter (m)
0.88 m
0.88 m
0.88 m
0.88 m
0.88 m
0.88 m
0.88 m
0.88 m
0.88 m
T-1 /AK-20F
TM-185 /AK-27I
TM-185 /AK-27I
TM-185 /AK-27I
TM-185 /AK-27I
TM-185 /AK-27I
TM-185 /AK-27I
TM-185 /AK-27I
UDMH /AK-27
Kerosene /
80%HNO3
+20%N2O4
Kerosene /
73%HNO3
+27%N2O4
Kerosene /
73%HNO3
+27%N2O4
Kerosene /
73%HNO3
+27%N2O4
Kerosene /
73%HNO3
+27%N2O4
Kerosene /
73%HNO3
+27%N2O4
Kerosene /
73%HNO3
+27%N2O4
Kerosene /
73%HNO3
+27%N2O4
Hydrazine /
73%HNO3 +27%N2O4
Mass propellant (t)
3.411
3.759
3.759
4.337
5.205
4.337
4.337
4.337
5.732
Engine
S2.253 (8D511)
S5.2 (9D21)
S5.2 (9D21)
S5.2 (9D21)
S5.2 (9D21)
S5.2 (9D21)
S5.2 (9D21)
S5.2 (9D21)
Isayev
Thrust s.l. (kN)
81.4
132.1
132.1
132.1
132.1
132.1
132.1
132.1
149.9
Thrust vac (kN)
94.8
146.3
146.3
146.3
146.3
146.3
146.3
146.3
165.5
Isp s.l. (Ns/kg)
2148
2285
2285
2285
2285
2285
2285
2285
2354
Isp vac Ns/kg)
2501
2530
2530
2530
2530
2530
2530
2530
2599
Propellant
Burn time, nominal (sec)
90
65
65
75
90
75
75
75
90
Total vacuum impulse (MNs)
8.53
9.51
9.51
10.97
13.17
10.97
10.97
10.97
14.90
TM-185 fuel
Polymer Distillate: 56 % (+/- 1,5 %)
Light Oil Pyrolyse: 40 % (+/- 1 %) for the increase of the density and the resistance against the oxidation through oxygen
Trikrezol:
4 % (prevents the crystallization of water)
AK-27I oxidizer
Concentrated Nitric Acid: 69.8 - 70.2%
Di-nitrogen Tetroxide:
24 - 28%
Water:
1.3 - 2%
Iodium inhibitor:
0.12 -0.16%
Ignition is accomplished by a hypergolic start fuel designated TG-02 "Samin" filled into the fuel line at the main fuel valve. TG-02 consists of 50 percent Tri-ethyl Amine and 50 percent Xylidiene. The propellant fed system is a turbo pump driven by a bipropellant gas
generator using the main propellants. The start and shut down valves are one shot devices, actuated by pyrotechnic charges. For improving the accuracy the engine is equipped with mechanical controls for correct thrust level and mixture ratio. Tank pressurization is
performed by air stored in high-pressure bottles in the missile's tail section, which are heated by the turbine exhaust gases.
Contents:
R-11 (8A61)
R-11M (8K11, Scud-A)
R-11MU
R-11M propulsion
Revised: 01.06.2015
R-17 (8K14, Scud-B)
R-17M (8K14M, Scud-C)
R-17 VTO
R-17 propulsion
Iranian Shahab-1 & -2
Iranian Qiam-1
Iraqi Al-Hussein / Al-Hijarah / Al-Abbas
R-17MU (8K14MU, Scud-D)
North Korean Hwasong-X
Rear of a Scud-B missile without jet vanes
Comparison between Scud-B and Scud-D
R-11M (Scud-A)
Hwasong-5
Shahab-2
R-17 (Scud-B)
Al-Hussein-1
R-17M
(Scud-C
Al-Abbas
Hwasong-6
R-17MU
(Scud-D
Qiam-1
Length total
10.604 m
11.164 m
10.944 m
12.264 m
13.244 m
11.166 m
11.166 m
10.500 m
12.406 m
Length without control unit/
warhead
7.441 m
7.444 m
7.444 m
8.764 m
9.740 m
7.894 m
7.894 m
7.894 m
9.134 m
Diameter (m)
0.88 m
0.88 m
0.88 m
0.88 m
0.88 m
0.88 m
0.88 m
0.88 m
0.88 m
T-1 /AK-20F
TM-185 /AK-27I
TM-185 /AK-27I
TM-185 /AK-27I
TM-185 /AK-27I
TM-185 /AK-27I
TM-185 /AK-27I
TM-185 /AK-27I
UDMH /AK-27
Kerosene /
80%HNO3
+20%N2O4
Kerosene /
73%HNO3
+27%N2O4
Kerosene /
73%HNO3
+27%N2O4
Kerosene /
73%HNO3
+27%N2O4
Kerosene /
73%HNO3
+27%N2O4
Kerosene /
73%HNO3
+27%N2O4
Kerosene /
73%HNO3
+27%N2O4
Kerosene /
73%HNO3
+27%N2O4
Hydrazine /
73%HNO3 +27%N2O4
Mass propellant (t)
3.411
3.759
3.759
4.337
5.205
4.337
4.337
4.337
5.732
Engine
S2.253 (8D511)
S5.2 (9D21)
S5.2 (9D21)
S5.2 (9D21)
S5.2 (9D21)
S5.2 (9D21)
S5.2 (9D21)
S5.2 (9D21)
Isayev
Thrust s.l. (kN)
81.4
132.1
132.1
132.1
132.1
132.1
132.1
132.1
149.9
Thrust vac (kN)
94.8
146.3
146.3
146.3
146.3
146.3
146.3
146.3
165.5
Isp s.l. (Ns/kg)
2148
2285
2285
2285
2285
2285
2285
2285
2354
Isp vac Ns/kg)
2501
2530
2530
2530
2530
2530
2530
2530
2599
Propellant
Burn time, nominal (sec)
90
65
65
75
90
75
75
75
90
Total vacuum impulse (MNs)
8.53
9.51
9.51
10.97
13.17
10.97
10.97
10.97
14.90
TM-185 fuel
Polymer Distillate: 56 % (+/- 1,5 %)
Light Oil Pyrolyse: 40 % (+/- 1 %) for the increase of the density and the resistance against the oxidation through oxygen
Trikrezol:
4 % (prevents the crystallization of water)
AK-27I oxidizer
Concentrated Nitric Acid: 69.8 - 70.2%
Di-nitrogen Tetroxide:
24 - 28%
Water:
1.3 - 2%
Iodium inhibitor:
0.12 -0.16%
Ignition is accomplished by a hypergolic start fuel designated TG-02 "Samin" filled into the fuel line at the main fuel valve. TG-02 consists of 50 percent Tri-ethyl Amine and 50 percent Xylidiene. The propellant fed system is a turbo pump driven by a bipropellant gas
generator using the main propellants. The start and shut down valves are one shot devices, actuated by pyrotechnic charges. For improving the accuracy the engine is equipped with mechanical controls for correct thrust level and mixture ratio. Tank pressurization is
performed by air stored in high-pressure bottles in the missile's tail section, which are heated by the turbine exhaust gases.
