Propulsion Unha-2 & Unha-3


     
Clustering of four Nodong engines



Third stage LRE 4 combustor (left)
and small homemade steering engine for the first stage (right),
used in pressure-fed mode (!?)



Unha second stage engien LRE-X combustor ? (shown in Iran)



This debris of Unha-3-#2 shows probably the propellant tanks for the steering engines

 

Unha-2

Engines

Thrust s.l.

Isp s.l.

Thrust vac

Isp vac

Propellant

Burn time

Flow rate

Total Imp

kN

N*s/kg

kN

N*s/kg

 

 tons

s

t/s

MN*s

1

 Nodong   (4)

1,137.6

2422

1,252.9

2667

 UDMH/AK-27

56.36

120

0.4696

150.3

Vernier (4)

40.0

1961

44.0

2157

 ?

1.22

60

0.0204

 2.6

2

 LRE-X  (4)

 

 

125.0

2501

 UDMH/N2O4

11.0

220

0.0500

28.1

Vernier (4)

 

 

10.0

1863

 ?

0.32

60

0.0054

 0.6

3

 KM (solid)

 

 

19.1

2452

 solid

0.86

110

0.0078

2.1

 

Unha-3#2

Engines

Thrust s.l.

Isp s.l.

Thrust vac

Isp vac

Propellant

Burn time

Flow rate

Total Imp

kN

N*s/kg

kN

N*s/kg

 

 tons

s

t/s

MN*s

1

 Nodong+  (4)

1,192.8

2540

1,303.3

2775

 UDMH/N2O4

56.36

120

0.4696

156.4

Vernier (4)

40.0

1961

44.0

2157

 ?

1.22

60

0.0204

 2.6

2

 LRE-X  (4)

 

 

125.0

2501

 UDMH/N2O4

10.0

200

0.0500

25.6

Vernier (4)

    

10.0

1863

?

0.32

60

0.0054

 0.6

3

 LRE-4+  (2)

 

 

35.4

2844

 UDMH/N2O4

3.05

245

0.0124

8.7

 

Unha-3#3

Engines

Thrust s.l.

Isp s.l.

Thrust vac

Isp vac

Propellant

Burn time

Flow rate

Total Imp

kN

N*s/kg

kN

N*s/kg

 

 tons

s

t/s

MN*s

1

 Nodong+  (4)

1,192.8

2540

1,303.3

2775

 UDMH/N2O4

56.36

120

0.4696

156.4

Vernier (4)

40.0

1961

44.0

2157

 ?

1.22

60

0.0204

 2.6

2

 LRE-X  (4)

 

 

125.0

2501

 UDMH/N2O4

11.0

220

0.0500

28.1

Vernier (4)

    

10.0

1863

 ?

0.32

60

0.0054

 0.6

3

 LRE-4+    (2)

 

 

35.4

2844

 UDMH/N2O4

3.05

245

0.0124

8.7

 

Verniers: probably pressure-fed mode