Asian space-rocket liquid-propellant engines

last update: 11.09.2014

 

Engine

Chamb.

 Fuel
Flow
(Cycle)

Nozzle
area
Ratio

 Press.
Exp.
Ratio

Chamb.
Press.
(MPa)

Propellants

 Stage

Oxid.
Mix
 Rate

Thrust s.l.

Isp s.l.

Thrust vac.

Isp vac

Flow
 Rate
(t/sec)

Launcher

kN

sec

Ns/kg

kN

sec

Ns/kg

 China
 YF-2A 4xYF-1 4 Open C.       UDMH / AK-27S Core   1,019.9 239.5 2349 1,131.7 265.7 2606 0.4342 DF-3 missile
 YF-3 1       2nd         294.2 280 2746 0.1071 DF-4 missile
 YF-2B 4xYF-1A 4 Open C.       UDMH / N2O4 1st   1,101.2 242.5 2378 1,214.4 267.4 2622 0.4631 CZ-1D

YF-3A

  1 Open C.       2nd         320.2 286.9 2814 0.1138 CZ-1
 YF-21 4xYF-20 4 Open C. 10   7.1 UDMH / N2O4 1st 2.10 2,784.6 258.9 2539  3,001.0 279 2736 1.0968 FB-1, DF-5
 YF-21A 4xYF-20A 4 10   7.1 1st   2,804.0 260.6 2556  3,020.3 280.8  2754

 1.0968

DF-5A, CZ-2C, CZ-3
 YF-21B 4xYF-20B 4       1st 2.12 2,961.6 260.6 2556 3,190.0 280.8  2754

 1.1584

CZ-2, CZ-3, CZ-4
 YF-21C 4xYF-20C 4       1st 2.12 2,961.6 260.6 2556 3,190.0 280.8  2754

 1.1584

CZ-2, CZ-3, CZ-4
 YF-22 1 Open C.       2nd         686.5 286.9 2814 0.2440 FB-1, DF-5
 YF-22A 1       2nd         719.8 289 2834 0.2540 CZ-2C, CZ-3, CZ-4
 YF-22B 1       2nd 2.18       742.4 298  2922 0.2540 CZ-2, CZ-3, CZ-4
 YF-22E long nozzle 1 Open C.       2nd         784.5 303 2971

0.2640

CZ-2, CZ-3, CZ-4
 YF-23 (F) 4 -       Verniers  1.57       46.1 281.7 2762 0.0167 CZ-2D, CZ-3+, CZ-4A

YF-23 (B, C)

            47.2 296.8 2911 0.0162 CZ-2, CZ-3, CZ-4
 YF-20B  DaFY-5-1 1 Open C.       Strap-ons   740.4 260.4 2556 797.5 280.8  2754

0.2896

CZ-2E, CZ-3B
 YF-20C 1       CZ-2F; CZ-3B+, -3C
 YF-40 2         2nd         98.1  295 2893 0.0339 CZ-1D
 YF-40A 2 Closed C. 55   4.48 3rd 2.14       98.1 303 2971 0.0330 CZ-4A
 YF-40B 2

 

      3rd         100.8 306 3001  0.0336 CZ-4B, -4C
 YF-73 4 Open C. 40   2.55 LH2 / LOX 3rd 5.0       44.15 420 4119  0.0107 CZ-3
 YF-73+ 4 40   2.63 3rd 5.0       44.43  425 4168 0.0107 CZ-3+
 YF-75 2x1 Open C. 80   3.76 3rd 5.1       156.9 439.7 4312 0.0364 CZ-3A, -3B, -3C
 YF-75D 2x1 Expander 80     2nd 6.0       196.1 441 4325 0.0454 CZ-5
 YF-77 2x1 Open C. 49   10.2 1st 5.45

980.7

305.8

2999

1,372.9 428.1 4198 0.3270 CZ-5

YF-220

5x1 Open C.     10 1st  5.5

7,722.6

 ~315

3432

10,615.8 ~433 4246 2.5000 CZ-SHLV

YF-220 vac

1     10 2nd  5.5       2,156.1 439.7 4364 0.500 CZ-SHLV
 YF-100 1x2 Closed C. 48   18.0 Kerosene/LOX Strap-ons 2.6 2,410.6 300 2942 2,692.7 335.1 3286 0.8194 CZ-5
 YF-100 1 48   18.0

1st; Strap-ons

2.6 1,205.3 300 2942 1,346.4 335.1 3286 0.4097 CZ-5, CZ-7
 YF-115 1  Closed C.       2nd         176.5 330 3236 0.0545 CZ-6
 YF-115 1x2       2nd         353.0 330 3236 0.1090 CZ-7

YF-650

1x2 Closed C.     20 Strap-ons 2.6

6600.1

305.9

3000

7187.0 333.1 3267 2.2002 CZ-SHLV

YF-650

2x2     20 1st 2.6

13,200.5

305.9

3000

14,374.2 333.1 3267 4.4004 CZ-SHLV

 

Engine

Chamb.

 Fuel
Flow
(Cycle)

Nozzle
Area
 Ratio

 Press.
Exp.
Ratio

Chamb.
Press.
(MPa)

Propellants

Stage

Oxid
Mix
Rate

Thrust s.l.

Isp s.l.

Thrust vac.

Isp vac

Flow
 Rate
(t/sec)

Launcher

kN

sec

Ns/kg

kN

sec

Ns/kg

 Japan
 LE-3 1 Pressure       Aerozin50 / N2O4 2nd         53.4 290.2 2846  0.0187 NLV-I
 LE-5 1 Open C. 140   3.7 LH2 / LOX 2nd 5.5       103.0 450 4413  0.0233 H-I
 LE-5A 1 Expander 130   3.98 2nd 5.0       121.9 451.9 4432  0.0275 H-II
 LE-5B-1 1 Expander 110   3.57 2nd 5.0       137.0 447 4384  0.0313 H-IIA

LE-5B-2

1       2nd 5.0       137.5 448 4393 0.0313 H-IIA, H-IIB, H-III
 LE-7 1 Closed C. 52   14.4 1st 6.0 843.4 348.2 3415 1,079.2 445.6 4370  0.2470 H-II
 LE-7A (short nozzle) 1 Closed C. 39   12.1 1st 5.9 814.9 325.9  3196  1,073.8 429.4 4211 0.2550 H-IIA
 LE-7A (long nozzle) 2x1 Closed C. 51.9   12.1 1st 5.9 1,677.0 338.1 3316 2,191.2 441.7 4332 0.5058 H-IIB
 LE-X 2x1   37   12.1 1st 5.9 2,433.5 363 3560 2,896.0 432 4236 0.6836 H-III

MB-60 (LE-11)

1       13.9 2nd 5.8       266.9 467 4580 0.0583 H-III

MB-35

1       10.3 3rd         155.7 468 4589 0.0339  
 TBD 1         LNG / LOX 2nd          97.8  345  3383

 0.0298

GXLV

 

Engine

Chamb.

 Fuel
Flow
(Cycle)

Nozzle
Area
 Ratio

Exp.
Ratio

Chamb.
Press.
(MPa)

Propellants

Stage

Oxid.
Mix
Rate

Thrust s.l.

Isp s.l.

Thrust vac.

Isp vac

Flow
 Rate
(t/sec)

Launcher

kN

sec

Ns/kg

kN

sec

Ns/kg

 India
 Vikas 2 1 Open C. 13.9   5.25 UDMH / N2O4 Strap-ons 1.86 600.5 248 2432 680.5 281 2756 0.2469 GSLV
 Vikas 4 1 30.8   5.85 2nd 1.86

 

    725.0  296  2903  0.2498 GSLV, PSLV
 Vikas 2B 1 Open C. 13.9   5.25 UH25 / N2O4 Strap-ons 1.87 677.7 255 2501 765.4 288 2824 0.2710 GSLV+
 Vikas 4B 1 Open C. 30.8   5.85 2nd         804.5 302 2962 0.2717 GSLV+, GSLV Mk.2
 Vikas X 2x1 Open C.       1st  

1,785.8

305

2991

1,961.3 335 3285 0.5970 LVM3 (GSLV Mk.3)
 CE-7.5 (CUS) 1 Closed C. 200   5.8  LH2 / LOX 3rd 6.0        73.6 452  4433 0.0166 GSLV Mk.2
 CE-20 1 Open C. 100   6.0 2nd 5.05       200.6 443 4344  0.0462 LVM3 (GSLV Mk.3)

CE-60

1   80   12.0 2nd         600 444.2 4356 0.1377 ULV project
 LVS 2 Pressure       MMH/MON 4th          14.8 308 3020 0.0049 PSLV

SCE-200  (RD-810)

1 Closed C.     18.0 Kerosene / LOX 1st 2.65

1784.8

299.1

2933

1,999.6 335 3286 0.6180 ULV project

 

Engine

Chamb.

 Fuel
Flow
(Cycle)

Nozzle
Area
 Ratio

Exp.
Ratio

Chamb.
Press.
(MPa)

Propellants

Stage

 Fuel
Promotion
(Cycle)

Thrust s.l.

Isp s.l.

Thrust vac.

Isp vac

Flow
 Rate
(t/sec)

Launcher

kN

sec

Ns/kg

kN

sec

Ns/kg

 Iran*
 Nodong 1 Open C. 9.0      UDMH / AK-27 1st   284.4 247 2422 313.8 272.5 2672 0.1174 Safir-1
 LRE-4 2 Open C. 16.0     2nd         33.3 290 2844 0.0117 Safir-1
 Nodong+ 1 Open C. 9.0     UDMH / N2O4 1st   314.9 259 2540 348.3 286.5 2810 0.1240 Safir-1B
 Nodong++ 1  9.0     1st   374.8 273 2677 411.9 300 2942  0.1400 Safir-1C
 Nodong+ 4x1 9.0     1st   1,259.5  259  2540 1,393.3 286.5 2810 0.4959 Simorgh
 LRE-4+ 2 Open C. 16.0     2nd         35.4 296 2903 0.0122 Safir-1B
 LRE-4+ 4 16.0     2nd         70.8  296  2903 0.0244 Simorgh
 LRE-15+ 2 Open C.       2nd         147.5 300 2903 0.0501 Simorgh +
* estimated data
 

Engine

Chamb.

 Fuel
Flow
(Cycle)

Nozzle
Area
 Ratio

Exp.
Ratio

Chamb.
Press.
(MPa)

Propellants

Stage

Oxid.
Mix
Rate

Thrust s.l.

Isp s.l.

Thrust vac.

Isp vac

Flow
 Rate
(t/sec)

Launcher

kN

sec

Ns/kg

kN

sec

Ns/kg

 Korea (North)*
 Nodong 1 Open C. 9.0      UDMH / AK-27 1st   284.4 247 2422 313.8 272.5 2672 0.1174 Paektusan, Unha-1
 Nodong 4x1 9.0     1st   1,137.6 247 2422 1,255.2 272.5 2672  0.4697 Unha-2
 LRE-4 2 Open C. 16.0     2nd         33.3 290 2844 0.0117 Unha-1
 LRE-15 2 Open C. >10.9     2nd         141.3 290 2844 0.0497 Unha-2
 Nodong+  4x1 Open C.  9.0      UDMH / N2O4 1st   1,259.5 259 2540 1,393.3 286.5 2810  0.4959 Unha-3
 LRE-4+ 2 Open C. 16.0     3rd         35.4 296 2903 0.0122 Unha-3
 LRE-15+ 2 Open C. >10.9     2nd         147.5 300 2942 0.0501 Unha-3
* estimated data
 

Engine

Chamb.

 Fuel
Flow
(Cycle)

Nozzle
Area
 Ratio

Exp.
Ratio

Chamb.
Press.
(MPa)

Propellants

Stage

Oxid.
Mix
Rate

Thrust s.l.

Isp s.l.

Thrust vac.

Isp vac

Flow
 Rate
(t/sec)

Launcher

kN

sec

Ns/kg

kN

sec

Ns/kg

 Korea (South)
 LRE-15 1 Pressure        Kerosene / LOX 1st   128.3 218.0 2138 166.7 283.5 2780 0.0600 KSR-III
 LRE-75 4x1 Open C.       1st 2.209 2,616.3 261.6 2565 2,981.2 298.1 2923 1.0198 KSLV-II
 LRE-75 vac 1       2nd 2.209       788.6 315.4 3093 0.2550 KSLV-II

LRE-7

1       3rd         68.6 320 3138 0.0219 KSLV-II