Russian manufacturer of rocket engines. Kuznetsov Design Bureau, Russia.
AKA: N D Kuznetsov; OKB276; SNTK imeni N. D. Kuznetsova.
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Associated Engines

11D52F Kuznetsov Lox/Kerosene rocket engine. 1961 kN. N1F 1965  B. Study 1965. As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t. Isp=347s. More...

11D51M Kuznetsov Lox/Kerosene rocket engine. 2843 kN. N1M 1965  A. Study 1965. As described in N1 improvement study, 1965. Huge modification of Block A engines  sea level thrust increased from 175 tonnes thrust to 250 tonnes. Isp=346s. More...

11D53F Kuznetsov Lox/Kerosene rocket engine. 612 kN. N1F 1965  V. Study 1965. As per N1 improvement study, 1965. Engine thrust increased and stretched propellant tanks resulting in 20% longer burn time. Isp=346s. More...

11D53M Kuznetsov Lox/Kerosene rocket engine. 735 kN. N1M 1965  V. Study 1965. As per N1 improvement study, 1965. Further increase in thrust of Block V engines. Isp=347s. Used on NIM 1965 launch vehicle. More...

11D52M Kuznetsov Lox/Kerosene rocket engine. 2745 kN. N1M 1965  B. Study 1965. As per N1 improvement study, 1965. Thrust increased to 280 tonnes per engine. Isp=330s. More...

11D51F Kuznetsov Lox/Kerosene rocket engine. 1918 kN. N1F 1965  A. Study 1965. As described in N1 improvement study, 1965. Block A engine thrust increased. Isp=331s. More...

NK15 Kuznetsov Lox/Kerosene rocket engine. 1544 kN. N1 stage 1 (block A). Development ended 1964. On the basis of NK9 the NK15 was developed for the N1 launcher. 30 were used on the Block A (Stage 1) of the N1. Isp=318s. First flight 1969. More...

NK15F Kuznetsov Lox/Kerosene rocket engine. 2180 kN. Development 19661972. Isp=350s. Engine had only a very short nozzle, the 24 engines around the periphery were to expand along a common central plug on the first stage of a studied N1 variant. More...

NK15V Kuznetsov Lox/Kerosene rocket engine. 1648 kN. Development ended 1964. Isp=325s. Developed from the NK9. 8 engines, featuring highexpansion nozzles, used on N1 Stage 2. First flight 1969. More...

NK15VM Kuznetsov lox/lh2 rocket engine. 1960 kN. N1 stage 2 (block B) replacement. Design 1972. Derivative of NK15 with kerosene replaced by hydrogen. Canceled before hottests. More...

NK19 Kuznetsov Lox/Kerosene rocket engine. N1 stage 4. Development ended 1964. Based on NK9 engine. Originally developed for the modernized second stage of the R9 (abandoned). Also to have been used on GR1 / 8K713 Stage 2. First flight 1969. More...

NK231 Kuznetsov turbofan engine. 226.5 kN. Tu160. Development ended 1992. Turbofan engine used in Tu160. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1980s. More...

NK21 Kuznetsov Lox/Kerosene rocket engine. N1 stage 3 (block V). Out of production. Based on NK9 engine. Propellants kerosene T1 / LOX. 4 engines used in N1 stage 3 (block V). Isp=318s. Used on N1 launch vehicle. First flight 1969. More...

NK39 Kuznetsov Lox/Kerosene rocket engine. 402 kN. N1F stage 3. Development ended 1971. Isp=352s. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1. More...

NK35 Kuznetsov lox/lh2 rocket engine. 1960 kN. Design 1972. Derivative of the NK15 with kerosene replaced by hydrogen. The engine was canceled before hottests. Proposed for the UR700M Mars booster in 1972, but this was not approved either. More...

NK33 LH2 Mod + 4 x LACE Kuznetsov air augmented rocket engine. 980.7 kN. N1MOK. Study 1974. Isp=430s. Ultimate derivative of NK9. Propellants changed to LH2/LOX, 16 x modified NK33 engines + 4 Liquid Air Cycle Engine Liquid Air/LH2 boosters. More...

NK31 Kuznetsov Lox/Kerosene rocket engine. 402 kN. Isp=353s. Upgraded version of engines for N1 stage 4, with multiple ignition capability and increased operational lifetime. Mothballed in 1974. Proposed for Black Colt launch vehicle in 1993. More...

NK33 Kuznetsov Lox/Kerosene rocket engine. 1638 kN. N1F, Kistler stage 1, Taurus II stage 1. Isp=331s. Modified version of original engine with multiple ignition capability. Never flown and mothballed in 1975 after the cancellation of the N1. Resurrected for Kistler, then for Taurus. More...

NK43 Kuznetsov Lox/Kerosene rocket engine. 1755 kN. N1F, Kistler stage 2. Design 1975. Isp=346s. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1. Resurrected for Kistler. More...

NK9 Kuznetsov Lox/Kerosene rocket engine. 441.3 kN. R9, GR1 stage 1. Isp=327s. Reached phase of stand testing in 1965, but then RD111 selected. Later planned for 1st Stage of GR1, but that rocket also cancelled. More...

NK9V Kuznetsov Lox/Kerosene rocket engine. 441.3 kN. N1 stage 2 / N1 stage 3 / R9 Stage 2. Developed for 2nd stage of the R9 ICBM (alternative to RD111 engine by OKB456). NK9 with increased expansion ratio. Isp=340s. First flight 1965. More...

NK9V11D53 Kuznetsov Lox/Kerosene rocket engine. 449 kN. N1 stage 3 (block V). Out of Production. Modification of NK9 engine for the N1 lunar rocket. May be identical to NK21 (stage 3). Isp=340s. More...

NK9V11D54 Kuznetsov Lox/Kerosene rocket engine. 392 kN. N1 stage 4 (block G). Out of Production. Modification of NK9 engine for the N1 lunar rocket. May be identical to NK19 (stage 4). Isp=340s. More...
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