YF-23 (rocket engine)

Last updated
YF-23E
Country of origin China
First flight1974-11-05
Designer Academy of Aerospace Liquid Propulsion Technology
Application Vernier engine
Associated LV Feng Bao 1, Long March 2, Long March 3 and Long March 4
StatusIn Production
Liquid-fuel engine
Propellant N2O4 / UDMH
Mixture ratio1.57
Configuration
Chamber4
Performance
Thrust (vacuum)47.1 kN (10,600 lbf)
Specific impulse (vacuum)297 seconds (2.91 km/s)
Burn time300s
Used in
Long March 2F, Long March 3A, Long March 3B, Long March 3C, Long March 4B and Long March 4C second stage.
References
References [1] [2] [3] [4]

The YF-23 is a liquid rocket vernier engine, burning N2O4 and UDMH. [5] It is used in along the YF-22 to form the YF-24 and YF-25 propulsion modules. [3] [6] [7] [8]

Contents

Versions

The basic engine has been used since the Feng Bao 1 rocket and has been the vernier propulsion of the Long March 2, Long March 3 and Long March 4 families second stage. [1] [9] [10]

Modules

This engine is bundled into modules along the YF-22 upper stage engine. [13] [14] [15] [16]

The relevant modules for second stage application are:

Related Research Articles

The Long March 1D was a member of China's Long March rocket family. During the 1990s CALT developed an improved version of the DF-4 to test the reentry vehicle warheads of the DF-31. They took advantage of this development and offered it as the Long March 1D for commercial application. The modifications included:

YF-73

The YF-73 was China's first successful cryogenic liquid hydrogen fuel and liquid oxygen oxidizer gimballed engine. It was used on the Long March 3 H8 third stage, running on the simple gas generator cycle and with a thrust of 44.15 kilonewtons (9,930 lbf). It had four hinge mounted nozzles that gimbaled each on one axis to supply thrust vector control and was restart capable. It used cavitating flow venturis to regulate propellant flows. The gas generator also incorporated dual heat exchangers that heated hydrogen gas, and supplied helium from separate systems to pressurize the hydrogen and oxygen tanks. The engine was relatively underpowered for its task and the start up and restart procedures were unreliable. Thus, it was quickly replaced by the YF-75.

The YF-75 is a liquid cryogenic rocket engine burning liquid hydrogen and liquid oxygen in a gas generator cycle. It is China's second generation of cryogenic propellant engine, after the YF-73, which it replaced. It is used in a dual engine mount in the H-18 third stage of the Long March 3A, Long March 3B and Long March 3C launch vehicles. Within the mount, each engine can gimbal individually to enable thrust vectoring control. The engine also heats hydrogen and helium to pressurize the stage tanks and can control the mixture ratio to optimize propellant consumption.

The RD-120 is a liquid upper stage rocket engine burning RG-1 and LOX in an oxidizer rich staged combustion cycle with an O/F ratio of 2.6. It is used in the second stage of the Zenit family of launch vehicles. It has a single, fixed combustion chamber and thus on the Zenit it is paired with the RD-8 vernier engine. The engine has been developed from 1976 to 1985 by NPO Energomash with V.P. Radovsky leading the development. It is manufactured by, among others, Yuzhmash in Ukraine.

The RD-0214 (GRAU Index: 8D811) is a rocket vernier engine burning N2O4 and UDMH in a gas generator cycle. It has four nozzles that can each gimbal 45 in plane to provide TVC to the RD-0212 propulsion module of Proton third stage. It is a revised version of the RD-0207.

The RD-0243 is a propulsion module composed of an RD-0244 main engine and a RD-0245 vernier engine. Both are liquid rocket engine, burning N2O4 and UDMH. The RD-0244 main engine operates in the oxidizer rich staged combustion cycle, while the vernier RD-0245 uses the simpler gas generator cycle. Since volume is at a premium on submarine launches, this module is submerged on the propellant tank. Its development period was from 1977 to 1985, having had its first launch on December 27, 1981. Originally developed for the RSM-54, it was used later for the Shtil'.

YF-20 Chinese rocket engine

The YF-20 is a Chinese liquid-fuel rocket engine burning N2O4 and UDMH in a gas generator cycle. It is a basic engine which when mounted in a four engine module forms the YF-21. The high altitude variation is known as the YF-22 is normally paired with the YF-23 vernier to form the YF-24 propulsion module for second stages. New versions when used individually for booster applications are called YF-25.

The FG-46 is a Chinese spin stabilized solid rocket motor burning HTPB. It was developed by China Hexi Chemical and Machinery Corporation for use in the Long March 2E on GTO missions. It first flew as a prototype SPTS-M14 on July 16, 1990 on the Badr A mission. It had its first commercial mission orbiting the AsiaSat 2 on November 28, 1995 and exactly one month later, on December 28 its second and last mission for EchoStar 1.

The CTS is an upper stage developed by the China Academy of Launch Vehicle Technology (CALT) to improve the performance of the Long March 2C to high LEO missions like SSO. The two stage LM-2 delivers the payload and stage to an elliptical orbit with the desired apogee and the CTS points the stack in the direction of the correct vector and activates the solid rocket motor (SRM) main engine to circularize it. It then dispenses the spacecraft and does a passivisation procedure.

The FG-47 is a Chinese solid rocket motor burning HTPB. It was developed by China Hexi Chemical and Machinery Corporation for use in the Long March 2C SD/CTS/SMA third stage. It had its inaugural flight on the Iridium-MFS demonstration mission on September 1, 1997.

S5.4

The S5.4, was a Russian liquid rocket engine burning TG-02 and AK20F in the gas generator cycle. It was originally used as the braking (deorbit) engine of the Vostok, Voskhod, and Zenit spacecraft, which later switched to solid engines.

The KTDU-35 was a Soviet spacecraft propulsion system composed of two liquid rocket engines, the primary, S5.60 (SKD) and the secondary S5.35 (DKD), fed from the same propellant tanks. Both engines burn UDMH and AK27I in the gas generator cycle. It was designed by OKB-2, the famous Isaev Design Bureau, for the original Soyuz programme.

The YF-1 was a Chinese liquid rocket engine burning N2O4 and UDMH in a gas generator cycle. It is a basic engine which when mounted in a four engine module forms the YF-2. It was used as the basis for developing a high altitude version known as the YF-3.

The FG-02 was a Chinese solid rocket motor burning Polysulfide. It was developed by China Hexi Chemical and Machinery Corporation for use in the Long March 1 third stage. It has a total nominal mass of 2,052 kg (4,524 lb), of which 1,806 kg (3,982 lb) is propellant load. It has an average thrust of 118 kN (27,000 lbf) with a specific impulse of 254 seconds burning for 38 seconds, with a total impulse of 4,500 kN (1,000,000 lbf). It used spin stabilization and a timing device to ignite in flight.

The FG-36 was a Chinese spin stabilized apogee kick motor burning HTPB. It was developed by China Hexi Chemical and Machinery Corporation for use in the Fengyun 2 satellite bus for insertion into GSO orbit.

The S5.80 is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It is currently used in the Soyuz-TMA-M spacecraft propulsion module KTDU-80, and its sibling, the S5.79 rocket engine, is still used as the main propulsion of the Zvezda ISS module. The S5.80 generates 2.95 kN (660 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 153.8 that enables it to achieve a specific impulse of 302 s (2.96 km/s). It is rated for 30 starts with a total firing time of 890 seconds. The engine, without the pressurization system or propellant tanks, weighs 310 kg (680 lb) and is an integrated unit that is 1.2 m (47 in) long with a diameter of 2.1 m (83 in).

A.M. Isayev Chemical Engineering Design Bureau

The A.M. Isayev Chemical Engineering Design Bureau, also known as KB KhimMash or just KBKhM, is a Russian rocket engine design and manufacturing company. It is located in the city of Korolyov. It started as the OKB-2 division of the NII-88 research institute, where A.Isaev directed the development of liquid rocket engines for ballistic missile submarines.

The RD-810 (РД-810) is a Ukrainian liquid propellant rocket engine burning LOX and Kerosene (RG-1) in a staged combustion cycle. It has a single combustion chamber that provides thrust vector control by gimbaling of the nozzle in two axis by +/- 8°. It is being designed in Ukraine by Yuzhnoye Design Bureau for the prospective first stage propulsion of the Mayak rocket family.

The RD-0255 is a propulsion module composed of an RD-0256 main engine and a RD-0257 vernier engine. Both are liquid rocket engine, burning UDMH in N2O4. The RD-0256 main engine operates in the oxidizer rich staged combustion cycle, while the vernier RD-0257 uses the simpler gas generator cycle. It was used on the R-36MUTTKh (GRAU:15A18) and R-36M2 (GRAU:15A18M). Subsequently, it has been in the Dnepr second stage and as of 2016 it is still in active service.

The RD-801 is a Ukrainian liquid propellant rocket engine burning LOX and Kerosene (RG-1) in a staged combustion cycle. It has a single combustion chamber that provides thrust vector control by gimbaling of the nozzle in two axis by +/- 6°. It is being designed in Ukraine by Yuzhnoye Design Bureau for the prospective first stage propulsion of the Mayak rocket family.

References

  1. 1 2 Norbert Bgügge. "Asian space-rocket liquid-propellant engines". B14643.DE. Archived from the original on 2015-07-17. Retrieved 2015-07-15.
  2. ↑ "Long March". Rocket and Space Technology. Retrieved 2015-07-08.
  3. 1 2 "YF-23". Encyclopedia Astronautica. Retrieved 2015-07-15.
  4. ↑ Sutton, George Paul (November 2005). "Liquid Rocket Propellant Engines in the People's Republic of China". History of Liquid Propellant Rocket Engines. AIAA. p. 873. ISBN   978-1563476495 . Retrieved 2015-07-15.
  5. ↑ Harvey, Brian (2004). "Launch Centers Rockets and Engines". China's Space Program — From Conception to Manned Spaceflight. Springer Science & Business Media. p. 232. ISBN   978-1852335663 . Retrieved 2015-07-15.
  6. ↑ "YF-22/23". Encyclopedia Astronautica . Retrieved 2015-07-15.
  7. ↑ "YF-22A/23A". Encyclopedia Astronautica. Retrieved 2015-07-15.
  8. ↑ "YF-25". Encyclopedia Astronautica. Retrieved 2015-07-15.
  9. 1 2 3 Norbert Bgügge. "YF rocket engine history". B14643.DE. Archived from the original on 2015-07-17. Retrieved 2015-07-15.
  10. ↑ Norbert Bgügge. "Propulsion FB-1". B14643.DE. Retrieved 2015-07-15.
  11. ↑ "Chapter 2 — General Description to LM-2E". LM-2E User's Manual. Issue 1999 (PDF). CASC. 1999. p. 2. Retrieved 2015-07-08.
  12. ↑ "Chapter 2 — General Description to LM-3B". LM-3B User's Manual. Issue 1999 (PDF). CASC. 1999. p. 2. Retrieved 2015-07-08.
  13. ↑ Norbert Bgügge. "Propulsion CZ-2, CZ-2C, CZ-2D". B14643.DE. Retrieved 2015-07-15.
  14. ↑ Norbert Bgügge. "Propulsion CZ-3, CZ-3A CZ-3B, CZ-3C". B14643.DE. Retrieved 2015-07-15.
  15. ↑ Norbert Bgügge. "Propulsion CZ-4A, CZ-4B, CZ-4C". B14643.DE. Retrieved 2015-07-15.
  16. ↑ Harvey, Brian (2013). "Chapter 3 — The Program". China in Space — The Great Leap Forward. Springer Science & Business Media. p. 87. ISBN   978-1461450436 . Retrieved 2015-07-15.
  17. ↑ "2.3 LM-3B and LM-3BE Launch Vehicles". LM-3A Series Launch Vehicle User's Manual. Issue 2011 (PDF). CASC. 2011. pp. 2–16. Retrieved 2015-07-08.


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