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S5.80

From Wikipedia, the free encyclopedia
Liquid pressure-fed rocket engine
S5.80
Country of originUSSR
Date1977-1986
First flight1986-05-21 (Soyuz TM-1)
DesignerOKB-2, Anton Tavzarachvili
ApplicationSpacecraft main propulsion
Predecessor11D426
StatusIn Production
Liquid-fuel engine
PropellantN2O4 /UDMH
Mixture ratio1.85
Cyclepressure fed
Configuration
Chamber1
Nozzle ratio153.8
Performance
Thrust, vacuum2.95 kN (660 lbf)
Chamberpressure0.88 MPa (128 psi)
Specific impulse, vacuum302 s (2.96 km/s)
Burn time890 seconds
Restarts30
Gimbal range±5°
Dimensions
Length1.2 m (47 in)
Diameter2.1 m (83 in)
Dry mass310 kg (680 lb)
Used in
Soyuz sinceSoyuz-TM andProgress sinceProgress-M
References
References[1][2][3][4]

TheS5.80 is aliquidpressure-fedrocket engine burningN2O4/UDMH with anO/F of 1.85. It is used for crew-ratedspacecraft propulsion applications. It is currently used in theSoyuz-TMA-M spacecraft propulsion moduleKTDU-80, and its sibling, theS5.79 rocket engine, is still used as the main propulsion of theZvezdaISS 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 aspecific 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).[4]

Versions

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This engine has been used with certain variations in thecrewedRussian space program since theSalyut 6 inSoviet times. The three main versions are:

  • 11D426: Used as the main orbit correction engine of theSoyuz-T it was part of the integrated propulsion moduleKTDU-426 which was the big innovation introduced with that series.[5] It enabled using fewer engines, increasing the reliability and reducing the weight of the spacecraft using a dual string redundant pressurization and propellant feed system for the main propulsion and thereaction control system. Since the latter could be used to de-orbit the spacecraft, it eliminated the need for backup orbital correction engine like theKTDU-35 required.[1][3][6]
  • S5.79 (AKAKRD-79): The orbit correction propulsion module of thesecond generation DOS stations, theSalyut-6 andSalyut-7 space stations, theMir Core Module and theZvezdaISS module. It was designed byKB KhIMMASH underRKK Energia specification based on the 11D426 design. It has improved life and restart capabilities, and is offered in a single compact unit. Each station has two of such engines.[1][7]
  • S5.80: An evolution of the 11D426 and S5.79 it is used on theKTDU-80 propulsion module that has been a staple of allSoyuz since theSoyuz-TM andProgress since theProgress-M. It has slightly reduced thrust but improved specific impulse, while improving engine life over the 11D426.[1][3][8]
Engine (SKD)11D426S5.79S5.80
Propulsion moduleKTDU-426KRD-79KTDU-80
Development1968–19741968-19771977–1986
Engine TypeLiquidpressure-fedrocket engine
Moduleintegratedspacecraft propulsion, pressurization and attitude control systemmain propulsion engineintegrated spacecraft propulsion, pressurization and attitude control system
PropellantN2O4/UDMH with 1.85 O/F ratio
Thrust (SKD)3.09 kN (690 lbf)3.09 kN (690 lbf)2.95 kN (660 lbf)
isp292 s (2.86 km/s)293.7 s (2.880 km/s)302 s (2.96 km/s)
Chamber Pressure0.88 MPa (128 psi)1.75 MPa (254 psi)0.88 MPa (128 psi)
Nozzle111
Expansion Ratio153.8
Burn time570s2700s890s
Ignitions407030
Mass270 kg (600 lb)38.5 kg (85 lb)310 kg (680 lb)
Length1,200 mm (47 in)840 mm (33 in)1,204 mm (47.4 in)
Diameter2,100 mm (83 in)550 mm (22 in)2,100 mm (83 in)
UsesSoyuz-TSalyut-6,Salyut-7,Mir Core Module,ZvezdaSoyuz-TMSoyuz-TMSoyuz-TMASoyuz-TMA-MProgress-MPirsPoisk
References[1][2][6][7][8][9][10]

See also

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References

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  1. ^abcde"Двигатели 1944-2000: Авиационные, Ракетные, Морские, Промышленные" [Aviadvigatel 1944-2000: Aviation, rocketry, naval and industry](PDF) (in Russian). pp. 75–81. Retrieved2015-07-25.
  2. ^abBrügge, Norbert."Spacecraft-propulsion blocks (KDU) from Isayev's design bureau (now Khimmash)". B14643.de. Archived fromthe original on 2015-06-02. Retrieved2015-06-02.
  3. ^abcPillet, Nicolas."Le système de propulsion du vaisseau Soyouz" [The propulsion system of the Soyuz spacecraft] (in French). Kosmonavtika.com. Retrieved2015-07-14.
  4. ^abRKK Energia (June 1999). "3.17. Комбинированная Двигательная Установка (КДУ) (Combined Propulsion System)".Soyuz Crew Operations Manual (SoyCOM) (ROP-19) Final. pp. 122–129 – via NASASpaceFlight.com.
  5. ^Chertok, Boris (May 2009). "Chapter 18 — Birth of the Soyuzes".Rockets and People Vol. 3 — Hot Days of the Cold War(PDF). Vol. 3 (NASA SP-2006-4110).NASA. p. 562.ISBN 978-0-16-081733-5. Retrieved2015-07-15.
  6. ^ab"KDU-426". Encyclopedia Astronautica. Archived fromthe original on May 23, 2002. Retrieved2015-07-25.
  7. ^ab"KRD-79". Encyclopedia Astronautica. Archived fromthe original on June 27, 2002. Retrieved2015-07-25.
  8. ^ab"KTDU-80". Encyclopedia Astronautica. Archived fromthe original on June 25, 2002. Retrieved2015-07-25.
  9. ^"Основные двигатели разработки КБХМ" [The main engines produced by KbKhA] (in Russian). Retrieved2015-07-25.
  10. ^McDowell, Jonathan."5.2: Russian engines". Jonathan Space Report. Retrieved2015-07-25.

External links

[edit]
Spacecraft engines and motors
Liquid fuel engines
Solid propellant motors
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