RD-0110

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RD-0110
Gas-generator
Configuration
Chamber4 main, 4 vernier thruster
Performance
Thrust, vacuum298.03 kN (67,000 lbf)
Thrust-to-weight ratio74.36[3]
Chamber pressure6.8 MPa (990 psi)
Specific impulse, vacuum325 s (3.19 km/s)
Burn time250 seconds
Dimensions
Length1,575 mm (62.0 in)
Diameter2,240 mm (88 in)
Dry mass408.5 kg (901 lb)
Used in
Molniya-M Block-I and on most Soyuz Block-I
References
References[4][5]

The RD-0110 (

attitude control for the stage. It has an extensive flight history with its initial versions having flown more than 64 years ago.[6][7][5]

History

RD-0105/RD-0109 development.[4][5][8][9] The engine had its debut flight on 10 October 1960, and the last Molniya flight was on 22 October 1967.[4][10]

For the crewed carrying Voskhod Block-I, a version of the engine that complied with the human rating 3K Regulations was needed. During 1963 OKB-154 developed this new version of the engine. Known with by the GRAU index 8D715P, the RD-0108 kept the same characteristics and performance of the RD-0107 while fully complying with the crew rating regulations.[11] This engine had its first flight on 16 November 1963, and last flew on 29 June 1976.[4][12]

For the

2.1b. It has flown over 1350 times, and accumulated more than 336,500 s of burn time and is still flown many times per year.[6]

Design

The RD-0110 was created in a period when KBKhA had just started to design rocket engines. After many studies, simplicity and reliability were the main drivers of the design. For this reason a single shaft integrating the LOX pump, the RG-1 pump and the turbine was chosen. To provide acceptable suction performance, the RD-0110 turbopump has a dual inlet design with back to back centrifugal impellers. This allows it to work at relatively low inlet pressures without requiring additional booster pumps. The turbine is driven by a fuel rich gas generator.[6] The ignition system for both the gas generator and the combustion chamber is done by pyrotechnic devices. The engine control is handled by a regulator, a throttle and a set of valves. It can throttle between 100% and 90.5%, with the option of 107% for a short time in emergencies.[3]

During development, combustion instability issues were observed. The problem was found to be intimately related to the injection system design. It was finally solved by developing an optimized bi-propellant centrifugal atomizer design. During certification testing, high frequency combustion instabilities at start up were still observed. Even though the start instabilities were relatively rare at 1 in 60 to 80, and only on acceptance bench, great effort was made to eliminate the issue. Thanks to acoustic studies and modelling, a solution was found. Six combustible longitudinal felt ribs were placed at the inner surface of the combustion chamber and this solved the issue permanently.[3]

The RD-0110 uses fuel as coolant for the

regenerative cooling system. As most other Soviet designs, it uses a corrugated metal construction for the cooling jackets. The thrust chamber and upper nozzle sections has the corrugated metal sandwiched between an inner and outer metal layers. The lower section of the nozzle has no external lining, exposing the corrugated jacket to save weight. All these sections use steel for construction. Given the extreme temperatures at the throat section, this part is made of copper alloy with milled channels and an external lining. A separate film cooling system is implemented though a different manifold and is injected though a circular slot upstream of the throat.[13]

Production

The RD-0107/0108/0110 engines are produced in the Voronezh Mechanical Plant.[1][5]

Versions

Modifications to the RD-0107 design have led to production of four distinct versions of the engine:

See also

References

  1. ^ a b "Liquid Rocket Engine". Voronezh Mechanical Plant. Archived from the original on 30 May 2015.
  2. ^ a b c d "RD-0107". Encyclopedia Astronautica. Archived from the original on 21 March 2002. Retrieved 29 May 2015.
  3. ^
    ISBN 978-1-56347-183-4
    . Retrieved 30 May 2015.
  4. ^ a b c d "RD0107, RD0108, RD0110. Molniya (8K78), Voskhod (8K78M), Soyuz (11A511У) launch vehicles". KBKhA. Archived from the original on 14 October 2011.
  5. ^ a b c d Zak, Anatoly (11 November 2020). "RD-0110". RussianSpaceWeb.com. Retrieved 27 November 2024.
  6. ^
    AIAA
    . July 2005. Retrieved 29 May 2015.
  7. ^ "R-7/Soyuz Data Sheet". Space Launch Report. Archived from the original on 6 August 2010.
  8. ^ "RD-0106". Encyclopedia Astronautica. Archived from the original on 20 March 2002. Retrieved 30 May 2015.
  9. ^ "RD0105. Luna (8K72) launch vehicle. RD0109. Vostok (8K72K) launch vehicle". KBKhA. Archived from the original on 23 November 2011. Retrieved 29 May 2015.
  10. ^ Pillet, Nicolas. "Liste des lancements Molnia" (in French). Kosmonavtika.com. Retrieved 30 May 2015.
  11. ^ "Part 9: Launchers for an Early Circumlunar Programme". Cosmopark.ru. Archived from the original on 25 September 2011.
  12. ^ Pillet, Nicolas. "Liste des lancements Voskhod" (in French). Kosmonavtika.com. Retrieved 30 May 2015.
  13. ISBN 978-1563476495
    .
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