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KDU-414

From Wikipedia, the free encyclopedia
KDU-414
KDU-414 as seen on the "Russia in Space" exhibition (Airport Frankfurt, Germany, 2002)
Country of originSoviet Union
First flight1960
Last flight1974
DesignerAleksei Isaev
ManufacturerIsayev Design Bureau[1]: 72 
ApplicationAttitude Control & Mid-course corrections[1]: 46 
SuccessorKDU-414A
Liquid-fuel engine
PropellantIRFNA / UDMH[2]
Mixture ratio2.6
CyclePressure-fed[3]
Configuration
ChamberSingle chamber
Performance
Thrust, vacuum445.5 lbf / 202 kgf[4]
1.96 kN[1]: 46–47 
Thrust-to-weight ratio3.27
Chamber pressure1.18 MPa / 11.80 bar[5]
Specific impulse, vacuum272 s[5]
Burn time40 s[6]
Restarts2[4]
Propellant capacity77 lb / 35 kg
Dimensions
Length3.34 ft / 1.02 m[7]
Diameter2.42 ft / 0.74 m[7]
Dry mass134 lb / 61 kg[7]
Used in
Molniya satellites (First series)
Kosmos satellites
Mars 1
Venera 1
Zond 2
Zond 3

The KDU-414 (Russian Корректирующая Двигательная Установка, Corrective Propulsion Unit), is a pressure-fed liquid rocket Propulsion Unit developed and produced by the Isayev Design Bureau (today known as KhimMash).[1] From 1960 onward, it powered several unmanned Soviet Spacecraft, including the first series of Molniya satellites, several Kosmos satellites as well as the space probes Mars 1, Venera 1, Zond 2 and Zond 3,[5] featured as a part of standardized spacecraft buses known as KAUR-2, 2MV and 3MV.

The Corrective Propulsion Unit consists of a single chamber 'S5.19' liquid rocket engine and a conical thermal protection cowl containing the spherical propellant tank.[8] A barrier splits the tank into two separate compartments, filled with the propellant, UDMH, and the oxidizer, IRFNA, respectively. This combination of propellants is hypergolic, igniting on contact. The rocket motor is supplied with fuel by pressurizing the tank using gaseous nitrogen, which doubles as a source of RCS propellant. Elastic barriers within the tank prevent the nitrogen gas and propellant/oxidiser from mixing with each other.[5]

A gimbal mount allows the engine to swivel along two axes.[5]

In 1974, it was replaced with its derived successor, the KDU-414A with the S5.114 engine.

References

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  1. ^ a b c d Harvey, Brian (2007). Russian Planetary Exploration: History, Development, Legacy and Prospects. Springer Verlag, Praxis Publishing Ltd. ISBN 978-0387463438. Archived from the original on 2022-07-10. Retrieved 2022-07-10.
  2. ^ Brügge, Norbert. "Spacecraft-propulsion blocks (KDU) from Isayev's design bureau (now Khimmash)". Archived from the original on 23 July 2021.
  3. ^ V. M., Kudryavtseva (1993). Osnovy teorii i rascheta zhidkostnykh raketnykh dvigateley Kn. 2 - Fundamentals of the theory and calculation of liquid rocket engines - Book 2 Основы теории и расчета жидкостных ракетных двигателей Кн. 2. Moscow: Vysshaya Shkola. p. 20-21. ISBN 5060025632.
  4. ^ a b Reeves, Robert (2007). The Superpower Space Race: An Explosive Rivalry through the Solar System. Springer Verlag. p. 195. ISBN 978-0306447686. Archived from the original on 2022-07-10.
  5. ^ a b c d e Gluschko, V. P. (1985). Kosmonavtika Entsiklopediya - Cosmonautic Encyclopedia Космонавтика Энциклопедия (PDF). Moscow. p. 159. Archived (PDF) from the original on 11 July 2022.{{cite book}}: CS1 maint: location missing publisher (link)
  6. ^ T. Huntress, JR., Wesley; Ya Marov, Mikhail (2011). Soviet Robots in the Solar System: Mission Technologies and Discoveries. Springer Verlag, Praxis Publishing Ltd. p. 103. ISBN 978-1441978974. Archived from the original on 2022-07-10. Retrieved 2022-07-10.
  7. ^ a b c "KDU-414". astronautix.com. Archived from the original on 18 March 2022.
  8. ^ "Inventing The Interplanetary Probe". mentallandscape.com. Archived from the original on 8 April 2022.
[edit]
  • Media related to KDU-414 at Wikimedia Commons
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