 KDU-414 as seen on the "Russia in Space" exhibition (Airport Frankfurt, Germany, 2002) | |
| Country of origin | Soviet Union |
|---|---|
| First flight | 1960 |
| Last flight | 1974 |
| Designer | Aleksei Isaev |
| Manufacturer | Isayev Design Bureau[1]: 72 |
| Application | Attitude Control & Mid-course corrections[1]: 46 |
| Successor | KDU-414A |
| Liquid-fuel engine | |
| Propellant | IRFNA / UDMH[2] |
| Mixture ratio | 2.6 |
| Cycle | Pressure-fed[3] |
| Configuration | |
| Chamber | Single chamber |
| Performance | |
| Thrust, vacuum | 445.5 lbf / 202 kgf[4] 1.96 kN[1]: 46–47 |
| Thrust-to-weight ratio | 3.27 |
| Chamber pressure | 1.18 MPa / 11.80 bar[5] |
| Specific impulse, vacuum | 272 s[5] |
| Burn time | 40 s[6] |
| Restarts | 2[4] |
| Propellant capacity | 77 lb / 35 kg |
| Dimensions | |
| Length | 3.34 ft / 1.02 m[7] |
| Diameter | 2.42 ft / 0.74 m[7] |
| Dry weight | 134 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
- ^ 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.
- ^ Brügge, Norbert. "Spacecraft-propulsion blocks (KDU) from Isayev's design bureau (now Khimmash)". Archived from the original on 23 July 2021.
- ^ 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.
- ^ 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.
- ^ 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.
- ^ a b c "KDU-414". astronautix.com. Archived from the original on 18 March 2022.
- ^ "Inventing The Interplanetary Probe". mentallandscape.com. Archived from the original on 8 April 2022.
External links
Media related to KDU-414 at Wikimedia Commons
Spacecraft engines and motors | ||
|---|---|---|
| Liquid fuel engines |  | |
| Solid propellant motors | ||
| Related articles | ||
This page was last edited on 24 November 2023, at 16:11