 The four nozzles of the RD-0110R surround the large single nozzle of the
NK-33 engine on the first stage of the Soyuz-2-1v. | |
| Country of origin | Russia |
|---|---|
| First flight | 2013-12-28 |
| Designer | KBKhA, [1] Viktor Gorokhov [2] |
| Manufacturer | Voronezh Mechanical Plant [2] |
| Application | 1st stage vernier engine |
| Associated LV | Soyuz-2-1v [1] |
| Predecessor | RD-0110 [1] |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | LOX [1] / RG-1 [1] |
| Cycle | Gas Generator [1] |
| Configuration | |
| Chamber | 4 [1] |
| Performance | |
| Thrust, vacuum | 265.1 kilonewtons (59,600 lbf) [1] |
| Thrust, sea-level | 230.5 kilonewtons (51,800 lbf) [1] |
| Chamber pressure | 6.6 megapascals (960 psi) [1] |
| Specific impulse, vacuum | 298.4 seconds [1] |
| Specific impulse, sea-level | 259.4 seconds [1] |
| Burn time | 210s [1] |
| Dimensions | |
| Length | 1,910 millimetres (75 in) [1] |
| Diameter | 2,675 millimetres (105.3 in) [1] |
| Dry weight | 850 kilograms (1,870 lb) [1] (including the support ring) |
| Used in | |
| Soyuz-2-1v first stage. | |
The RD-0110R ( GRAU Index 14D24) is a rocket engine burning kerosene in liquid oxygen in a gas generator combustion cycle. It has four nozzles that can gimbal up to 45 degrees in a single axis and is used as the vernier thruster on the Soyuz-2-1v first stage. [1] It also has heat exchangers that heat oxygen and helium to pressurize the LOX and RG-1 tanks of the Soyuz-2.1v first stage, respectively. The oxygen is supplied from the same LOX tank in liquid form, while the helium is supplied from separate high pressure bottles (known as the T tank). [1]
The engine's development started in 2010 and it is a heavily modified version of the RD-0110. The main areas of work were shortening the nozzles to optimize them for the atmospheric part of the flight (the RD-0110 is a vacuum optimized engine), propellant piping, heat exchangers and the gimballing system, which was developed by TsSKB Progress. The RD-0110R engine is produced at the Voronezh Mechanical Plant. [2]
See also
- Soyuz-2-1v - The first rocket to use the RD-0110R
- KBKhA - The RD-0110R designer bureau
- RSC Progress - The designer of the Soyuz-2.1v and the RD-0110R nozzle gimbal
- Voronezh Mechanical Plant - A space hardware manufacturer company that manufactures the RD-0110R
References
External links
- https://kbkha.ru/deyatel-nost/raketnye-dvigateli-ao-kbha/rd0110r/
- https://web.archive.org/web/20211208214531/http://www.vmzvrn.ru/produktsiya-i-uslugi/zhrd/rd-0110r/
- http://russianspaceweb.com/rd0110r.html
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Liquid fuel |
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Solid fuel |
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 | This rocketry article is a stub. You can help Wikipedia by expanding it. |
|
The four nozzles of the RD-0110R surround the large single nozzle of the
NK-33 engine on the first stage of the Soyuz-2-1v. | |
| Country of origin | Russia |
|---|---|
| First flight | 2013-12-28 |
| Designer | KBKhA, [1] Viktor Gorokhov [2] |
| Manufacturer | Voronezh Mechanical Plant [2] |
| Application | 1st stage vernier engine |
| Associated LV | Soyuz-2-1v [1] |
| Predecessor | RD-0110 [1] |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | LOX [1] / RG-1 [1] |
| Cycle | Gas Generator [1] |
| Configuration | |
| Chamber | 4 [1] |
| Performance | |
| Thrust, vacuum | 265.1 kilonewtons (59,600 lbf) [1] |
| Thrust, sea-level | 230.5 kilonewtons (51,800 lbf) [1] |
| Chamber pressure | 6.6 megapascals (960 psi) [1] |
| Specific impulse, vacuum | 298.4 seconds [1] |
| Specific impulse, sea-level | 259.4 seconds [1] |
| Burn time | 210s [1] |
| Dimensions | |
| Length | 1,910 millimetres (75 in) [1] |
| Diameter | 2,675 millimetres (105.3 in) [1] |
| Dry weight | 850 kilograms (1,870 lb) [1] (including the support ring) |
| Used in | |
| Soyuz-2-1v first stage. | |
The RD-0110R ( GRAU Index 14D24) is a rocket engine burning kerosene in liquid oxygen in a gas generator combustion cycle. It has four nozzles that can gimbal up to 45 degrees in a single axis and is used as the vernier thruster on the Soyuz-2-1v first stage. [1] It also has heat exchangers that heat oxygen and helium to pressurize the LOX and RG-1 tanks of the Soyuz-2.1v first stage, respectively. The oxygen is supplied from the same LOX tank in liquid form, while the helium is supplied from separate high pressure bottles (known as the T tank). [1]
The engine's development started in 2010 and it is a heavily modified version of the RD-0110. The main areas of work were shortening the nozzles to optimize them for the atmospheric part of the flight (the RD-0110 is a vacuum optimized engine), propellant piping, heat exchangers and the gimballing system, which was developed by TsSKB Progress. The RD-0110R engine is produced at the Voronezh Mechanical Plant. [2]
See also
- Soyuz-2-1v - The first rocket to use the RD-0110R
- KBKhA - The RD-0110R designer bureau
- RSC Progress - The designer of the Soyuz-2.1v and the RD-0110R nozzle gimbal
- Voronezh Mechanical Plant - A space hardware manufacturer company that manufactures the RD-0110R
References
External links
- https://kbkha.ru/deyatel-nost/raketnye-dvigateli-ao-kbha/rd0110r/
- https://web.archive.org/web/20211208214531/http://www.vmzvrn.ru/produktsiya-i-uslugi/zhrd/rd-0110r/
- http://russianspaceweb.com/rd0110r.html
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Liquid fuel |
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|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
|
Solid fuel |
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| This rocketry article is a stub. You can help Wikipedia by expanding it. |