RD-810
| Country of origin | Ukraine |
|---|---|
| Designer | Yuzhnoye Design Bureau |
| Manufacturer | Yuzhmash |
| Application | First Stage |
| Status | In development |
| Liquid-fuel engine | |
| Propellant | LOX / RG-1 |
| Mixture ratio | 2.65 |
| Cycle | Staged Combustion |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust (vac.) | 2,105 kN (473,000 lbf) |
| Thrust (SL) | 1,876 kN (422,000 lbf) |
| Chamber pressure | 18 MPa (2,600 psi) |
| Isp (vac.) | 335.5 s (3.290 km/s) |
| Isp (SL) | 299 s (2.93 km/s) |
| Gimbal range | 8 |
| Dimensions | |
| Dry weight | 2,800 kg (6,200 lb) |
| References | |
| References | |
The RD-810 (РД-810) is an Ukrainian liquid propellant rocket engine burning LOX and Kerosene (RG-1) in a staged combustion cycle. It has a single combustion chambers that provide thrust vector control by gimbaling of the nozzle in two axis by +/- 8°. It is being designed in Ukraine by Yuzhnoye Design Bureau for the prospective first stage propulsion of the Mayak rocket family.
The RD-810 as well as the RD-801 are being designed based on the work of the RD-8 vernier and the maintenance and improvement of the RD-120 engines. The RD-810 can be used stand alone on a Mayak or could be used in a module of four called RD-810M to replace the RD-170 on the Zenit.
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Wikipedia