From Wikipedia, the free encyclopedia
Ukrainian rocket engine
RD-810 (РД-810) Country of origin Ukraine Designer Yuzhnoye Design Bureau Manufacturer Yuzhmash Application First Stage Status In development Propellant LOX / RP-1 Mixture ratio 2.65 Cycle Staged Combustion Chamber 1 Thrust, vacuum 2,105 kN (473,000 lbf) Thrust, sea-level 1,876 kN (422,000 lbf) Chamber pressure 18 MPa (2,600 psi) Specific impulse, vacuum 335.5 s (3.290 km/s) Specific impulse, sea-level 299 s (2.93 km/s) Gimbal range 8 Dry mass 2,800 kg (6,200 lb) References [1][2][3][4]The RD-810 (РД-810) is a Ukrainian liquid propellant rocket engine burning LOX and Kerosene (RG-1) in a staged combustion cycle.[4] It has a single combustion chamber that provides 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.[4][2]
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.[2]
and
solid motorsfor
orbital launch vehicles LiquidRetroSearch is an open source project built by @garambo | Open a GitHub Issue
Search and Browse the WWW like it's 1997 | Search results from DuckDuckGo
HTML:
3.2
| Encoding:
UTF-8
| Version:
0.7.4