RD-8 ( 11D513 ) is a four- chamber steering liquid - propellant rocket engine of single start-up, designed to create thrust and control the flight of the second stage of the Zenit LV through all stabilization channels.
| RD-8 | |
|---|---|
| Type of | Rocket engine |
| Fuel | kerosene |
| Oxidizing agent | liquid oxygen |
| Combustion chambers | four |
| A country | the USSR Ukraine |
| Using | |
| Operating time | from 1985 to the present |
| Application | PH Zenit |
| Production | |
| Constructor | Design Bureau "South" |
| Time of creation | 1976-1985 |
| Manufacturer | Yuzhmash |
| Oversized specifications | |
| Weight | 380 kg |
| Height | 1,500 mm |
| Diameter | 4000 mm |
| Performance data | |
| Thrust | 8 tf |
| Specific impulse | 342 s |
| Combustion chamber pressure | 7.65 MPa |
Stage flight control is carried out by swinging each engine chamber in one plane at an angle of ± 33 °. The steering engine with a turbopump fuel component supply system, for the first time in the history of rocket science, is designed according to a scheme with afterburning of generator gas.
The working fluid of the TNA turbine is an oxidizing gas produced in a gas generator during the combustion of fuel components. When starting, the pneumostarter spins the TNA rotor.
The fuel components in the combustion chambers and in the gas generator are ignited using starting fuel.
The engine maintains a given thrust and regulates the ratio of fuel components.
Each engine arrives at the rocket assembly after conducting a fire test and technological test without subsequent bulkheading.
Links
- Aircraft, rocket, marine, industrial engines. 1944-2000. Directory.