Engine Model: RD-860. Manufacturer Name: RD-860. Designer: Yuzhnoye. Developed in: Developed late 1960's. Application: Upper stages. Propellants: N2O4/UDMH. Thrust(vac): 5.900 kN (1,326 lbf). Throttled thrust(vac): 1.960 kN (441 lbf). Isp: 320 sec. Burn time: 1,500 sec. Mass Engine: 30 kg (66 lb). Chambers: 1. Oxidizer to Fuel Ratio: 2.00. Country: Ukraine. Status: Developed 1972. The RD-860 engine was intended for launch vehicle and used a novel scheme combining an existing proven combustion chamber but using a pneumatic pump for propellant supply. This allowed:
- Multiple restarts (up to 15)
- Precision throttling of thrust to any value between 200 and 600 kgf simply by controlling the pneumatic pump, without the need for an elaborate control system with various pressure and flow sensors
- Reduction in the gas needed for propellant feed was reduced by 1.4 to 1.7 times compared to conventional methods
- High accuracy of mixture ratio maintenance
- Stage tanks operarted under low pressure
- Thrust increase of existing thrust chambers by 1.4 to 1.8 x
- Use of proven components from mass-produced engines such as combustion chamber, pneumatic pump elements, and control units
Bibliography:
