RD860 and RD860L engines with pneumatic pump propellant feed system are designed for LV upper stages, space tugs and unmanned takeoff and landing modules.
RD860L engine consists of two blocks (EB-1 – dual-chamber, stationary, EB-2 – RD860 engine with gimballing).
The engines are developed on the basis of PS802 proven technologies, and provide for multiple firing.
BASIC SPECIFICATIONS
| Engine model | РД860 | РД860L |
|
Mass, kg |
4.3 |
106 |
|
Propellant components: |
АТ+НДМГ |
|
|
Vacuum thrust, tf (main/throttle) |
0,5/0,25 |
1/0,25 |
|
Vacuum specific impulse, s |
322,5 |
316 |
|
Propellant mixture ratio |
2,32 |
|
|
Number of firings |
2 |
|
|
TRL |
6 |
|
PS802 propulsion system with the use of pneumatic pump propellant feed system. The propulsion system is developed for Krechet AST, provides additional injection of different payloads including into lunar trajectory.
It has high mass energy characteristics, has a capability of multiple firing during flight and duration of in-flight functioning for 10 days and more.
BASIC SPECIFICATIONS
|
Mass, kg |
165,4 |
|
|
Propellant components: |
АТ+НДМГ |
|
|
Vacuum thrust, tf |
0,45 |
|
|
Vacuum specific impulse, s |
322,5 |
|
|
Propellant mixture ratio |
2,25 |
|
|
Number of firings |
10 |
|
|
TRL |
7 |
|
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