Engines for lunar missions
Engines for lunar missions
ENGINES FOR LUNAR MISSIONS
ENGINES FOR LUNAR MISSIONS
RD860
RD860
Liquid-propellant
ROCKET ENGINE BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The RD860 is a single-chamber, restartable main engine with a pneumatic pump feed system.
The engine is designed to produce thrust and control the powered flight pitch and yaw of LV upper stages, space tugs, and unmanned takeoff and landing modules.
The engine employs the tried-and-tested technologies of the DU802 propulsion system.
DESCRIPTION
| Propellants | NT+UDMH |
| Thrust in vacuum (main/throttled), tf | 0.5/0.25 |
| Specific impulse in vacuum (main/throttled), s | 322.5/316 |
| Propellant mixture ratio | 2.25 |
| Starts | 10* |
| Engine weight, kg | 34** |
| TRL | 6 |
* depends on the onboard gas capacity of the LV stage
** not including the weight of gimbal actuators and the frame
** not including the weight of gimbal actuators and the frame
RD860L
RD860L
Liquid-propellant
ROCKET ENGINE BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The RD-860L is a restartable main engine with two engine assemblies and a pneumatic pump feed system.
The engine is designed to produce thrust and control the powered flight pitch and yaw of LV upper stages, space tugs, and unmanned takeoff and landing modules.
The RD860L comprises two engine assemblies (a two-chamber stationary engine assembly DB-1, and a DB-2 consisting of an RD860 gimballed engine in a gimbal bearing).
The engine employs the tried-and-tested technologies of the DU-802 propulsion system.
DESCRIPTION
| Propellants | NT+UDMH |
| Thrust in vacuum (main/throttled), tf | 1/0.25 |
| Specific impulse in vacuum (main/throttled), s | 322.5/316 |
| Propellant mixture ratio | 2.25 |
| Starts | 10* |
| Engine weight, kg | 106** |
| TRL | 6 |
* depends on the onboard gas capacity of the LV stage
** including the weight of the frame and not including the weight of gimbal actuators
** including the weight of the frame and not including the weight of gimbal actuators
RD860M
RD860M
Liquid-propellant
ROCKET ENGINE BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The RD860М is a restartable main engine with three engine assemblies and a pneumatic pump feed system.
The engine is designed to produce thrust and control the powered flight pitch and yaw of LV upper stages, orbital tugs, and unmanned takeoff and landing modules.
The RD860М is a cluster of three RD860 engine assemblies (stationary engine assemblies DB-1 and DB-3 and a gimballed engine assembly DB-2).
The RD860М engine employs the tried-and-tested technologies of the DU802 propulsion system.
DESCRIPTION
| Engine thrust in vacuum (main/throttled), tf | 0.5/0.25 |
| Specific impulse in vacuum (main/throttled), s | 322.5/316 |
| Propellant mixture ratio | 2.25 |
| Starts | 10* |
| Propulsion system mass, kg | 112** |
| TRL | 6 |
* depends on the onboard gas capacity of the LV stage
** including the weight of the frame and not including the weight of gimbal actuators
** including the weight of the frame and not including the weight of gimbal actuators
RD860
RD860
ROCKET ENGINE BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The RD860 is a single-chamber, restartable main engine with a pneumatic pump feed system.
The engine is designed to produce thrust and control the powered flight pitch and yaw of LV upper stages, space tugs, and unmanned takeoff and landing modules.
The engine employs the tried-and-tested technologies of the DU802 propulsion system.
FEATURES
| Propellants | NT+UDMH |
| Thrust in vacuum (main/throttled), tf | 0.5/0.25 |
| Specific impulse in vacuum (main/throttled), s | 322.5/316 |
| Propellant mixture ratio | 2.25 |
| Starts | 10* |
| Engine weight, kg | 34** |
| TRL | 6 |
* depends on the onboard gas capacity of the LV stage
** not including the weight of gimbal actuators and the frame
** not including the weight of gimbal actuators and the frame
RD860L
RD860L
ROCKET ENGINE BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The RD860L is a restartable main engine with two engine assemblies and a pneumatic pump feed system.
The engine is designed to produce thrust and control the powered flight pitch and yaw of LV upper stages, space tugs, and unmanned takeoff and landing modules.
The RD860L comprises two engine assemblies (a two-chamber stationary engine assembly DB-1, and a DB-2 consisting of an RD860 gimballed engine in a gimbal bearing).
The engine employs the tried-and-tested technologies of the DU802 propulsion system.
FEATURES
| Propellants | NT+UDMH |
| Thrust in vacuum (main/throttled), tf | 1/0.25 |
| Specific impulse in vacuum (main/throttled), s | 322.5/316 |
| Propellant mixture ratio | 2.25 |
| Starts | 10* |
| Engine weight, kg | 106** |
| TRL | 6 |
* depends on the onboard gas capacity of the LV stage
** including the weight of the frame and not including the weight of gimbal actuators
** including the weight of the frame and not including the weight of gimbal actuators
RD860M
RD860M Liquid-propellant
ROCKET ENGINE BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The RD860М is a restartable main engine with three engine assemblies and a pneumatic pump feed system.
The engine is designed to produce thrust and control the powered flight pitch and yaw of LV upper stages, orbital tugs, and unmanned takeoff and landing modules.
The RD860М is a cluster of three RD860 engine assemblies (stationary engine assemblies DB-1 and DB-3 and a gimballed engine assembly DB-2).
The RD860М engine employs the tried-and-tested technologies of the DU802 propulsion system.
FEATURES
| Engine thrust in vacuum (main/throttled), tf | 0.5/0.25 |
| Specific impulse in vacuum (main/throttled), s | 322.5/316 |
| Propellant mixture ratio | 2.25 |
| Starts | 10* |
| Propulsion system mass, kg | 112** |
| TRL | 6 |
* depends on the onboard gas capacity of the LV stage
** including the weight of the frame and not including the weight of gimbal actuators
** including the weight of the frame and not including the weight of gimbal actuators