Descent propulsion system
The descent propulsion system (DPS - pronounced 'dips') or lunar module descent engine (LMDE), internal designation VTR-10, is a variable-throttle hypergolic rocket engine invented by Gerard W. Elverum Jr. and developed by Space Technology Laboratories (TRW) for use in the Apollo Lunar Module descent stage. It used Aerozine 50 fuel and dinitrogen tetroxide (N
2O
4) oxidizer. This engine used a pintle injector, which paved the way for other engines to use similar designs.
| Country of origin | United States |
|---|---|
| Date | 1964–1972 |
| Designer | Gerard W. Elverum Jr. |
| Manufacturer | TRW |
| Application | Lunar descent stage propulsion |
| Predecessor | None |
| Successor | TR-201 |
| Status | Retired |
| Liquid-fuel engine | |
| Propellant | N 2O 4 / Aerozine 50 |
| Mixture ratio | 1.6 |
| Cycle | Pressure-fed |
| Pumps | None |
| Configuration | |
| Chamber | 1 |
| Nozzle ratio | 47.5 (Apollo 14 & before) 53.6 (Apollo 15 and later) |
| Performance | |
| Thrust, vacuum | 10,500 lbf (47 kN) maximum, throttleable between 1,050 lbf (4.7 kN) and 6,825 lbf (30.36 kN) |
| Throttle range | 10% - 60%, Full thrust |
| Thrust-to-weight ratio | 25.7 |
| Chamber pressure | 110 psi (760 kPa) (100% Thrust) 11 psi (76 kPa) (10% Thrust) |
| Specific impulse, vacuum | 311 s (3.05 km/s) (at Full Thrust) 285 s (2.79 km/s) (10% Thrust) |
| Burn time | 1030 seconds |
| Restarts | Designed for 2 restarts, has been tested up to four times on Apollo 9 |
| Gimbal range | 6° pitch and yaw |
| Dimensions | |
| Length | 85.0 in (2.16 m) (Apollo 14 and earlier) 100.0 in (2.54 m) (Apollo 15 and later) |
| Diameter | 59.0 in (1.50 m) (Apollo 14 and earlier) 63.0 in (1.60 m) (Apollo 15 and later) |
| Dry weight | 394 lb (179 kg) |
| Used in | |
| Lunar module as descent engine | |
| References | |
| References | |
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