Thedescent propulsion system (DPS - pronounced 'dips') orlunar module descent engine (LMDE), internal designationVTR-10, is a variable-throttlehypergolicrocket engine invented by Gerard W. Elverum Jr.^[3][4][5] and developed bySpace Technology Laboratories (TRW) for use in theApollo Lunar Module descent stage. It usedAerozine 50 fuel anddinitrogen tetroxide (N
₂O
₄) oxidizer. This engine used apintle injector, which paved the way for other engines to use similar designs.

The propulsion system for the descent stage of the lunar module was designed to transfer the vehicle, containing two crewmen, from a 60-nautical-mile (110 km) circular lunar parking orbit to an elliptical descent orbit with apericynthion of 50,000 feet (15,000 m), then provide a powered descent to the lunar surface, with hover time above the lunar surface to select the exact landing site. To accomplish these maneuvers, a propulsion system was developed that usedhypergolic propellants and agimballed pressure-fed ablative cooled engine that was capable of beingthrottled. A lightweight cryogenic helium pressurization system was also used. The exhaustnozzle extension was designed to crush without damaging the LM if it struck the surface, which happened on Apollo 15.^[6]

According to NASA history publicationChariots for Apollo, "The lunar module descent engine probably was the biggest challenge and the most outstanding technical development of Apollo."^[7] A requirement for a throttleable engine was new for crewed spacecraft. Very little advanced research had been done in variable-thrust rocket engines up to that point.Rocketdyne proposed a pressure-fed engine using the injection of inert helium gas into the propellant flow to achieve thrust reduction at a constant propellant flow rate. While NASA'sManned Spacecraft Center (MSC) judged this approach to be plausible, it represented a considerable advance in the state of the art. (In fact, accidental ingestion of helium pressurant proved to be a problem onAS-201, the first flight of the Apollo Service Module engine in February 1966.) Therefore, MSC directed Grumman to conduct a parallel development program of competing designs.^[7]

Grumman held a bidders' conference on March 14, 1963, attended byAerojet General, Reaction Motors Division ofThiokol, United Technology Center Division ofUnited Aircraft, and Space Technology Laboratories, Inc. (STL). In May, STL was selected as the competitor to Rocketdyne's concept. STL proposed an engine that was gimbaled as well as throttleable, using flow control valves and a variable-areapintle injector, in much the same manner as does a shower head, to regulate pressure, rate of propellant flow, and the pattern of fuel mixture in the combustion chamber.^[7]

The first full-throttle firing of Space Technology Laboratories' LM descent engine was carried out in early 1964. NASA planners expected one of the two drastically different designs would emerge the clear winner, but this did not happen throughout 1964. Apollo Spacecraft Program Office managerJoseph Shea formed a committee of NASA, Grumman and Air Force propulsion experts, chaired by American spacecraft designerMaxime Faget, in November 1964 to recommend a choice, but their results were inconclusive. Grumman chose Rocketdyne on January 5, 1965. Still not satisfied, MSC DirectorRobert R. Gilruth convened his own five-member board, also chaired by Faget, which reversed Grumman's decision on January 18 and awarded the contract to STL.^[7][8]

To keep the DPS as simple, lightweight, and reliable as possible, the propellants were pressure-fed withhelium gas instead of using heavy, complicated, and failure-proneturbopumps.Cryogenicliquid helium was loaded into the tank before liftoff and the tank sealed. Heat leak through the tank insulation warmed the liquid until it becamesupercritical helium. The helium warmed over time, increasing the tank pressure.^[9]: 4 The helium was pressure regulated down to 246 psi (1.70 MPa) for the propellant tanks.^[9]: 4 This allowed a sufficient inventory of pressurant gas to be stored in a relatively small volume, with a much lighter tank than would have been required to store the helium as a room temperature gas. The system was also equipped with a burst disk assembly that relieved the pressure when pre-set pressure (1,881 to 1,967 psi [12.97 to 13.56 MPa]) was reached, allowing the gas to vent harmlessly into space. Once the helium was gone however, DPS operation would be limited due to inability to maintain system pressure as the propellant was expelled from the tanks. This was not seen as an issue, since normally the helium release would not occur until after the lunar module was on the Moon, by which time the DPS had completed its operational life and would never be fired again.

The design and development of the innovative thrust chamber and pintle design is credited to TRW Aerospace Engineer Gerard W. Elverum Jr.^[10][11][12] The engine could throttle between 1,050 and 10,125 pounds-force (4.67–45.04 kN) but operation between 65% and 92.5% thrust was avoided to prevent excessive nozzle erosion. It weighed 394 pounds (179 kg), with a length of 90.5 inches (230 cm) and diameter of 59.0 inches (150 cm).^[6]

The LMDE achieved a prominent role in theApollo 13 mission, serving as the primary propulsion engine after the oxygen tank explosion in theApollo Service Module. After this event, the ground controllers decided that theService Propulsion System could no longer be operated safely, leaving the DPS engine inAquarius as the only means of maneuvering Apollo 13.

In order to extend landing payload weight and lunar surface stay times, the last threeApollo Lunar Modules were upgraded by adding a 10-inch (25 cm)nozzle extension to the engine to increase thrust. The nozzle exhaust bell, like the original, was designed to crush if it hit the surface. It never had on the first three landings, but did buckle on the first Extended landing,Apollo 15.

After the Apollo program, the DPS was further developed into the TRWTR-201 engine. This engine was used in the second stage, referred to asDelta-P, of the Delta launch vehicle (Delta 1000,Delta 2000,Delta 3000 series) for 77 successful launches between 1972–1988.^[13]

• NASA Technical Note: Apollo Experience Report – Descent Propulsion System. March 1973 31 pages, much detail on both designs, and the testing.
• Apollo Lunar Module Propulsion Systems Overview, NASA
• Rocket Propulsion – The Apollo Mission, Don Harvey. Mr. Harvey worked at STL designing the LMDE

• Rocket engines
• Rocket engines using hypergolic propellant
• Apollo program hardware
• TRW Inc.
• Rocket engines using the pressure-fed cycle

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