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Apollo Lunar Module

Apollo 16 LM Orion on lunar surface
Role: manned lunar landing and subsequent takeoff
Crew: 2; CDR, LM pilot
Height: 20.9 ft 6.37 m
Diameter: 14 ft 4.27 m
Landing gear span: 29.75 ft 9.07 m
Volume: 235 ft³ 6.65 m³
Ascent module: 10,024 lb 4,547 kg
Descent module: 22,375 lb 10,149 kg
Total: 32,399 lb 14,696 kg
Rocket engines
LM RCS (N2O4/UDMH) x 16: 100 lbf ea 441 N
Ascent Propulsion System
(N2O4/Aerozine 50) x 1:
3,500 lbf ea 15.6 kN
Descent Propulsion System
(N2O4/Aerozine 50) x 1:
9,982 lbf ea 44.40 kN
Endurance: 3 days 72 hours
Aposelene: 100 miles 160 km
Periselene: surface surface
Spacecraft delta v: 15,390 ft/s 4,690 m/s
Apollo LM diagram

Apollo LM diagram (NASA)
Grumman Apollo LM
The Apollo Lunar Module was the lander portion of the Apollo spacecraft built for the USmarker Apollo program by Grumman to achieve the transit from lunar orbit to the surface and back. The module was also known as the LM from the manufacturer designation (often pronounced "lem," from NASA's early name for it, Lunar Excursion Module).

The module was designed to carry a crew of two and rested on four landing legs. It consisted of two stages, the descent stage and the ascent stage. The total mass of the module was 15,264 kg, with the majority (10,334 kg) in the descent stage. Initially unpopular because the many delays in its development significantly stretched the projected timeline of the Apollo program, the LM eventually became the most reliable component of the Apollo/Saturn system, the only one never to suffer any failure that significantly impacted a mission, and in at least one instance (LM-7 Aquarius) greatly exceeded its design requirements.


The Apollo Lunar Module was designed after NASA chose to reach the moon via lunar orbit rendezvous (LOR) instead of by direct ascent or Earth orbit rendezvous (EOR). Both direct ascent and EOR would have involved the entire Apollo spacecraft landing on the moon. Once the decision had been made to proceed using LOR, it became necessary to produce a separate craft capable of reaching the lunar surface and ascending back to lunar orbit.
Early concept model of the lunar module, c.
The Apollo Lunar Module was built by Grumman Aircraft Engineering and was chiefly designed by the American aerospace engineer, Tom Kelly. Grumman had begun lunar orbit rendezvous studies in late 1950s and again in 1962. In July 1962, eleven firms were invited to submit proposals for the LM. Nine did so in September, and Grumman was awarded the contract that same month. The contract cost was expected to be around $350 million. There were initially four major subcontractors—Bell Aerosystems (ascent engine), Hamilton Standard (environmental control systems), Marquardt (reaction control system) and Rocketdyne (descent engine).

The primary guidance, navigation and control system (PGNCS) on the LM was developed by the MIT Instrumentation Laboratory; the Apollo Guidance Computer was manufactured by Raytheon. A backup navigation tool, the Apollo Abort Guidance System (AGS), was developed by TRW.

To learn lunar landing techniques, astronauts practiced in the Lunar Landing Research Vehicle (LLRV), a flying vehicle that simulated the Lunar Module on earth. A 200-foot (61 m)-tall, 400-foot (122 m)- long gantry structure was constructed at NASA Langley Research Centermarker; the LLRV was suspended in this structure from a crane, and "piloted" by moving the crane.

Early configurations of the LEM included a forward docking port; initially, it was believed the LEM crew would be active in the docking with the CSM. Early designs included large curved windows and seats for the astronauts. A configuration freeze did not start until April 1963, when the ascent and descent engine designs were decided. In addition to Rocketdyne, a parallel program for the descent engine was ordered from Space Technology Laboratories in July 1963, and by January 1965 the Rocketdyne contract was cancelled. As the program continued, there were numerous redesigns to save weight (including "Operation Scrape"), improve safety, and fix problems. The final design eliminated seats (the astronauts stood while flying the LM), and allowed the design of smaller windows and a lighter structure, resulting in significant weight savings. The LM was initially supposed to be powered by fuel cells built by Pratt and Whitney, but in March 1965 they were discarded in favor of an all battery design.

The initial design iteration had the LEM with three landing legs. As any particular leg would have to carry the weight of the vehicle if it lands at any significant angle, three legs was the lightest configuration. However, it would be the least stable if one of the legs were damaged during landing. The next landing gear design iteration had five legs and was the most stable configuration for landing on an unknown terrain. That configuration, however, was too heavy and the designers compromised on four landing legs.

The first LM flight was on January 22, 1968 when the unmanned LM-1 was launched atop a Saturn IB for testing of propulsion systems in orbit. The next LM flight was aboard Apollo 9 using LM-3 on March 3, 1969 as the first manned test flight to test a number of systems in Earth orbit including LM and CSM crew transit, LM propulsion, separation and docking. Apollo 10, launched on May 18, 1969, was another series of tests, this time in lunar orbit with the LM separating and descending to within 10 km of the surface. From the successful tests the LM successfully descended to and ascended from the lunar surface with Apollo 11. The Apollo 12 and Apollo 14 LMs achieved precision landings with upgraded computers and navigational techniques.

In April 1970, the lunar module Aquarius played an unexpected role in saving the lives of the three astronauts of the Apollo 13 mission after an oxygen tank in the service module exploded. Aquarius served as a refuge for the astronauts during their return to Earth, while its batteries were used to recharge the vital re-entry batteries of the command module that brought the astronauts through the Earth's atmosphere and to a safe splashdown on April 17, 1970. The LM's descent engine, designed to slow the vehicle during its descent to the moon, was used to accelerate the Apollo 13 spacecraft around the moon and back to Earth. The LM's systems, designed to support two astronauts for 45 hours, actually supported three astronauts for 90 hours.

The Lunar Modules for the final three Apollo missions (15, 16, and 17) were significantly upgraded to allow for greater landing payload weights and longer lunar surface stay times. The descent engine power was improved by the addition of a ten-inch (254 mm) extension to the engine bell, and the descent fuel tanks were increased in size. Hover times and landing weights were also maximized by having the CSM perform the initial deorbit burn of the attached CSM-LM (a practice begun on Apollo 14), with the LM then separating for the final powered descent to the surface. The most important cargo on these missions was the Lunar Roving Vehicle, which was stowed on Quadrant 1 of the LM Descent Stage and deployed by astronauts after landing. The upgraded capability of these "J-Mission" LMs allowed three day stays on the moon.

Lunar Module specifications

The Apollo Lunar Module Crew Cabin.
Apollo Spacecraft: Apollo Lunar Module Diagram.
Apollo Lunar Module
The Lunar Module was the Apollo spacecraft that landed on the moon and returned to lunar orbit. It consists of the Descent and Ascent stages.

The Descent stage contains the landing gear; EVA ladder; landing radar; descent rocket engine and fuel to land on the moon. It has several cargo compartments with replacement PLSS batteries and lithium hydroxide canisters; the Apollo Lunar Surface Experiment Packages ALSEP; Mobile Equipment Cart (a hand-pulled equipment cart used on Apollo 14) or the Lunar Rover (used on Apollo 15, 16, and 17); deployable S-band antenna (Apollo 11-14); surface television camera; surface tools; and lunar sample collection boxes. The descent stage carried consumables for the lunar stay: batteries; oxygen and water for drinking and cooling. The descent stage ladder carried a plaque.

The Ascent stage contains the crew cabin; environmental control (life support) system; instrument panels; overhead hatch/docking port; forward hatch; reaction control system; rendezvous radar; VHF and S-band communications equipment and antennae; guidance and navigation systems (primary and backup); active thermal control system (an ice sublimator); ascent rocket engine; and enough fuel, battery power, cooling water, and breathing oxygen to return to lunar orbit and rendezvous with the Apollo Command and Service Module. The ascent stage also carried lunar rock and soil samples back with the crew, as much as 238 pounds (108 kg) on Apollo 17.

  • Specifications: (Baseline LM)
    • Ascent Stage:
      • Crew: 2
      • Crew cabin volume: 6.65 m³ (235 ft³)
      • Height: 3.76 m (12.34 ft)
      • Diameter: 4.2 m (13.78 ft)
      • Mass including fuel: 4,670 kg (10,300 lb)
      • Atmosphere: 100% oxygen at 33 kPa (4.8 lb/in²)
      • Water: two 19.3 kg (42.5 lb) storage tanks
      • Coolant: 11.3 kg (25 lb) of ethylene glycol/water solution
      • Thermal Control: one active water-ice sublimator.
      • RCS (Reaction Control System) Propellant mass: 287 kg (633 lb)
      • RCS thrusters: 16 x 445 N; four quads
      • RCS propellants: N2O4/Aerozine 50
      • RCS specific impulse: 2.84 km/s (290 s)
      • APS Propellant mass: 2,353 kg (5,187 lb)
      • APS thrust: 15.6 kN (3,500 lbf)
      • APS propellants: N2O4/Aerozine 50
      • APS pressurant: 2 x 2.9 kg helium tanks at 21 MPa
      • Engine specific impulse: 3.05 km/s (311 s)
      • Thrust-to-weight ratio at liftoff: 0.34 (twice lunar gravity)
      • Ascent stage delta V: 2,220 m/s (7,280 ft/s)
      • Batteries: two 28-32 volt, 296 ampere-hour silver-zinc batteries; 56.7 kg each
      • Power: 28 V DC, 115 V 400 Hz AC
    • Descent Stage:
      • Height: 3.2 m (10.5 ft)
      • Diameter: 4.2 m (13.8 ft)
      • Landing gear diameter: 9.4 m (30.8 ft)
      • Mass including fuel: 10,334 kg (22,783 lb)
      • Water: 1 x 151 kg storage tank
      • Propellants mass: 8,165 kg (18,000 lb)
      • DPS thrust: 45.04 kN (10,125 lbf), throttleable between 10% and 60% of full thrust
      • DPS propellants: N2O4/Aerozine 50 (UDMH/N2H4)
      • DPS pressurant: 1 x 22 kg supercritical helium tank at 10.72 kPa.
      • Engine specific impulse: 3.05 km/s (311 s)
      • Descent stage delta V: 2,470 m/s (8,100 ft/s)
      • Batteries: four (Apollo 9-14) or five (Apollo 15-17) 28-32V, 415 A-h silver-zinc batteries; 61.2 kg each

Lunar Modules produced

The Apollo 11 Lunar Module Eagle in lunar orbit.
Serial number Name Use Launch date Current location Image

Apollo 5 January 22, 1968 Reentered Earth's atmosphere

Not flown
On display at the National Air and Space Museummarker, Washington, DCmarker
LM-3 Spider Apollo 9 March 3, 1969 Reentered Earth's atmosphere
LM-4 Snoopy Apollo 10 May 18, 1969 Descent stage impacted Moon; Ascent stage in solar orbit

Eagle Apollo 11 July 16, 1969 Descent stage on lunar surface; Ascent stage left in lunar orbit, eventually crashed on moon
LM-6 Intrepid Apollo 12 November 14, 1969 Descent stage on lunar surface; Ascent stage deliberately crashed into moon
LM-7 Aquarius Apollo 13 April 11, 1970 Reentered Earth's atmosphere
LM-8 Antares Apollo 14 January 31, 1971 Descent stage on lunar surface; Ascent stage deliberately crashed into moon
LM-9 Not flown
On display at the Kennedy Space Centermarker (Apollo/Saturn V Center)
LM-10 Falcon Apollo 15 July 26, 1971 Descent stage on lunar surface; Ascent stage deliberately crashed into moon
LM-11 Orion Apollo 16 April 16, 1972 Descent stage on lunar surface; Ascent stage left in lunar orbit, eventually crashed on moon
LM-12 Challenger Apollo 17 December 7, 1972 Descent stage on lunar surface; Ascent stage deliberately crashed into moon
Not flown (meant for later Apollo flights)
Partially completed by Grumman; restored and on display at Cradle of Aviation Museummarker, Long Island, New Yorkmarker. Also used during HBO's 1998 mini-series From the Earth to the Moon.
Not flown (meant for later Apollo flights)
Never completed; unconfirmed reports claim that some parts (in addition to parts from test vehicle LTA-3) are included in LM on display at the Franklin Institutemarker, Philadelphiamarker (see Franklin Institute web page.)
Not flown (meant for later Apollo flights)
* For the location of LMs left on the Lunar surface, see the list of artificial objects on the Moon.

LM truck

The Apollo LM Truck was a stand-alone LM descent stage intended to deliver up to five metric tons of payload to the Moon for an unmanned landing. This technique was intended to deliver equipment and supplies to a permanent manned lunar base. As originally proposed, it would be launched on a Saturn V with a full Apollo crew to accompany it to lunar orbit and then guide it to a landing next to the base; the base crew would then unload the "truck" while the orbiting crew returned to earth.


The LSAM launches its ascent stage to return the astronauts to Lunar Orbit.
The LM design was later incorporated into the Apollo Telescope Mount on the successful Skylab station. Originally planning to launch it on an unmanned Saturn 1B, similar to the unmanned Apollo 5 flight, NASA decided to save costs and launch the ATM with the station itself. This decision saved the station, as the ATM's "windmill" solar panels helped keep the station operational after damage to the station's solar panels during launch.

In 2005 NASA announced that the successor to the Space Shuttle, the Orion spacecraft, would feature a Lunar Surface Access Module (LSAM) named Altair that is roughly based on the Apollo LM. Like the LM, it is designed with both descent and ascent modules, but unlike the LM, it will incorporate improved computer systems, laser ranging and radar tracking systems for landing, waste-management systems, and an airlock for the crew, eliminating the need to depressurize the entire cockpit and reducing lunar dust tracked into the cabin to a minimum.

Altair will be powered by four RL10 engines in the descent stage and a single RL10 in the ascent stage, all fuelled by liquid hydrogen (LH2) and liquid oxygen (LOX), which produce greater specific impulse than the hypergolic fuels used on the LM (as well as being safer, as LH2 and LOX produces water, while hypergolics are very toxic). This will allow the LSAM to land anywhere on the Moon, although NASA has targeted the polar regions of the Moon (Apollo was limited to the equatorial regions), which is a desired location for a future lunar base.

In addition, the LSAM can be flown by an astronaut crew, or unmanned (similar in nature to the drone used by the U.S. Air Force), the latter to bring supplies to the future lunar outpost(s). Thus, the LSAM could function as the unflown LM truck envisioned in the Apollo Applications Program. In the unmanned configuration, the LSAM's payload equals the LM's fully fuelled weight.

Another major difference between the LSAM and the LM is that the LSAM will be launched separately on the Shuttle-derived Ares V rocket, with the CEV being launched separately on the man-rated Ares I rocket. Once in orbit, the Orion CSM will then dock with the LSAM and then be propelled to the Moon on the Earth Departure Stage. The LM, on the other hand, was launched along with the CSM on the Saturn V and retrieved after the S-IVB finished firing the translunar injection burn.

As an additional note, the LM was given a call sign to identify it separately from the CSM – all LSAMs will possibly bear the name "Altair," as the "Orion" name has already been chosen for the orbiter. Unlike the CSM and LM, the CEV/LSAM combination will bear a dual identity number, much like the Spacelab missions associated with the Space Shuttle (i.e. STS-9/Spacelab 1) or the Salyut space stations orbited by the former Soviet Unionmarker in the 1970s and 1980s (i.e. Soyuz 11marker/Salyut 1).

Depiction in fiction

The development and construction of the lunar module is dramatized in the miniseries From the Earth to the Moon episode entitled "Spider". This is in reference to LM-3, used on Apollo 9, which the crew named Spider after its spidery appearance.


Image:Apollo 15 landing on the Moon.ogg|Apollo 15 landing on the Moon seen from the perspective of the Lunar Module Pilot. Starts at about 5000 feetImage:Apollo 15 liftoff from the Moon.ogg|Apollo 15's Lunar Module blasts off and leaves the moon. View from TV camera on RoverImage:Apollo 15 liftoff from inside LM.ogg|Apollo 15's Lunar Module blasts off and leaves the moon. View from inside LMImage:Ap17-ascent.ogg|Apollo 17's Lunar Module blasts off and leaves the moon. View from TV camera on Rover

See also



  • Kelly, Thomas J. (2001). Moon Lander: How We Developed the Apollo Lunar Module (Smithsonian History of Aviation and Spaceflight Series). Smithsonian Institution Press. ISBN 1-56098-998-X.
  • Baker, David (1981). The History of Manned Space Flight. Crown Publishers. ISBN 0-517-54377-X
  • Brooks, Courtney J., Grimwood, James M. and Swenson, Loyd S. Jr (1979) Chariots for Apollo: A History of Manned Lunar Spacecraft NASA SP-4205.
  • Sullivan, Scott P. (2004) Virtual LM: A Pictorial Essay of the Engineering and Construction of the Apollo Lunar Module. Apogee Books. ISBN 1-894959-14-0
  • Stoff, Joshua. (2004) Building Moonships: The Grumman Lunar Module. Arcadia Publishing. ISBN 0-7385-3586-9
  • Stengel, Robert F. (1970). Manual Attitude Control of the Lunar Module, J. Spacecraft and Rockets, Vol. 7, No. 8, pp. 941-948.

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