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LM 3, 4, 5, 6, 7, 8, 10, 11, 12 (LEM 3, 4, 5, 6, 7, 8, 10, 11, 12)

LM 5 (Apollo 11) [NASA]

LM 6 (Apollo 12) ascent stage [NASA]

LM 11 (Apollo 16) [NASA]

The NASA/Grumman Apollo Lunar Module (LM) after descending to the lunar surface from lunar orbit, provides a base from which the astronauts explore the landing site and enables the astronauts to take off from the lunar surface to rendezvous and dock with the orbiting Command and Service Modules (CSM).

The LM consists of an ascent stage and a descent stage. Both stages function as a single unit during separation from the CM, lunar descent, and lunar stay. The descent stage serves as a launching platform from which the ascent stage lifts off from the lunar surface. The ascent stage operates independently during the lunar ascent, rendezvous, and docking phase of the Apollo mission.

Ascent Stage

The ascent stage, control center of the LM, is comprised of three main areas: crew compartment, midsection, and equipment bay. The crew compartment and midsection make up the cabin, which has an overall volume of 6.7 m3. The basic structure is primarily aluminum alloy; titanium is used for fittings and fasteners. Aircraft-type construction methods are used. Skin and web panels are chemically milled to reduce weight. Mechanical fasteners join the major structural assemblies with epoxy as a sealant. Structural members are fusion welded wherever possible, to minimize cabin air pressurization leaks. The basic structure includes supports for throst control engine clusters and various antennas. The entire basic structure is enveloped by thermal insulation and a micrometeoroid shield.

The Ascent Stage contained the Aerozine 50 fuel / nitrogen tetroxide oxidizer fueled pressure-fed Ascent Propulsion System (APS) engine and two hypergolic propellant tanks for return to lunar orbit and rendezvous with the Apollo Command/Service Module. It also contained a Reaction Control System (RCS) for attitude and translation control, which consisted of sixteen hypergolic R4D thrusters similar to those used on the Service Module, mounted in four quads, with their own propellant supply. A forward EVA hatch provided access to and from the lunar surface, while an overhead hatch and docking port provided access to and from the Command Module.

Internal equipment included a life support system; a VHF communications system with two antennas for communication with the Command Module; a unified S-band system and steerable parabolic dish antenna for communication with Earth; an EVA antenna which relayed communications from antennas on the astronauts' Portable Life Support Systems through the LM; primary (PGNCS) and backup (AGS) guidance and navigation systems; an Alignment Optical Telescope for visually determining the spacecraft orientation; rendezvous radar with its own steerable dish antenna; and an ice sublimation system for active thermal control. Electrical storage batteries, cooling water, and breathing oxygen were stored in amounts sufficient for a lunar surface stay of 48 hours initially, extended to 75 hours for the later missions.

Descent Stage

The descent stage is the unmanned portion of the LM; it represents approximately two-thirds of the weight of the LM at the earth-launch phase. The main structure of the descent stage consists of two pairs of parallel beams arranged in a cruciform, with a deck on the upper and lower surfaces, approximately 65 inches apart. The ends of the beams, approximately 81 inches from the center, are closed off by aluminum beams to provide five equally sized compartments: a center compartment, one forward and one aft of the center compartment, and one right and one left of the center compartment. A four-legged truss (outrigger) at the end of each pair of beams serves as a support for the LM in the SLA and as the attachment point for the upper end of the landing gear primary strut. Two of the four interstage fittings for attachment of the ascent stage are mounted on the forward compartment beams. The other two fittings are on the aft beam of the side compartments. The five compartments formed by the main beams house Main Propulsion Subsystem components. The center compartment houses the descent engine, which is supported by truss members and an engine gimbal ring. Descent engine fuel and oxidizer tanks are in the remaining compartments.

The Descent stage's primary job was to support a powered landing and surface extravehicular activity. When the excursion was over, it served as the launch pad for the ascent stage. Octagon-shaped, it was supported by four folding landing gear legs, and contained a throttleable Descent Propulsion System (DPS) engine with four hypergolic propellant tanks containing Aerozine 50 fuel and nitrogen tetroxide oxidizer. A continuous-wave Doppler radar antenna was mounted by the engine heat shield on the bottom surface, to send altitude and rate of descent data to the guidance system and pilot display during the landing. Almost all external surfaces, except for the top, platform, ladder, descent engine and heat shield, were covered in amber, dark amber, black, silver, and yellow aluminized Kapton foil blankets for thermal insulation. The number 1 landing leg on the front side had an attached platform in front of the ascent stage's EVA hatch and a ladder, which the astronauts used to ascend and descend between the cabin to the surface. The footpad of each landing gear contained a 170 cm long surface contact sensor probe, which signaled the commander to switch off the descent engine. The probe was omitted from the number 1 leg of every landing mission, to avoid a suit-puncture hazard to the astronauts, as the probes tended to break off and protrude upwards from the surface.

Equipment for the lunar exploration was carried in the Modular Equipment Stowage Assembly (MESA), a drawer mounted on a hinged panel dropping out of the lefthand forward compartment. Besides the astronaut's surface excavation tools and sample collection boxes, the MESA contained a television camera with a tripod; as the commander opened the MESA by pulling on a lanyard while descending the ladder, the camera was automatically activated to send the first pictures of the astronauts on the surface back to Earth. A United States flag for the astronauts to erect on the surface was carried in a container mounted on the ladder of each landing mission.

The Early Apollo Surface Experiment Package (EASEP) and on later missions the Apollo Lunar Surface Experiment Package (ALSEP), was carried in the opposite compartment on the fat side of thr LM. An external compartment on the right front panel carried a deployable mesh-dish reflector S-band antenna and a mounting tripod. This was not used on the Apollo 11 landing due to time constraints and the fact that acceptable communications were being received using the LM's S-band antenna, but was used on the Apollo 12 and 14 missions.

A hand-pulled Modular Equipment Transporter (MET), similar in appearance to a golf cart, was carried on Apollo 13 and 14 to transport the tools and samples on extended moonwalks.

On the extended missions (Apollo 15 onwards), the antenna and TV camera were mounted on the Lunar Roving Vehicle (LRV), which was carried folded up and mounted on an external panel. The cargo compartments also contained replacement Portable Life Support System (PLSS) batteries and extra lithium hydroxide canisters on the extended missions.

Nation: USA
Type / Application: Manned lunar lander
Operator: NASA
Contractors: Grumman, NASA
Equipment:
Configuration:
Propulsion: Descent Stage: LMDE; Ascent Stage: RS-18 (LMAE), 16 R-4D
Power: Batteries
Lifetime:
Mass:
Orbit:
Satellite COSPAR Date LS Launch Vehicle Remarks
LM 3 (LEM 3, Spider) 1969-018C 03.03.1969 CCK LC-39A Saturn-5 with Apollo 9
LM 4 (LEM 4, Snoopy) 1969-043C 18.05.1969 CCK LC-39B Saturn-5 with Apollo 10
LM 5 (LEM 5, Eagle) 1969-059C 16.07.1969 CCK LC-39A Saturn-5 with Apollo 11
LM 6 (LEM 6, Intrepid) 1969-099C 14.11.1969 CCK LC-39A Saturn-5 with Apollo 12
LM 7 (LEM 7, Aquarius) 1970-029# 11.04.1970 CCK LC-39A Saturn-5 with Apollo 13
LM 8 (LEM 8, Antares) 1971-008C 31.01.1971 CCK LC-39A Saturn-5 with Apollo 14
LM 9 (LEM 9) - not launched
LM 10 (LEM 10, Falcon) 1971-063C 26.07.1971 CCK LC-39A Saturn-5 with Apollo 15, PFS 1
LM 11 (LEM 11, Orion) 1972-031C 16.04.1972 CCK LC-39A Saturn-5 with Apollo 16, PFS 2
LM 12 (LEM 12, Challenger) 1972-096C 07.12.1972 CCK LC-39A Saturn-5 with Apollo 17
LM 13 (LEM 13) - not launched
LM 14 (LEM 14) - not launched
LM 15 (LEM 15) - not launched