Apollo 14 Lunar Module Instrument Host Overview ======================== The Apollo 14 Lunar Module (LM) 'Antares' was the third crewed vehicle to land on the Moon. It carried two astronauts, Alan B. Shepard Jr. and LM pilot Edgar D. Mitchell, the fifth and sixth men to walk on the Moon. Also included on the LM was the Apollo Lunar Surface Experiments Package (ALSEP) containing scientific experiments to be deployed and left on the lunar surface and other scientific and sample collection apparatus. The LM separated from the Command/Service Module (CSM) at 04:50:44 UT and landed at 09:18:11 UT (4:18:11 a.m. EST) on 5 February 1971 in the lunar highlands near the crater Fra Mauro at 3.6453 S latitude, 17.4714 W longitude (IAU Mean Earth Polar Axis coordinate system [Davies and Colvin, 2000]). The LM landed on the slope of a small depression, tilted at 8 degrees. Shepard and Mitchell made two moonwalk extra-vehicular activities (EVAs) totaling 9 hours, 23 minutes. The first EVA began at 14:42:13 UT and ended at 19:30:03 UT. During this first EVA the astronauts deployed the ALSEP and other experiments. During the second EVA, which took place from 8:11:15 to 12:45:56 UT on 6 February, the astronauts walked almost to the rim of nearby Cone crater, collecting samples along the traverse. At the end of this walk Shepard used a contingency sampler with a 6-iron connected to the end to hit two golf balls. The astronauts traversed a total of 3.45 km and collected 42.28 kg of lunar samples. The LM lifted off the Moon on 6 February at 18:48:42 UT after 33 hours 31 minutes on the lunar surface. After docking with the CSM (piloted by Stuart A. Roosa) at 20:35:53 UT, the LM was jettisoned at 22:48:00 UT and impacted the Moon at 3.42 S, 19.67 W, between the Apollo 12 and Apollo 14 seismic stations, at 00:45:25 UT on 7 February. Lunar Module Spacecraft and Subsystems -------------------------------------- The lunar module was a two-stage vehicle designed for space operations near and on the Moon. The spacecraft mass of 15,264 kg was the mass of the LM including astronauts, expendables, and 11,010 kg of propellants. The fully fueled mass of the ascent stage was 4943 kg and the descent stage 10,334 kg. The ascent and descent stages of the LM operated as a unit until staging, when the ascent stage functioned as a single spacecraft for rendezvous and docking with the command and service module (CSM). The descent stage comprised the lower part of the spacecraft and was an octagonal prism 4.2 meters across and 1.7 m thick. Four landing legs with round footpads were mounted on the sides of the descent stage and held the bottom of the stage 1.5 m above the surface. The distance between the ends of the footpads on opposite landing legs was 9.4 m. One of the legs had a small astronaut egress platform and ladder. A one meter long conical descent engine skirt protruded from the bottom of the stage. The descent stage contained the landing rocket, two tanks of aerozine 50 fuel, two tanks of nitrogen tetroxide oxidizer, water, oxygen and helium tanks and storage space for the lunar equipment and experiments, and in the case of Apollo 15, 16, and 17, the lunar rover. The descent stage served as a platform for launching the ascent stage and was left behind on the Moon. The ascent stage was an irregularly shaped unit approximately 2.8 m high and 4.0 by 4.3 meters in width mounted on top of the descent stage. The ascent stage housed the astronauts in a pressurized crew compartment with a volume of 6.65 cubic meters. There was an ingress-egress hatch in one side and a docking hatch for connecting to the CSM on top. Also mounted along the top were a parabolic rendezvous radar antenna, a steerable parabolic S-band antenna, and 2 in-flight VHF antennas. Two triangular windows were above and to either side of the egress hatch and four thrust chamber assemblies were mounted around the sides. At the base of the assembly was the ascent engine. The stage also contained an aerozine 50 fuel and an oxidizer tank, and helium, liquid oxygen, gaseous oxygen, and reaction control fuel tanks. There were no seats in the LM. A control console was mounted in the front of the crew compartment above the ingress-egress hatch and between the windows and two more control panels mounted on the side walls. The ascent stage was launched from the Moon at the end of lunar surface operations and returned the astronauts to the CSM. The descent engine was a deep-throttling ablative rocket with a maximum thrust of about 45,000 N mounted on a gimbal ring in the center of the descent stage. The ascent engine was a fixed, constant-thrust rocket with a thrust of about 15,000 N. Maneuvering was achieved via the reaction control system, which consisted of the four thrust modules, each one composed of four 450 N thrust chambers and nozzles pointing in different directions. Telemetry, TV, voice, and range communications with Earth were all via the S-band antenna. VHF was used for communications between the astronauts and the LM, and the LM and orbiting CSM. There were redundant tranceivers and equipment for both S-band and VHF. An environmental control system recycled oxygen and maintained temperature in the electronics and cabin. Power was provided by 6 silver-zinc batteries. Guidance and navigation control were provided by a radar ranging system, an inertial measurement unit consisting of gyroscopes and accelerometers, and the Apollo guidance computer (AGC). Updates to the AGC in the LM were relayed by voice, then typed into the computer by an astronaut. Scientific Experiments ---------------------- The following scientific experiments were performed on board or at the Apollo 14 Lunar Module: - The Photography Experiment documented the deployment of experiments, augmented crew observations and descriptions of the lunar traverses, and recorded the effects of the interaction between Apollo equipment and the lunar surface. - The Lunar Field Geology Experiment entailed the collection and documentation fo geologic rock samples. - The Laser Ranging Retroreflector permitted ground-based stations to conduct short-pulse laser ranging to a corner reflector array on the lunar surface at the Fra Mauro site. - Lunar Portable Magnetometer obtained additional scientific information about the location, strength, and dimensions of local magnetic sources. - The Soil Mechanics Experiment studied the properties of the lunar soil. - The Solar Wind Composition Experiment collected samples of the solar wind for analysis on Earth. - The S-Band Transponder Experiment measured the lunar gravitational field by observing the dynamical motion of the spacecraft in free fall orbits to provide information about the distribution of lunar mass. For more information about the lunar module and its experiments, see the Apollo 14 Preliminary Science Seport (1971). References ========== Apollo 14 Preliminary Science Report, NASA SP-272, published by NASA, Washington, D.C., 1971. Davies, M.E., and T.R. Colvin, Lunar coordinates in the regions of the Apollo landers, Journal of Geophysical Research, Volume 105, Issue E8, pages 20,227-20,280, 2000.