Considerations in lunar landmark sighting and recommended techniques - Project Apollo
Lunar landmark sighting techniques for Apollo command service module
Simon, E. H., Jr.↗
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Results for “SERVICE MODULE”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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CSM rendezvous procedures - G mission Final report
Command service module rendezvous procedures
Source record↗
Nondestructive testing of Apollo CSM spacecraft ordnance devices by neutron radiography
Nondestructive testing of Apollo CSM /Command and Service Module/ spacecraft ordnance explosive devices by indirect and direct neutron radiography
Ewbank, N. M.↗
Apollo fuel cell power system
Fuel cell assemblies as primary electrical source for Apollo command and service modules, discussing heat removal, water vapor control and transient performance
Ferguson, R. B.↗
A survey of spacecraft testing as applied to long-duration space missions
Apollo Applications Program command and service module test requirements to achieve reliable hardware for extended missions
Douglas, W. H.↗
Environmental control system of Apollo spacecraft worked O.K. thanks to redesigned hardware
Apollo command and service modules environmental control system, discussing redesign of faulty hardware
Nicolello, H.↗
System for non-dispersive analysis of lunar X- rays from Apollo
Apollo command service module nondispersive X ray detection system for lunar composition map compilation, discussing design and performance
Adler, I.↗
Past and present manned-spacecraft electronics and implications for the space shuttle
Space shuttle electronics requirements, considering systems in Mercury and Gemini spacecraft and Apollo lunar and command service modules
Gardiner, R. A.↗
Current events
Apollo spacecraft program evolution, discussing Apollo 13 accident, command and service module modifications, oxygen tank design, mission objectives, etc
Mcdivitt, J. A.↗
Apollo 13 Mission Report
The Apollo 13 mission, planned as a lunar landing in the Fra Mauro area, was aborted because of an abrupt loss of service module cryogenic oxygen associated with a fire in one of the two tanks at approximately 56 hours. The lunar module provided the necessary support to sustain a minimum operational condition for a safe return to earth. A circumlunar profile was executed as the most efficient means of earth return, with the lunar module providing power and life support until transfer to the command module just prior to entry. Although the mission was unsuccessful as planned, a lunar flyby and several scientific experiments were completed.
Source record↗
MSC Apollo 13 investigation team. Panel 1 - Spacecraft incident investigation. Volume 1 - Anomaly investigation Final report
Analysis of anomalies, cause, and results of command service module oxygen tank failure on Apollo 13 flight
Source record↗
A survey of spacecraft testing as applied to long-duration space missions
Apollo Applications Program command and service module test requirements to achieve reliable hardware for extended missions
Douglas, W. H.↗
The flight of Apollo 13 - A successful failure
Apollo 13 in flight emergencies and countermeasures, discussing fire in Service Module oxygen tank causes and effects on spacecraft systems and solutions
Lovell, J. A.↗
Apollo 15 X-ray fluorescence experiment
The X-ray fluorescence spectrometer, carried in the SIM bay of the command service module was employed principally for compositional mapping of the lunar surface while in lunar orbit, and secondarily, for X-ray astronomical observations during the trans-earth coast. The lunar surface measurements involved observations of the intensity and characteristics energy distribution of the secondary or fluorescent X-rays produced by the interaction of solar X-rays with the lunar surface. The astronomical observations consisted of relatively long periods of measurements of X-rays from pre-selected galactic sources such as Cyg-X-1 and Sco X-1 as well as from the galactic poles.
Adler, I.↗
The quasi-inertial and wide-deadband modes as backup attitude options for the Skylab mission
The quasi-inertial (QI) and wide deadband (WDB) modes were investigated as alternatives to the solar inertial (SI) mode in case two control moment gyros fail during the Skylab mission. Both modes provide a substantial reduction in propellant requirements from the solar interial hold requirement with either the orbital assembly/thruster attitude control system or service module reaction control system. Spacecraft motion in the QI mode is produced by a command rate and results in a small amplitude oscillation (17 deg, maximum) about the SI orientation. In the WDB mode a somewhat similar, but larger amplitude motion (35 deg maximum) about the SI orientation is developed by appropriate choice of controller deadbands and switch line slopes.
Elrod, B. D.↗
The Apollo Docking System
The Apollo docking system is the means by which the Apollo command and service modules and the lunar module are connected and disconnected during a lunar-landing mission. The system incorporates a CSM probe assembly that mates with a drogue assembly on the LM. Twelve automatic latches mounted on the CSM docking ring provide for structural integrity between the vehicles and for tunnel sealing during crew transfer. A functional description of the flight hardware and the alternate concepts that were evaluated to determine the system best suited to Apollo requirements are presented.
Kenneth A Bloom↗
Apollo 15 30-day failure and anomaly listing report
The significant anomalies that occurred during the Apollo 15 mission are discussed. The five major areas are command and service modules, lunar module, scientific instrument module experiments, Apollo lunar surface experiment package and associated equipment, and government furnished equipment.
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Thermal performance and radio-frequency transmissivity of candidate ablation materials for S-band antenna window application on manned spacecraft
A test program was conducted in the MSC 1.5 MW arc-heated facility to evaluate the thermal performance of ablation materials having potential application as radio frequency windows. These tests were conducted for the improvement of omnidirectional antenna operating characteristics during atmospheric reentry. Since a full scale model of the Apollo command service module was available for antenna tests, this mockup was used as a basic for the tests. Test models were subjected to heating conditions simulating the nominal lunar return trajectory (AS-501) and the design trajectories, high heat load and high heating rate. RF measurements were made before and after the arc jet tests to measure attenuation effects due to the thermal degradation of the materials under consideration. The test program demonstrated that additional development is required in materials technology to achieve an ablative system with both good RF transmission characteristics and thermal-structural integrity.
Tillian, D. J.↗