TEMS radar error model regression analysis results from the Saturn AS-201, AS-202, and SA-203 flight tests
Tracking system error model regression analysis results from Apollo-Saturn tests
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Tracking system error model regression analysis results from Apollo-Saturn tests
Monte Carlo simulation for Apollo go, no-go verification
Effects of measurement noise, measurement bias, and station location uncertainties on Apollo mission phases
Miniaturizing n automatic amino acid analyzer for use on Apollo mission and Mars Voyager mission
Thin film personal communication system for Apollo astronaut use during extravehicular assignments
Signal margin calculation procedures for CSM UNIFIED S-BAND downlink channel Apollo AS-202 TO aircraft NASA 432
Overview on scientific support requirements for extended lunar exploration missions including experiments, data management, equipment, astronaut training, and lunar systems planning
The lunar module (LM) landing phase is one of the most critical phases of the entire Apollo mission. Landing impact is of critical concern because at no other time during the LM mission is there less opportunity for vehicle control. To assure a successful landing, the alightment system must not only provide required shock attenuation for protection of crew and structure, but must also assure stability against overturning after touchdown. The paper discusses important design features of the alightment system, such as geometric arrangement, energy absorber characteristics, and deployment mechanisms. Performance characteristics of the vehicle at touchdown, as found analytically, are presented. Model and full-size testing of the landing system is briefly discussed.
Performance, design, test, and qualification requirements of computer programs for support system for on-board checkout and data management system of Saturn/Apollo application program
Analysis of crew performance in Apollo command module
Integrated NASA tracking antenna network for Apollo missions using spacecraft transponder
U.S. Saturn/Apollo moon program, considering Saturn V booster, Apollo spacecraft and Lunar Excursion Module
The development of the Apollo Launch Data Telemetry System, the real-time interface between the Merritt Island Launch Area (MILA) and the Mission Control Center-Houston (MCC-H), is reviewed from its beginning through the system planning stages, and then into the final hardware implementation.
Apollo X-ray astronomy experiment, noting instrumentation techniques employed and advantages
Thermal control subsystem for Apollo lunar surface experiments package, noting construction and operation principles
Apollo thermal control systems and concepts, discussing self-shadowing
Nondestructive testing /NDT/ of materials, components and systems for Saturn-Apollo program
Ames emissivity experiment on OSO-II to measure thermal radiation properties of temperature control coatings exposed to space environment