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Results for “GROUND SUPPORT SYSTEM”
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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Head to head test procedures for the hydrodynamic support of Saturn V
Test procedures for functional tests of hydrodynamic supports for Saturn V vehicle
Facility construction and equipment installation
Facility construction, and installation of S-band systems and ground support equipment for Deep Space Network
Apollo launch operations.
Ground support equipment and launch installations for Apollo launch operation and testing
Technical development status of the project Apollo Lunar Excursion Module.
Design and program for Apollo Lunar Excursion Module, noting propulsion, guidance, control, ground support, etc
Checkout criteria and ground support equipment for the Apollo spacecraft.
Checkout criteria and requirements for manned spacecraft, specifically Apollo
Apollo network
Although the design of the Apollo network followed closely behind the Manned Space Flight Network (MSFN) modification for the Gemini program, many site modifications were necessary to provide Apollo support due to the greater scope of the Apollo program. The Apollo program requires instrumentation for support of the S-I, S-11, S IV-B/IU, Command Service Module (CSM) and Lunar Excursion Module (LEM) stages. Command Service Module (CSM) and Lunar Excursion Module (LEM) stages. Support must also be provided at both orbital and lunar distances. Increased data processing capability is required for processing and displaying significantly larger amounts of information. The ground network requires the capability of processing both Pulse Code Modulation (PCM) telemetry and command data for the CSM, LEM, and S IV-B/IU. In various stages of the Apollo program, both tone (on UHF) and digital [on Unified S-Band (USB) and UHF] command capabilities are required. Also at various stages both USB and VHF telemetry links are required.
An advanced study of an Application Technology Satellite /ATS-4/ mission, volume I, book 3 Final study report, May - Nov. 1966
Flight dynamics, experiment operational phase sequence, and support operations for Applications Technology Satellite /ATS/ MISSION
The organization of the United States geodetic satellite program.
Organization of U.S. geodetic satellite program, discussing responsibilities for various phases of operation
Future support requirements for the manned space program.
Support requirements for future manned space programs
Contact ion engine system for ATS satellites D and E Annual progress report, 22 Mar. 1967 - 22 Mar. 1968
Ion microthrustor systems and ground support equipment for Applications Technology Satellites D and E
Dispersion development program
The requirement for the predictable dispersion of small munitions over large areas from ground support missile systems has resulted in the development of a fin stabilized submissile and sling ejection system for the Little John warhead. The progressive development of this system is traced including a comparison of simulator, sled test, and flight test results. The results indicate that it is not only necessary but also possible to eject long slender bodies, from a missile warhead at Mach 1, in a stable, uniform and predictable manner.
Helios mission support
The Helios-1 third solar occultation and fourth perihelion is covered. A Helios-2 spacecraft emergency and third solar conjunction (occultation) are also discussed. Additional topics include STDN-DSN telemetry and command cross-support, Ground Data System tests, tracking coverage, plus DSN system performance for August and September 1976.
A Multi-Band Far-Infrared Survey with a Balloon-Borne Telescope
Nine additional radiation sources, above a 3-sigma confidence level of 1300 Jy, were identified at 100 microns by far infrared photometry of the galactic plane using a 0.4 meter aperture, liquid helium cooled, multichannel far infrared balloon-borne telescope. The instrument is described, including its electronics, pointing and suspension systems, and ground support equipment. Testing procedures and flight staging are discussed along with the reduction and analysis of the data acquired. The history of infrared astronomy is reviewed. General infrared techniques and the concerns of balloon astronomers are explored.
Common data buffer system
A high speed common data buffer system is described for providing an interface and communications medium between a plurality of computers utilized in a distributed computer complex forming part of a checkout, command and control system for space vehicles and associated ground support equipment. The system includes the capability for temporarily storing data to be transferred between computers, for transferring a plurality of interrupts between computers, for monitoring and recording these transfers, and for correcting errors incurred in these transfers. Validity checks are made on each transfer and appropriate error notification is given to the computer associated with that transfer.
GSFC Preferred Parts List PPL-15
A listing is presented of preferred electronic parts, part upgrading procedures, part derating guidelines, and part screening procedures to be used in the selection, procurement, and application of parts for Goddard Space Flight Center space systems and ground support equipment.
The Goddard Space Flight Center preferred parts list, revision A
A listing is presented of preferred electronic parts, part upgrading procedures, part derating guidelines, and part screening procedures to be used in the selection, procurement, and application of parts for Goddard Space Flight Center space systems and ground support equipment.
Cost effective development of a Shuttle-based astronomical instrument control system
The high level language FORTH is used for the electronic control of the Space Shuttle-based Ultraviolet Imaging Telescope, in a flight computer system which minimizes costs. The greater part of the breadboard version of the flight computer is assembled from commercially available components, reducing novel circuit design features and permitting simultaneous development of both hardware and software. The commercial boards are then refabricated on aluminum core heat conducting stock, using high reliability parts to produce the flight versions of the system. The system's ground support equipment employs a MINC-25 minicomputer which performs such functions as flight computer software development, PROM programming, test and integration support, and flight operations support. The implementation of these concepts in flight computer telescope controls is described.