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Results for “CHECKOUT EQUIPMENT”

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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At least 55 records · Page 3
All sourcesNASA NTRSDOE OSTI
NASA NTRS1966

Orbital tube flare for tubing connectors

Marshall engineering personnel have developed and are now refining a new and unique method of mechanically flaring tubing. The system eliminates the use of the conventional split backing die which is used with most tube-flaring equipment. The Marshall-developed tool is adapted for use on standard Leonard 3-CP-HD flaring machines. The stationary split backing die is replaced in function with a die ring, whose i.d.-surface rolls or orbits around the o.d. of the tube flare zone. An i.d.-flaring cone moves axially and forces the metal against the rolling die to form the flare. Major advantages of this system are the elimination of flash, or split die marks, on the back angle of the flare, and improved flare-surface finishes, permitting more uniform sealing characteristics and improvements of the total geometric configuration of the flare as required by the MSFC specification MC-146. The Orbital Adapter system of tooling is currently being used to manufacture flared tube hardware for the Saturn V S-IO space launch vehicle at MSFC, for the Agena space launch vehicle (used for the Gemini project) at Lockheed, Sunnyvale, for LEM checkout equipment for Grumman, and for the Saturn S-IV-B space launch vehicle by Douglas Aircraft Company. Several other aerospace firms are evaluating the system for possible incorporation on their tube flaring requirements. Marshall engineers are now concentrating their efforts on refining and reducing the total cost of the overall system.

Tubing↗
NASA NTRS1966

Solid state thermostat has integral probe and circuitry

Compact, reliable thermostat provides a temperature readout signal and a continuous temperature-control output for temperature monitoring by automatic checkout equipment or telemetry systems. It employs a solid state circuit in a housing rigidly attached to a thermistor probe.

Source record↗
NASA NTRS1980

Window comparator for voltages

Circuit determines whether voltage is within preselected range of voltage levels.Device requires fewer components than previous window comparators and is less susceptible to errors from reference drift. Comparator is useful in process-control circuitry, measuring instruments, and checkout equipment.

Black, J. M.↗
NASA NTRS1979

KSC facilities status and planned management operations

A status report is presented on facilities and planned operations at the Kennedy Space Center with reference to Space Shuttle launch activities. The facilities are essentially complete, with all new construction and modifications to existing buildings almost finished. Some activity is still in progress at Pad A and on the Mobile Launcher due to changes in requirements but is not expected to affect the launch schedule. The installation and testing of the ground checkout equipment that will be used to test the flight hardware is now in operation. The Launch Processing System is currently supporting the development of the applications software that will perform the testing of this flight hardware.

Gray, R. H.↗
NASA NTRS1979

NASA electronic message experiment and study: Detailed test plans

A methodology for evaluating the utility of high speed digital facsimile as a component of the projected NASA-wide electronic message network is presented. Equipment checkout, operator familiarization, pretest calibration, and the development of procedures are addressed. An experimental test program of the facsimile message service which will carry duplicates of the actual messages sent by other means is highlighted. Also, an operational test program during which messages will be sent on a regular basis in order to accumulate the information that will be used to evaluate system performance and project future growth is described.

Source record↗
NASA NTRS1989

First incremental buy for Increment 2 of the Space Transportation System (STS)

Thiokol manufactured and delivered 9 flight motors to KSC on schedule. All test flights were successful. All spent SRMs were recovered. Design, development, manufacture, and delivery of required transportation, handling, and checkout equipment to MSFC and to KSC were completed on schedule. All items of data required by DPD 400 were prepared and delivered as directed. In the system requirements and analysis area, the point of departure from Buy 1 to the operational phase was developed in significant detail with a complete set of transition documentation available. The documentation prepared during the Buy 1 program was maintained and updated where required. The following flight support activities should be continued through other production programs: as-built materials usage tracking on all flight hardware; mass properties reporting for all flight hardware until sample size is large enough to verify that the weight limit requirements were met; ballistic predictions and postflight performance assessments for all production flights; and recovered SRM hardware inspection and anomaly identification. In the safety, reliability, and quality assurance area, activities accomplished were assurance oriented in nature and specifically formulated to prevent problems and hardware failures. The flight program to date has adequately demonstrated the success of this assurance approach. The attention focused on details of design, analysis, manufacture, and inspection to assure the production of high-quality hardware has resulted in the absence of flight failures. The few anomalies which did occur were evaluated, design or manufacturing changes incorporated, and corrective actions taken to preclude recurrence.

Source record↗
NASA NTRS1990

STS-31 Crew Training: Firefighting, Food Tasting, EVA Prep and Post

The Space Shuttle crew is shown lighting a pond of gasoline and then performing firefighting tasks. The crew is also shown tasting food including lemonade, chicken casserole, and tortillas, and performing extravehicular activity (EVA) equipment checkouts in the CCT middeck and airlock.

Source record↗
NASA NTRS1995

Automated data acquisition technology development:Automated modeling and control development

This report documents the completion of, and improvements made to, the software developed for automated data acquisition and automated modeling and control development on the Texas Micro rackmounted PC's. This research was initiated because a need was identified by the Metal Processing Branch of NASA Marshall Space Flight Center for a mobile data acquisition and data analysis system, customized for welding measurement and calibration. Several hardware configurations were evaluated and a PC based system was chosen. The Welding Measurement System (WMS), is a dedicated instrument strickly for use of data acquisition and data analysis. In addition to the data acquisition functions described in this thesis, WMS also supports many functions associated with process control. The hardware and software requirements for an automated acquisition system for welding process parameters, welding equipment checkout, and welding process modeling were determined in 1992. From these recommendations, NASA purchased the necessary hardware and software. The new welding acquisition system is designed to collect welding parameter data and perform analysis to determine the voltage versus current arc-length relationship for VPPA welding. Once the results of this analysis are obtained, they can then be used to develop a RAIL function to control welding startup and shutdown without torch crashing.

Romine, Peter L.↗
NASA NTRS2016

Thermal Design, Tvac Testing, and Lessons Learned for Critical GSE of ATLAS and the ICESat-2 Mission

This presentation describes the thermal design of the three main of optical components which comprise the Bench Checkout Equipment (BCE) for the Advanced Topographic Laser Altimeter System (ATLAS) instrument, which is flying on the ICESat-2 mission. Thermal vacuum testing of these components is also described in this presentation, as well as a few lessons learned. These BCE components serve as critical GSE for the mission; their purpose is to verify ATLAS is performing well. It has been said that, in one light, the BCE is the most important part of ATLAS, since, without it, ATLAS cannot be aligned properly or its performance verified before flight. Therefore, careful attention was paid to the BCEs thermal design, development, and component-level Tvac testing prior to its use in instrument-level and spacecraft-level Tvac tests with ATLAS. This presentation describes that thermal design, development, and testing, as well as a few lessons learned.

Thermal ATLAS BCE↗
NASA NTRS1965

Improvements in stage checkout

Test methods, equipment, and computer programs for improved quality control in space vehicle stage checkout

CHECKOUT EQUIPMENT↗
NASA NTRS1967

Design of an on-board checkout system.

Onboard Checkout System /OCS/ design, considering system selection techniques, design development, equipment, etc, with orientation on OCS design by NASA/MSC

AIRBORNE EQUIPMENT↗