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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 649 records · Page 36

All sources NASA NTRS DOE OSTI

NASA NTRS1971

Expendable second stage reusable space shuttle booster. Volume 6: Interface control drawings

The major expendable second stage interfaces which must be controlled in the development of the expendable second stage reusable space shuttle booster are defined. Interface control drawings are presented for the following configurations: (1) booster/expendable second stage (ESS), (2) space shuttle engine/expendable second stage, (3) expendable second stage/ground support equipment, (4) expendable second stage/payload, and (5) orbiter/expendable second stage.

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NASA NTRS1972

Crew interface specifications preparation for in-flight maintenance and stowage functions

The findings and data products developed during the Phase 2 crew interface specification study are presented. Five new NASA general specifications were prepared: operations location coding system for crew interfaces; loose equipment and stowage management requirements; loose equipment and stowage data base information requirements; spacecraft loose equipment stowage drawing requirements; and inflight stowage management data requirements. Additional data was developed defining inflight maintenance processes and related data concepts for inflight troubleshooting, remove/repair/replace and scheduled maintenance activities. The process of maintenance task and equipment definition during spacecraft design and development was also defined and related data concepts were identified for futher development into formal NASA specifications during future follow-on study phases of the contract.

Parker, F. W.↗

NASA NTRS1972

Interface control and MRL phasedown report

Engine interface control activities were performed to coordinate engine and component design activities in conformance with the 1137400E flight engine baseline. Interface control drawings were maintained. The preliminary operational flight engine measurement requirements list is consistent with design requirements, the flight engine configuration, and an allocated minimum measurement channel quantity.

Smith, J. L.↗

NASA NTRS1972

The role of process history, phase morphology and interface strength upon the mechanical properties of dispersion strengthened alloys

An analytical rationale for the sensitivity-insensitivity of dispersion-strengthened systems to process history is provided. In particular, the research was focussed upon the influence of the particle-matrix interface bond in TD-Nickel and TD-Nichrome, and the manner in which the differences in both elastic constants and thermal expansion coefficients between these phases stress this interface when these alloys are subjected to mechanical and thermal loads upon the mechanical properties of these alloys.

Ansell, G. S.↗

NASA NTRS1973

Triple redundant computer system/display and keyboard subsystem interface

Interfacing of the redundant display and keyboard subsystem with the triple redundant computer system is defined according to space shuttle design. The study is performed in three phases: (1) TRCS configuration and characteristics identification; (2) display and keyboard subsystem configuration and characteristics identification, and (3) interface approach definition.

Gulde, F. J.↗

NASA NTRS1973

Actuator digital interface unit (AIU)

Alternate versions of the actuator interface unit are presented. One alternate is a dual-failure immune configuration which feeds a look-and-switch dual-failure immune hydraulic system. The other alternate is a single-failure immune configuration which feeds a majority voting hydraulic system. Both systems communicate with the data bus through data terminals dedicated to each user subsystem. Both operational control data and configuration control information are processed in and out of the subsystem via the data terminal which yields the actuator interface subsystem, self-managing within its failure immunity capability.

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NASA NTRS1974

Space processing applications payload equipment study. Volume 2B: Payload interface analysis (power/thermal/electromagnetic compatibility)

As a part of the task of performing preliminary engineering analysis of modular payload subelement/host vehicle interfaces, a subsystem interface analysis was performed to establish the integrity of the modular approach to the equipment design and integration. Salient areas that were selected for analysis were power and power conditioning, heat rejection and electromagnetic capability (EMC). The equipment and load profiles for twelve representative experiments were identified. Two of the twelve experiments were chosen as being representative of the group and have been described in greater detail to illustrate the evaluations used in the analysis. The shuttle orbiter will provide electrical power from its three fuel cells in support of the orbiter and the Spacelab operations. One of the three shuttle orbiter fuel cells will be dedicated to the Spacelab electrical power requirements during normal shuttle operation. This power supplies the Spacelab subsystems and the excess will be available to the payload. The current Spacelab sybsystem requirements result in a payload allocation of 4.0 to 4.8 kW average (24 hour/day) and 9.0 kW peak for 15 minutes.

Hammel, R. L.↗

NASA NTRS1973

Design study of RL10 derivatives. Volume 3, part 1: Preliminary interface control document

The Interface Control Document contains engine information necessary for installation of the baseline RL10 Derivative engines in the Space Tug vehicle. The ICD presents a description of the baseline engines and their operating characteristics, mass and load characteristics, and environmental criteria. The document defines the engine/vehicle mechanical, electrical, fluid and pneumatic interface requirements.

Adams, A.↗

NASA NTRS1974

Instrument constraints and interface specifications. Earth Observatory Satellite system definition study (EOS)

The equipment specifications for the thematic mapper and high resolution pointable imager for use on the Earth Observatory Satellite (EOS) are presented. The interface requirements of the systems are defined. The interface requirements are extracted from the equipment specifications and are intended as a summary to be used by the system and spacecraft designer. The appropriate documentation from which the specifications of the equipment are established are identified.

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NASA NTRS1974

Flight management - Pilot procedures and system interfaces for the 1980-1990's

In the air transportation system of the 1980-1990's, aircraft must perform with greater precision in time and position than is possible today. Rapid development in electronics technology makes renovation in airborne-system concepts feasible. The Ames Research Center is conducting research on pilot procedures and pilot-system interfaces for such systems. Research on various pilot-system interface devices and manned simulations was conducted to study rules of distributed decision making authority among pilots and controllers with various airborne display concepts, and a pilot-oriented command logic for the control of avionic systems was studied. Results are summarized, and ongoing work and future research plans described.

Wempe, T. E.↗

NASA NTRS1974

Atom movements occurring at solid metal-semiconductor interfaces

Solid metal-semiconductor interfaces often undergo chemical reaction at rather low temperatures, in some cases not much above room temperature. After some general discussion of these reactions, more detailed consideration is given to simple noncompound-forming systems, and, in particular, to the Si-Al, Ge-Al, and Si-Au systems. Diffusive transport of Si or Ge in these solid metallizations is very rapid, though the converse process, diffusion of metal in solid Si or Ge, is usually so slow as to be negligible. The interface reaction itself is less well understood but is becoming controllable in intrinsically favorable cases like Ge-Al and in other cases by more sophisticated means.

Mccaldin, J. O.↗

NASA NTRS1975

PPP/nonreal-time trajectory program interface requirements and capabilities

The selection process for interfacing a nonreal time trajectory program with the procedures and performance program is outlined; the interface provides summary data timelines for any desired trajectory profile. Consideration was given to two separate digital programs for satisfying capabilities. One was the CDC 6400 digital program BANDITO, and the second was the UNIVAC 1110 SVDS program.

Mcgavern, J. L.↗

NASA NTRS1976

Shuttle payload interface verification equipment study. Volume 2: Technical document, part 1

The technical analysis is reported that was performed during the shuttle payload interface verification equipment study. It describes: (1) the background and intent of the study; (2) study approach and philosophy covering all facets of shuttle payload/cargo integration; (3)shuttle payload integration requirements; (4) preliminary design of the horizontal IVE; (5) vertical IVE concept; and (6) IVE program development plans, schedule and cost. Also included is a payload integration analysis task to identify potential uses in addition to payload interface verification.

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NASA NTRS1976

Interface markings in crystals experiment MA-060

Doped germanium single crystals with interface demarcation were successfully grown during the Apollo Soyuz Test Project mission. Interface demarcation permitted the determination of the microscopic growth behavior from the onset to the termination of solidification. Preliminary segregation analysis shows striking differences in segregation in the presence of gravity. The correlation between microscopic growth rate behavior and the composition of the solid on the microscale is being evaluated.

Gatos, H. C.↗

NASA NTRS1974

Study of orbiter/payload interface communications configuration control board directive from an operational perspective

Orbiter/payload data and communications interface was examined. It was found that the Configuration Control Board Directive (CCBD) greatly increases the capability of the orbiter to communicate with a wide variety of projected shuttle payloads. Rather than being derived from individual payload communication requirements, the CCBD appears to be based on an operational philosophy that requires the orbiter to duplicate or augment the ground network/payload communication links. It is suggested that the implementation of the CCBD be reviewed and compared with the Level 1 Program Requirements Document, differences reconciled, and interface characteristics defined.

Addis, A. W.↗

NASA NTRS1976

Orbiter altitude at ALT interface based on ALSES (Approach and Landing Shuttle Engineering Simulation) analyses. Mission planning, mission analysis and software formulation

The details of the orbiter altitude attainable at the approach and landing tests (ALT) interface determined by the approach and landing shuttle engineering simulation (manned) were documented. The analysis culminated in the verification of the trends observed in a similar analysis performed previously on the space vehicle dynamics simulation (unmanned). Altitude variations attributable to pilot steering variability ranged between 492 ft higher to 383 ft lower. The requirement for this parametric analysis is first elaborated. The specifications, assumptions, and analytical approach used to determine the orbiter altitude at the ALT interface are then presented, followed by the results of the analytical approach and the conclusions and recommendations.

Colwell, C. L.↗

NASA NTRS1976

Space shuttle engineering and operations support. Orbiter to spacelab electrical power interface. Avionics system engineering

The results are presented of an investigation of the factors which affect the determination of Spacelab (S/L) minimum interface main dc voltage and available power from the orbiter. The dedicated fuel cell mode of powering the S/L is examined along with the minimum S/L interface voltage and available power using the predicted fuel cell power plant performance curves. The values obtained are slightly lower than current estimates and represent a more marginal operating condition than previously estimated.

Emmons, T. E.↗

NASA NTRS1976

DSN standard interface adapter and buffer assembly used in the Mark 3 data system

The DSN Standard Interface Adapter and Buffer Assembly (referred to as the 900/SIA) is used to effect interface compatibility between the Xerox data systems 920 computer (XDS 920) and the Mark 3 data system (MDS) processors. It sets forth the requirements based on the differences between the two systems. Operational characteristics and general design strategy are described, as well as certain efficient implementation techniques used. From a software standpoint, the transfer protocol is discussed to a level of detail sufficient for its operation.

Anderson, T.↗