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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 451 records · Page 25
All sourcesNASA NTRSDOE OSTI
NASA NTRS1975

Manned maneuvering unit mission definition study. Volume 1: MMU applications analysis and performance requirements

Applications of Manned Maneuvering Units (MMU'S) to the space shuttle program are identified and described. The applications analyses included studies of the shuttle orbiter, orbiter subsystems, and both Sortie and Automated Payloads. Based on practicable MMU applications, general performance and control requirements for shuttle supporting maneuvering units are defined and compared to units evaluated on Skylab. The results of the MMU applications analyses and the general MMU performance and control requirements are presented. To describe a versatile utility-type maneuvering unit, conceptual designs of MMU support subsystems and ancillary equipment were prepared. Concepts for attaching and securing the MMU crewman to various vehicles, structure configurations, and rescue systems were developed. Concepts for ancillary provisions are reported.

Source record↗
NASA NTRS1975

Shuttle Kit Freezer Refrigeration Unit Conceptual Design

The refrigerated food/medical sample storage compartment as a kit to the space shuttle orbiter is examined. To maintain the -10 F in the freezer kit, an active refrigeration unit is required, and an air cooled Stirling Cycle refrigerator was selected. The freezer kit contains two subsystems, the refrigeration unit, and the storage volume. The freezer must provide two basic capabilities in one unit. One requirement is to store 215 lbs of food which is consumed in a 30-day period by 7 people. The other requirement is to store 128.3 lbs of medical samples consisting of both urine and feces. The unit can be mounted on the lower deck of the shuttle cabin, and will occupy four standard payload module compartments on the forward bulkhead. The freezer contains four storage compartments.

Copeland, R. J.↗
NASA NTRS1975

Development of an automated potable water bactericide monitoring unit

A monitor unit has been developed that permits the direct determination of the level of elemental iodine, used for microbiological control, in a spacecraft potable water supply system. Salient features of unit include low weight, volume and maintenance requirements, complete automatic operation, no inflight calibration, no expendables (except electrical current) and high accuracy and precision. This unit is capable of providing a signal to a controller that, in turn, automatically adjusts the addition rate of iodine to the potable water system so that a predetermined level of iodine can be maintained. In addition, the monitor provides a reading whereby the crewman can verify that the proper amount of iodine (within a range) is present in the water. A development history of the monitor is presented along with its design and theory of operation. Also presented are the results generated through testing of the unit in a simulated Shuttle potable water system.

Walsh, J. M.↗
NASA NTRS1973

Combination of an electrolytic pretreatment unit with secondary water reclamation processes

The design and fabrication of a flight concept prototype electrolytic pretreatment unit (EPU) and of a contractor-furnished air evaporation unit (AEU) are described. The integrated EPU and AEU potable water recovery system is referred to as the Electrovap and is capable of processing the urine and flush water of a six-man crew. Results of a five-day performance verification test of the Electrovap system are presented and plans are included for the extended testing of the Electrovap to produce data applicable to the combination of electrolytic pretreatment with most final potable water recovery systems. Plans are also presented for a program to define the design requirements for combining the electrolytic pretreatment unit with a reverse osmosis final processing unit.

Wells, G. W.↗
NASA NTRS1975

Test procedures, AN/AIC-27 system and component units

The AN/AIC-27 (v) intercommunication system is a 30-channel audio distribution which consists of: air crew station units, maintenance station units, and a central control unit. A test procedure for each of the above units and also a test procedure for the system are presented. The intent of the test is to provide data for use in shuttle audio subsystem design.

Reiff, F. H.↗
NASA NTRS1976

US metric study mission to the United Kingdom and the Federal Republic of Germany: Report of the NASA representative (Executive Summary)

The trip report is given of the NASA representative of the U.S. metric study mission to the United Kingdom and the Federal Republic of Germany. The mission was organized and conducted under the aegis of the American National Metric Council to learn at first hand the progress of metrication in the United Kingdom and the progress of metrication in the aerospace industry in both the United Kingdom and the Federal Republic of Germany. Representatives of the mission included a cross section of government, industry, labor, and other segments of the private sector. After general and special meetings in the United Kingdom, U.S. members with aerospace related interests met with aerospace representatives in the Federal Republic of Germany.

Vlannes, P. N.↗
NASA NTRS1975

Relative ages of flow units in Mare Imbrium and Sinus Iridum

A method for determining relative ages from low-resolution Lunar Orbiter photographs of lunar plains has been developed and applied to Mare Imbrium and Sinus Iridum. The method is an extension of previous ones and uses the shapes of craters and a small-impact erosion model to estimate the net accumulated impact flux. The net impact flux that has accumulated on a surface of uniform age is a measure of relative age of that surface and can be estimated by the largest diameters of craters that have been degraded by the net impact flux. Frequency distributions or relative ages indicate that there are four major units present in Mare Imbrium and Sinus Iridum. The older mare units are generally found along the edge of the basin and the younger units in the center. A similar distribution of ages of units in Mare Serenitatis shows the two basins have had similar filling histories. Filling histories for other circular basins may be similar to these two.

Boyce, J. M.↗
NASA NTRS1978

Ages of flow units in the far eastern maria and implications for basin-filling history

The spatial distribution of major units of uniform relative age exposed in the far eastern maria and Mare Humorum was determined using a crater density mapping technique. Correlation of crater densities and radiometric ages of Apollo and Luna landing sites provided estimates of the absolute ages for the units. The combination of such data with relative age data from previous crater morphology studies produced a complete map of the distribution of major age units in the lunar near-side maria. The map shows that there are young (2.5 + or - 0.5 billion years old) mare basalts in the eastern maria, although most young flows occur in the western maria. The vents for the young flows generally are found along the edges of basins. Because old mare units (greater than 3.5 billion years old) are also commonly found around the edges of the basins, it is suggested that the basins were subsiding during filling, probably as a result of isostatic compensation due to the weight of the lava.

Boyce, J. M.↗
NASA NTRS1978

Design, development, fabrication and delivery of register and multiplexer units

Several approaches for implementing the register and multiplexer unit into two CMOS monolithic chip types were evaluated. The CMOS standard cell array technique was selected and implemented. Using this design automation technology, two LSI CMOS arrays were designed, fabricated, packaged, and tested for proper static, functional, and dynamic operation. One of the chip types, multiplexer register type 1, is fabricated on a 0.143 x 0.123 inch chip. It uses nine standard cell types for a total of 54 standard cells. This involves more than 350 transistors and has the functional equivalent of 111 gates. The second chip, multiplexer register type 2, is housed on a 0.12 x 0.12 inch die. It uses 13 standard cell types, for a total of 42 standard cells. It contains more than 300 transistors, the functional equivalent of 112 gates. All of the hermetically sealed units were initially screened for proper functional operation. The static leakage and the dynamic leakage were measured. Dynamic measurements were made and recorded. At 10 V, 14 megabit shifting rates were measured on multiplexer register type 1. At 5 V these units shifted data at a 6.6 MHz rate. The units were designed to operate over the 3 to 15 V operating range and over a temperature range of -55 to 125 C.

Feller, A.↗
NASA NTRS1980

Taxonomic classification of world map units in crop producing areas of Argentina and Brazil with representative US soil series and major land resource areas in which they occur

The most probable current U.S. taxonomic classification of the soils estimated to dominate world soil map units (WSM)) in selected crop producing states of Argentina and Brazil are presented. Representative U.S. soil series the units are given. The map units occurring in each state are listed with areal extent and major U.S. land resource areas in which similar soils most probably occur. Soil series sampled in LARS Technical Report 111579 and major land resource areas in which they occur with corresponding similar WSM units at the taxonomic subgroup levels are given.

Huckle, H. F.↗
NASA NTRS1985

The Solid Rocket Booster Auxiliary Power Unit: Meeting the Challenge

The thrust vector control systems of the solid rocket boosters are turbine-powered, electrically controlled hydraulic systems which function through hydraulic actuators to gimbal the nozzles of the solid rocket boosters and provide vehicle steering for the Space Shuttle. Turbine power for the thrust vector control systems is provided through hydrazine fueled auxiliary power units which drive the hydraulic pumps. The solid rocket booster auxiliary power unit resulted from trade studies which indicated significant advantages would result if an existing engine could be found to meet the program goal of 20 missions reusability and adapted to meet the seawater environments associated with ocean landings. During its maturation, the auxiliary power unit underwent many design iterations and provided its flight worthiness through full qualification programs both as a component and as part of the thrust vector control system. More significant, the auxiliary power unit has successfully completed six Shuttle missions.

Hughes, R. W.↗
NASA NTRS1984

Orbital flight test of the manned maneuvering unit

Based on the experience provided by the first astronaut maneuvering unit used in the early extravehicular activities missions, a manned maneuvering unit (MMU) was developed that culminated in emergence of the M509 unit. The M509 unit, flown on the STS41-B, is a self-contained propulsive backpack. A flight support station (FSS) provides cargo bay stowage for the MMU, serves as a donning/doffing station, and provides an interface with the Orbiter gaseous nitrogen system for propellant refueling, electrical power for heaters, and temperature instrumentation. The MMU propulsion system, its control system, the electrical system and the flight displays are described. The orbital flight test has demonstrated superior handling and flying qualities of the MMU.

Stewart, R. L.↗
NASA NTRS1986

Orbital flight simulation utility software unit specifications, revision 1

The HP PASCAL source code defines the specifications for a Utility Software Unit (USU) designed to support orbital flight simulators such as MANHANDLE and GREAS (General Research and Engineering Analysis Simulator). Besides providing basic input/output, mathematical, matrix, quaternion, and statistical routines for such simulators, one of the primary functions of the USU is to isolate all system-dependent codes in one well-defined compartment, thereby facilitating transportation of the simulations from one computer to another. Directives are given for the PASCAL compilers of the HP-9000 Series 200 Pascal 3.0 and the HP-9000 Series 500 HP-UX 5.0 operating systems that produce a single file of relocatable code from four separate files of source code. Three of the source code files are common to both operating systems. The fourth source code file (utilspif.I) contains all of the system-dependent PASCAL code for the USU. A fifth file of source code written in C is required to interface utilspif.I with the HP-UX I/O package. The Pascal 3.0 compiler directives and the driver source code for a unit rest program and counterparts for the HP-UX 5.0 operating system are given. The major portion of the unit test program source code is common to both operating systems. Unit test results from the Pascal 3.0 operating system and results from the HP-UX operating system are given.

Wilson, S. W.↗
NASA NTRS1987

Surface units on Mars: The assemblage in the Valles Marineris

The Valles Marineris system of troughs offers a unique opportunity to investigate Martian surface units in the third dimension. The troughs are more than 7 km deep in places and thus expose a significant portion of the Martian upper crust. The geological units within the Valles Marineris can be subdivided into three broad categories: wall rock, interior deposits, and surficial cover. Overall, the exposure units in the Valles Marineris give insights into surface units elsewhere on Mars. The observations tend to support the hypotheses that the highland material is charaged with ice, that some light-colored, rolling, smooth deposits are of volcanic origin, and that dark dunes and streaks are composed of wind blown mafic materials.

Lucchitta, B. K.↗
NASA NTRS1991

Magellan: Preliminary description of Venus surface geologic units

Observations from approximately one-half of the Magellan nominal eight-month mission to map Venus are summarized. Preliminary compilation of initial geologic observations of the planet reveals a surface dominated by plains that are characterized by extensive and intensive volcanism and tectonic deformation. Four broad categories of units have been identified: plains units, linear belts, surficial units, and terrain units.

Saunders, R. S.↗
NASA NTRS1993

Shuttle orbiter with telescoping main propulsion unit and payload

An improved Space Shuttle with variable internal volume is provided. The Space Shuttle Orbiter includes a telescoping main propulsion unit. This main propulsion unit contains the main rocket engines and fuel tanks and telescopes into the Space Shuttle. A variable cavity is located between this unit and the crew compartment. Accordingly, the positioning of the telescoping main propulsion unit determines the volume of the variable cavity. Thus, the volume of the variable length of the entire Space Shuttle may be increased or decreased to achieve desired configurations for optimal storage. In one embodiment of the invention, the payload also telescopes within the variable cavity.

Macconochie, Ian O.↗
NASA NTRS1993

Unit cell geometry of 3-D braided structures

The traditional approach used in modeling of composites reinforced by three-dimensional (3-D) braids is to assume a simple unit cell geometry of a 3-D braided structure with known fiber volume fraction and orientation. In this article, we first examine 3-D braiding methods in the light of braid structures, followed by the development of geometric models for 3-D braids using a unit cell approach. The unit cell geometry of 3-D braids is identified and the relationship of structural parameters such as yarn orientation angle and fiber volume fraction with the key processing parameters established. The limiting geometry has been computed by establishing the point at which yarns jam against each other. Using this factor makes it possible to identify the complete range of allowable geometric arrangements for 3-D braided preforms. This identified unit cell geometry can be translated to mechanical models which relate the geometrical properties of fabric preforms to the mechanical responses of composite systems.

Du, Guang-Wu↗
NASA NTRS1993

A unit-cell model of textile composite beams for predicting stiffness properties

Flexural stiffness properties of a textile composite beam are obtained from a finite-element model of the unit cell. Three linearly independent deformations, namely, pure extension, pure bending and pure shear, are applied to the unit cell. The top and bottom surfaces of the beam are assumed to be traction free. Periodic boundary conditions on the lateral boundaries of the unit cell are enforced by multi-point constraint elements. From the forces acting on the unit cell, the flexural stiffness coefficients of the composite beam are obtained. The difficulties in determining the transverse shear stiffness are discussed, and a modified approach is presented. The methods are first verified by applying them to isotropic and bimaterial beams for which the results are known, and then illustrated for a simple plain-weave textile composite.

Sankar, Bhavani V.↗