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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 19 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1971

Mechanical/structural design implications of space-basing on shuttle system

A conceptual design study was conducted to identify some of the mechanical/structural differences which result from the use of a tug/payload combination in a space-basing mode as contrasted with a ground-based mode of operation. The basic mechanical/structural differences associated with space-basing were identified by analyzing a space-basing strategy in which the tug and payload are launched separately by the EOS and comparing it with the ground-based mode in which the tug/payload is launched as an integral unit in the EOS. This operational concept, which is the simplest of a number of possible space-basing strategies, was also used to identify the major impacts on the Earth Orbit Shuttle. The mechanical/structural differences that were identified from a comparison of payloads operating in the ground and space-based modes of operation are discussed in addition to delineating the advantages and disadvantages associated with various payload deployment/retrieval mechanisms.

Ludlow, K. G.↗
NASA NTRS1965

Space-based centrifuge

Engineering and biomedical studies of therapeutic and training potential of space-based centrifuge

TRAINING↗
NASA NTRS1972

Manned versus unmanned space-based astronomy.

Discussion of the pros and cons of manned and unmanned space-based astronomical observatory systems. Rather than compete with one another, manned and unmanned systems, it is felt, should complement themselves mutually. The paramount factor inhibiting the growth of both manned and unmanned systems is shown to be the high cost per pound of payload equipment. The main hope for reducing this cost is the advent of a space station or shuttle sortie mode of operation in which the frequency of flights will reduce the necessity to guarantee experiment success. This, in turn, should reduce the complexity of experiment management and the cost of experiment hardware.

Henize, K. G.↗
NASA NTRS1975

Activities in space-based solar power development

Two space-based power concepts are considered. The satellite solar power system concept employs a large solar cell array to convert solar energy to electrical energy. The energy, in the form of microwaves, is transmitted to the ground where it is converted to dc power and transmitted to the utility network. According to the power relay satellite concept, power is generated on the ground at large stations in remote areas. The generated power in the form of microwaves is beamed for distribution to a relay satellite. Studies related to an investigation of the feasibility of the two concepts are briefly discussed.

Whitacre, W. E.↗
NASA NTRS1971

A Preliminary Structural Analysis of Space-Base Living Quarters Modules to Verify a Weight-Estimating Technique

The determination of a base line (minimum weight) design for the primary structure of the living quarters modules in an earth-orbiting space base was investigated. Although the design is preliminary in nature, the supporting analysis is sufficiently thorough to provide a reasonably accurate weight estimate of the major components that are considered to comprise the structural weight of the space base.

Grissom, David S.↗
NASA NTRS1975

Space-based solar power conversion and delivery systems (study), engineering analysis

A systems analysis of synchronous, orbit-based power generation and relay systems that could be operational in the 1990's is described along with a comparison with earth-based systems to be operational in the same time frame. Operational and economic requirements for the orbiting systems and near term research activities which will be required to assure feasibility, development, launch and operational capabilities of such systems in the post- 1990 time frame are examined.

Nathan, C. A.↗
NASA NTRS1976

Space-based solar power conversion and delivery systems study. Volume 2: Engineering analysis of orbital systems

Program plans, schedules, and costs are determined for a synchronous orbit-based power generation and relay system. Requirements for the satellite solar power station (SSPS) and the power relay satellite (PRS) are explored. Engineering analysis of large solar arrays, flight mechanics and control, transportation, assembly and maintenance, and microwave transmission are included.

Source record↗
NASA NTRS1976

Space-based power conversion and power relay systems: Preliminary analysis of alternate systems

The results are presented of nine months of technical study of non-photovoltaic options for the generation of electricity for terrestrial use by satellite power stations (SPS). A concept for the augmentation of ground-based solar power plants by orbital sunlight reflectors was also studied. Three SPS types having a solar energy source and two which used nuclear reactors were investigated. Data derived for each included: (1) configuration definition, including mass statement; (2) information for use in environmental impact assessment; (3) energy balance (ratio of energy produced to that required to achieve operation), and (4) development and other cost estimates. Cost estimates were dependent upon the total program (development, placement and operation of a number of satellites) which was postulated. This postulation was based upon an analysis of national power capacity trends and guidelines received from MSFC.

Source record↗
NASA NTRS1976

Systems definition space-based power conversion systems

Potential space-located systems for the generation of electrical power for use on Earth are discussed and include: (1) systems producing electrical power from solar energy; (2) systems producing electrical power from nuclear reactors; and (3) systems for augmenting ground-based solar power plants by orbital sunlight reflectors. Systems (1) and (2) would utilize a microwave beam system to transmit their output to Earth. Configurations implementing these concepts were developed through an optimization process intended to yield the lowest cost for each. A complete program was developed for each concept, identifying required production rates, quantities of launches, required facilities, etc. Each program was costed in order to provide the electric power cost appropriate to each concept.

Source record↗
NASA NTRS1971

Review of Orbital Propellant Transfer Techniques and the Feasibility of a Thermal Bootstrap Propellant Transfer Concepts

This study was performed in support of the NASA Task B-2 Study Plan for Space Basing. The nature of space-based operations implies that orbital transfer of propellant is a prime consideration. The intent of this report is (1) to report on the findings and recommendations of existing literature on space-based propellant transfer techniques, and (2) to determine possible alternatives to the recommended methods. The reviewed literature recommends, in general, the use of conventional liquid transfer techniques (i.e., pumping) in conjunction with an artificially induced gravitational field. An alternate concept that was studied, the Thermal Bootstrap Transfer Process, is based on the compression of a two-phase fluid with subsequent condensation to a liquid (vapor compression/condensation). This concept utilizes the intrinsic energy capacities of the tanks and propellant by exploiting temperature differentials and available energy differences. The results indicate the thermodynamic feasibility of the Thermal Bootstrap Transfer Process for a specific range of tank sizes, temperatures, fill-factors and receiver tank heat transfer coefficients.

Yoshikawa, H. H.↗
NASA NTRS1993

Charge-exchange erosion studies of accelerator grids in ion thrusters

A particle simulation model is developed to study the charge-exchange grid erosion in ion thrusters for both ground-based and space-based operations. Because the neutral gas downstream from the accelerator grid is different for space and ground operation conditions, the charge-exchange erosion processes are also different. Based on an assumption of now electric potential hill downstream from the ion thruster, the calculations show that the accelerator grid erosion rate for space-based operating conditions should be significantly less than experimentally observed erosion rates from the ground-based tests conducted at NASA Lewis Research Center (LeRC) and NASA Jet Propulsion Laboratory (JPL). To resolve this erosion issue completely, we believe that it is necessary to accurately measure the entire electric potential field downstream from the thruster.

Peng, Xiaohang↗
NASA NTRS1972

In-space propellant logistics. Volume 4: Project planning data

The prephase A conceptual project planning data as it pertains to the development of the selected logistics module configuration transported into earth orbit by the space shuttle orbiter. The data represents the test, implementation, and supporting research and technology requirements for attaining the propellant transfer operational capability for early 1985. The plan is based on a propellant module designed to support the space-based tug with cryogenic oxygen-hydrogen propellants. A logical sequence of activities that is required to define, design, develop, fabricate, test, launch, and flight test the propellant logistics module is described. Included are the facility and ground support equipment requirements. The schedule of activities are based on the evolution and relationship between the R and T, the development issues, and the resultant test program.

Source record↗
NASA NTRS1972

The oscillator strengths of the SO /A 3Pi/-/X 3Sigma-/ band systems.

The oscillator strengths for these SO transition band systems are calculated using RKR Franck-Condon factors and the radiative lifetime previously derived from electron-beam phase-shift measurements by Smith (1971). The SO transition concerned is of considerable astrophysical importance in the search for SO in the interstellar medium by means of space-based telescopes with monochromators since the transition probability is concentrated, as shown, in relatively few transitions from the ground state.

Smith, W. H.↗
NASA NTRS1975

Overcoming two significant hurdles to space power generation Transportation and assembly

The design of large, space-based power generation satellites is strongly influenced by the transportation modes available and the assembly methods adopted. Flight plans for assembly are explored using the Space Shuttle as the transport vehicle. Future heavy-lift launch systems are postulated, and their impact on assembly cost of operational Solar Satellite Power Stations (SSPS) presented. Sensitivity to various levels of ground detail parts prefabrication are compared to corresponding levels of orbital fabrication. Assumptions concerning the degree of human skills are outlined, and related to the method of assembly. Cost comparisons and recommendations for continued studies are developed.

Kline, R.↗
NASA NTRS1975

The U.S. SEASAT program

The SEASAT program is a space-based operational oceanographic measurement system, which will be capable of providing continuous, all-weather, world-wide, timely data on global ocean dynamics and other physical properties of practical importance to a wide community of governmental and private sector users. This paper describes user requirements, case studies of projected applications, the sensor systems employed, and testing programs.

Mccandless, S. W.↗
NASA NTRS1975

The evolution of the Tracking and Data Relay Satellite System /TDRSS/

Certain limitations of a ground-based network of remote tracking stations for communications with spacecraft are to be overcome by making use of a space-based network. Studies related to the development of a Tracking and Data Relay Satellite System (TDRSS) are discussed. The TDRSS is to function as an integral part of the post-1980 NASA Spaceflight Tracking and Data Network (STDN). The TDRSS will consist of two operational Tracking and Data Relay (TDR) spacecraft separated by at least 130 deg in longitude. According to current planning, the STDN will also include five ground-based sites, for support of users with orbital altitudes greater than approximately 2000 km, and two launch support sites.

Godfrey, R. D.↗