Search NASA⌕ Search

SEARCH · Search NASA

Results for “transportation 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.

Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.

At least 145 records · Page 8
All sourcesNASA NTRSDOE OSTI
DOE OSTI2023

Electrifying the U.S. Transportation System with the Joint Office

The Joint Office of Energy and Transportation is accelerating an electrified transportation system that is convenient, reliable, affordable, accessible, and equitable. The Joint Office was created under the Bipartisan Infrastructure Law (BIL) to leverage the combined expertise of the U.S. Departments of Energy and Transportation. This is an overview fact sheet describing the Joint Office of Energy and Transportation.

ADVANCED PROPULSION SYSTEMS↗
NASA NTRS1978

Space transportation systems, 1980-2000

An overview of projected space transportation systems for the 1980-2000 period is presented. Methods for meeting the requirements in that area are documented through a description of the Space Shuttle and its current upper stages, reusable transfer vehicles, Shuttle uprating, fully reusable and single-stage transports, heavy lift vehicles, and advanced vehicles for orbital transfer and lunar landing. The structure of the liquid oxygen/liquid hydrogen boosters, cryogenic propellants, whose main propulsion system is a derivative of the RL-10 engine used in the Centaur launch, and mixed mode propulsion engine is also described, as is the flyback booster concept and such related issues as propellants and rocket engines, staging velocity, configuration shape, and whether it should be manned or unmanned. Especially noted are proposed propulsion systems going beyond the present Shuttle such as the nuclear and electric propulsion concepts, the resistojet, using liquid hydrogen, ion thruster, using argon, magnetoplasmadynamic thrusters, solar thermal rocket, and solar sail concept where the basic idea is to use a 'sail' of thin reflective material to generate a net force by reflection of solar radiation.

Cohan, C. J.↗
NASA NTRS1976

OAST Space Theme Workshop. Volume 2: Theme summary. 6: Advanced transportation systems. A: Theme statement. B. 26 April 1976 presentation. C. Theme summary. D. Initiative actions

Technology requirements for an integrated space transportation system capability which will allow the nation to use space efficiently, reliably, and routinely in the years between 1985 and 2000 with a significant return on invested resources will build on the currently defined space transportation system using shuttle, the IUS, and the advanced upper stage such as the solar electric propulsion system. Contributing technologies should include those which support (1) total reusability with minimal refurbishment; (2) responsiveness to high launch rate requirements when operation and energy are the predominant recurring costs; and (3) maximum flexibility in operation between earth and LEO and between LEO and GEO. Initiatives undertaken to advance the heavy lift to launch vehicles, single stage to orbit vehicles, and orbit transfer vehicles are listed.

Source record↗
NASA NTRS1975

Mission roles for the Solar Electric Propulsion Stage (SEPS) with the space transportation system. Volume 1: Executive summary

A study was conducted to determine the characteristics of solar electric propulsion stage (SEPS) for the space transportation system. Emphasis is placed on the rationale leading to the concepts for the development and operations program which enhances the cost effectiveness of the SEPS operating with the space transportation system. The approach in describing design concepts and configurations is concerned with the decision controlling factors and selection criteria. The mission roles for the SEPS in accomplishing proposed space activities are defined.

Hammock, D. M.↗
NASA NTRS2009

Space Transportation System Availability Relationships to Life Cycle Cost

Future space transportation architectures and designs must be affordable. Consequently, their Life Cycle Cost (LCC) must be controlled. For the LCC to be controlled, it is necessary to identify all the requirements and elements of the architecture at the beginning of the concept phase. Controlling LCC requires the establishment of the major operational cost drivers. Two of these major cost drivers are reliability and maintainability, in other words, the system's availability (responsiveness). Potential reasons that may drive the inherent availability requirement are the need to control the number of unique parts and the spare parts required to support the transportation system's operation. For more typical space transportation systems used to place satellites in space, the productivity of the system will drive the launch cost. This system productivity is the resultant output of the system availability. Availability is equal to the mean uptime divided by the sum of the mean uptime plus the mean downtime. Since many operational factors cannot be projected early in the definition phase, the focus will be on inherent availability which is equal to the mean time between a failure (MTBF) divided by the MTBF plus the mean time to repair (MTTR) the system. The MTBF is a function of reliability or the expected frequency of failures. When the system experiences failures the result is added operational flow time, parts consumption, and increased labor with an impact to responsiveness resulting in increased LCC. The other function of availability is the MTTR, or maintainability. In other words, how accessible is the failed hardware that requires replacement and what operational functions are required before and after change-out to make the system operable. This paper will describe how the MTTR can be equated to additional labor, additional operational flow time, and additional structural access capability, all of which drive up the LCC. A methodology will be presented that provides the decision makers with the understanding necessary to place constraints on the design definition. This methodology for the major drivers will determine the inherent availability, safety, reliability, maintainability, and the life cycle cost of the fielded system. This methodology will focus on the achievement of an affordable, responsive space transportation system. It is the intent of this paper to not only provide the visibility of the relationships of these major attribute drivers (variables) to each other and the resultant system inherent availability, but also to provide the capability to bound the variables, thus providing the insight required to control the system's engineering solution. An example of this visibility is the need to provide integration of similar discipline functions to allow control of the total parts count of the space transportation system. Also, selecting a reliability requirement will place a constraint on parts count to achieve a given inherent availability requirement, or require accepting a larger parts count with the resulting higher individual part reliability requirements. This paper will provide an understanding of the relationship of mean repair time (mean downtime) to maintainability (accessibility for repair), and both mean time between failure (reliability of hardware) and the system inherent availability.

Rhodes, Russel E.↗
NASA NTRS1972

Study of aircraft in intraurban transportation systems

A systems analysis was conducted to define the technical economic and operational characteristics of an aircraft transportation system for short-range intracity commutor operations. The analysis was for 1975 and 1985 in the seven county, Detroit, Michigan area. STOL and VTOL aircraft were studied in sizes from 40 to 120 passengers. The preferred vehicle for the Detroit area was the deflected slipstream STOL. Since the study was parametric in nature, it is applicable to generalization, and it was concluded that a feasible intraurban air transportation system could be developed in many viable situations.

Stout, E. G.↗
NASA NTRS1997

Space Transportation Systems Using Tethers

The groundwork has been laid for tether space transportation systems. NASA has developed tether technology for space applications since the 1960's. Important recent milestones include retrieval of a tether in space (TSS-1, 1992), successful deployment of a 20-km-long tether in space (SEDS-1, 1993), and operation of an electrodynamic tether with tether current driven in both directions-power and thrust modes (PMG, 1993). Various types of tethers and systems can be used for space transportation. Short electrodynamic tethers can use solar power to 'push' against a planetary magnetic field to achieve propulsion without the expenditure of propellant. The planned Propulsive Small Expendable Deployer System (ProSEDS) experiment will demonstrate electrodynamic tether thrust during its flight in early 2OOO. Utilizing completely different physical principles, long non-conducting tethers can exchange momentum between two masses in orbit to place one body into a transfer orbit for lunar and planetary missions. Recently completed system studies of this concept indicate that it would be a relatively low-cost in-space asset with long-term multimission capability. Both methods of using tethers for space transportation and propulsion are described in the paper.

Johnson, Les↗
NASA NTRS1977

User access to the National Space Transportation System

Economical and efficient use of the Space Transportation System (STS) will depend to a large extent on the ability to utilize standard procedures and operations; and for early users transitioning from expendable launch vehicles, the ability to use previous procedures and documentation. Users of the STS will need to know how and where to obtain the information needed to know the STS capabilities, how to obtain a flight assignment, costs involved, and processing of their payloads in preparation for launch.

Mccoy, H. E.↗
NASA NTRS1981

Transportation systems evaluation methodology development and applications, phase 3

Transportation systems or proposed changes in current systems are evaluated. Four principal evaluation criteria are incorporated in the process, operating performance characteristics as viewed by potential users, decisions based on the perceived impacts of the system, estimating what is required to reduce the system to practice; and predicting the ability of the concept to attract financial support. A series of matrix multiplications in which the various matrices represent evaluations in a logical sequence of the various discrete steps in a management decision process is used. One or more alternatives are compared with the current situation, and the result provides a numerical rating which determines the desirability of each alternative relative to the norm and to each other. The steps in the decision process are isolated so that contributions of each to the final result are readily analyzed. The ability to protect against bias on the part of the evaluators, and the fact that system parameters which are basically qualitative in nature can be easily included are advantageous.

Kuhlthau, A. R.↗
NASA NTRS1988

A transportation system for routine visits to Mars

A conceptual transportation system designed for routing visits to Mars is described. The system is planned to provide routine support for a base population of roughly 20 people on Mars. The system utilizes in situ resource production to support Mars missions and generates artificial gravity while delivering additional consumables. The system uses cycling space stations for support. Possible lunar resource capabilities, taxi vehicles, and technology and human issues are examined.

Roberts, Barney B.↗
NASA NTRS1989

Propulsive options for a manned Mars transportation system

In this investigation, five potential manned Mars transportation systems are compared. These options include: (1) a single vehicle, chemically propelled (CHEM) option, (2) a single vehicle, nuclear thermal propulsion (NTP) option, (3) a single vehicle solar electric propulsion (SEP) option, (4) a single vehicle hybrid nuclear electric propulsion (NEP)/CHEM option, and (5) a dual vehicle option (NEP cargo spacecraft and CHEM manned vehicle). In addition to utilizing the initial vehicle weight in low-earth orbit as a measure of mission feasibility, this study addresses the major technological barriers each propulsive scenario must surpass. It is shown that instead of a single clearly superior propulsion system, each means of propulsion may be favored depending upon the specified program policy and the extent of the desired manned flight time. Furthermore, the effect which aerobraking and multiple transfer cycles have upon mission feasibility is considered.

Braun, Robert D.↗
NASA NTRS1994

Integral habitat transport system

In the 1993 Fall quarter, the ME 4182 design class was sponsored to study various scenarios that needed to be studied for Martian travel. The class was sponsored by NASA and there were several different design projects. The design that group three chose was an integral transport system for a Martian habitat. An integral transport system means the design had to be one that was attached to the habitat. There were several criteria that the design had to meet. Group three performed an in depth study of the Martian environment and looked at several different design ideas. The concept group three developed involved the use of kinematic linkages and the use of Martian gravity to move the habitat. The various design concepts, the criteria matrices and all other aspects that helped group three develop their design can be found in their 1993 ME 4182 design report. Now it is Winter quarter 1994 and group three is faced with another problem. The problem is building a working prototype of their Fall design. The limitations this quarter were the parts. The group had to make the prototype work with existing manufactured parts or make the parts themselves in a machine shop. The prototype was scaled down roughly about twelve times smaller than the original design. The following report describes the actions taken by group three to build a working model.

Elliott, Bill↗
NASA NTRS1988

Fracture control requirements for payloads using the National Space Transportation System (NSTS)

The purpose of this document is to establish the fracture control requirements for all payload hardware to be launched or retrieved using the National Space Transportation System (NSTS). Meeting these requirements implements the minimum fracture control requirements of NHB 1700.7, 'Safety Policy and Requirements for Payloads Using the Space Transportation System (STS).' All NSTS payload fracture control shall be in accordance with the requirements stated herein.

George A Rodney↗
NASA NTRS1976

An exploratory study to determine the integrated technological air transportation system ground requirements of liquid-hydrogen-fueled subsonic, long-haul civil air transports

An exploratory study was conducted to evaluate the feasibility and cost impact of implementing a liquid-hydrogen-fueled (LHz), air transport support system at Chicago-O’Hare International Airport. The study assumed an available supply of hydrogen to the airport boundary. It also assumed that the present widebody fleet at O’Hare was replaced by 400 passenger, LH2-fueled aircraft operating on the current frequency schedule and route network. The LH2 aircraft configurations used in this study were developed during a previous NASA-sponsored study. A baseline air terminal concept was developed which permitted airlines and the airport to operate JP- or LH2-fueled aircraft at common terminal gates. The concept included installation of a hydrogen liquefaction and storage facility on airport property, as well as the fuel distribution system. The capital investment and hydrogen-related operating costs to the airlines were estimated. The study concluded that the system would be technically and operationally feasible at O’Hare, and that economics would be a prime factor in future decisions regarding the use of LH2 as an air transport fuel. Research and technology recommendations were made to improve component efficiency/reliability. The study also concluded that additional investigation should be conducted on the implementation of a nationwide or worldwide LH2 air transportation system, to understand fully the operational and economic implications of the total system, before decisions could be made relative to committing to this option.

Hydrogen↗
NASA NTRS1973

BEAMR: An interactive graphic computer program for design of charged particle beam transport systems

A computer program for a PDP-15 is presented which calculates, to first order, the characteristics of charged-particle beam as it is transported through a sequence of focusing and bending magnets. The maximum dimensions of the beam envelope normal to the transport system axis are continuously plotted on an oscilloscope as a function of distance along the axis. Provision is made to iterate the calculation by changing the types of magnets, their positions, and their field strengths. The program is especially useful for transport system design studies because of the ease and rapidity of altering parameters from panel switches. A typical calculation for a system with eight elements is completed in less than 10 seconds. An IBM 7094 version containing more-detailed printed output but no oscilloscope display is also presented.

Leonard, R. F.↗
NASA NTRS1978

Technology requirements for advanced earth orbital transportation system. Volume 1: Executive summary

Normal technology requirements applicable to Single Stage to Orbit (SSTO) systems were projected to the 1985 time period. These technology projections were then incorporated in a vehicle design analysis of three different operational concepts resulting in four configurations of a Single Stage to Orbit system. The resultant performance, weights and costs of each concept were then compared and a system concept selected. A figure of merit was developed for advanced technology programs based on a cost/performance basis. The selected advanced technology programs were then used to reassess the vehicle to determine the impact on performance, weight and cost. Based on study results, recommendations are provided in technology areas associated with earth orbit transportation systems. The recommendations address advanced space transportation system design considerations, both hardware and software technolgoy program requirements.

Hepler, A. K.↗
NASA NTRS1991

A PC-based bus monitor program for use with the transport systems research vehicle RS-232 communication interfaces

Experiment critical use of RS-232 data busses in the Transport Systems Research Vehicle (TSRV) operated by the Advanced Transport Operating Systems Program Office at the NASA Langley Research Center has recently increased. Each application utilizes a number of nonidentical computer and peripheral configurations and requires task specific software development. To aid these development tasks, an IBM PC-based RS-232 bus monitoring system was produced. It can simultaneously monitor two communication ports of a PC or clone, including the nonstandard bus expansion of the TSRV Grid laptop computers. Display occurs in a separate window for each port's input with binary display being selectable. A number of other features including binary log files, screen capture to files, and a full range of communication parameters are provided.

Easley, Wesley C.↗