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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 163 records · Page 9
All sourcesNASA NTRSDOE OSTI
NASA NTRS1990

A test matrix sequencer for research test facility automation

The hardware and software configuration of a Test Matrix Sequencer, a general purpose test matrix profiler that was developed for research test facility automation at the NASA Lewis Research Center, is described. The system provides set points to controllers and contact closures to data systems during the course of a test. The Test Matrix Sequencer consists of a microprocessor controlled system which is operated from a personal computer. The software program, which is the main element of the overall system is interactive and menu driven with pop-up windows and help screens. Analog and digital input/output channels can be controlled from a personal computer using the software program. The Test Matrix Sequencer provides more efficient use of aeronautics test facilities by automating repetitive tasks that were once done manually.

Mccartney, Timothy P.↗
NASA NTRS1980

Shuttle remote manipulator system hardware test facility

The shuttle remote manipulator (RMS) is designed and built for operations in a zero gravity environment. As such, the ground test facility for the integrated RMS must simulate conditions which support verification of the overall system performance. In order to allow ground test operations, a test facility was constructed with an area of 60 ft. x 120 ft. and extremely tight tolerances on floor flatness and slope. An air bearing support structure was designed for the RMS to operate with 4 degrees of freedom. The RMS system test facility and systems tests conducted to date are described.

Wagner-Bartak, C. G.↗
NASA NTRS1993

Space Chemical Propulsion Test Facilities at NASA Lewis Research Center

The NASA Lewis Research Center, located in Cleveland, Ohio, has a number of space chemical propulsion test facilities which constitute a significant national space testing resource. The purpose of this paper is to make more users aware of these test facilities and to encourage their use through cooperative agreements between the government, industry, and universities. Research which is of interest to the government is especially encouraged and often can be done in a cooperative manner that best uses the resources of all parties. An overview of the Lewis test facilities is presented.

Urasek, Donald C.↗
NASA NTRS1973

Test facility for 6000 hour life test of 30 cm mercury ion thruster

The environmental and instrumentation requirements for long term testing of electrical propulsion thrusters which impose severe and unusual requirements upon the simulation facility were studied. High speed ions ejected from a mercury thruster erode material from collecting surfaces, which is then scattered and redeposited upon other surfaces, with resultant damage to the chamber and test article. By collecting the thruster plume on a frozen mercury surface damage to the thruster and chamber by back-scattered erosion products was minimized. Provisions for unattended operation, remote data acquisition, personnel safety, and instrumentation for assessing thruster performance are also discussed.

Caldwell, J. J.↗
NASA NTRS1990

High power, high frequency component test facility

The NASA Lewis Research Center has available a high frequency, high power laboratory facility for testing various components of aerospace and/or terrestrial power systems. This facility is described here. All of its capabilities and potential applications are detailed.

Roth, Mary Ellen↗
NASA NTRS1990

Low thrust rocket test facility

A low thrust chemical rocket test facility has recently become operational at the NASA-Lewis. The new facility is used to conduct both long duration and performance tests at altitude over a thruster's operating envelope using hydrogen and oxygen gas for propellants. The facility provides experimental support for a broad range of objectives, including fundamental modeling of fluids and combustion phenomena, the evaluation of thruster components, and life testing of full rocket designs. The major mechanical and electrical systems are described along with aspects of the various optical diagnostics available in the test cell. The electrical and mechanical systems are designed for low down time between tests and low staffing requirements for test operations. Initial results are also presented which illustrate the various capabilities of the cell.

Arrington, Lynn A.↗
NASA NTRS1990

Low thrust rocket test facility

A low thrust chemical rocket test facility has recently become operational at the NASA-Lewis. The new facility is used to conduct both long duration and performance tests at altitude over a thruster's operating envelope using hydrogen and oxygen gas for propellants. The facility provides experimental support for a broad range of objectives, including fundamental modeling of fluids and combustion phenomena, the evaluation of thruster components, and life testing of full rocket designs. The major mechanical and electrical systems are described along with aspects of the various optical diagnostics available in the test cell. The electrical and mechanical systems are designed for low down time between tests and low staffing requirements for test operations. Initial results are also presented which illustrate the various capabilities of the cell.

Arrington, Lynn A.↗
NASA NTRS1994

Strategic avionics technology definition studies. Subtask 3-1A3: Electrical Actuation (ELA) Systems Test Facility

Future aerospace vehicles will require use of the Electrical Actuator systems for flight control elements. This report presents a proposed ELA Test Facility for dynamic evaluation of high power linear Electrical Actuators with primary emphasis on Thrust Vector Control actuators. Details of the mechanical design, power and control systems, and data acquisition capability of the test facility are presented. A test procedure for evaluating the performance of the ELA Test Facility is also included.

Rogers, J. P.↗
NASA NTRS1972

The design of components for an advanced Rankine cycle test facility.

The design of a facility for testing components of an advanced Rankine cycle power system is summarized. The facility is a three-loop system in which lithium, potassium and NaK-78 are the working fluids of the primary, secondary and heat-rejection loops, respectively. Design bases and performance predictions for the major loop components, including the lithium heater and the potassium boiler, condenser and preheater, are outlined.

Bond, J. A.↗
NASA NTRS2004

1998 Calibration of the Mach 4.7 and Mach 6 Arc-Heated Scramjet Test Facility Nozzles

A calibration of the Arc-Heated Scramjet Test Facility (AHSTF) Mach 4.7 and Mach 6 nozzles was performed in 1998. For each nozzle, three different typical facility operating test points were selected for calibration. Each survey consisted of measurements, at 340 separate locations across the 11 inch square nozzle exit plane, of pitot pressure, static pressure, and total temperature. Measurement density was higher (4/inch) in the boundary layer near the nozzle wall than in the core nozzle flow (1/inch). The results generated for each of these calibration surveys were contour plots at the nozzle exit plane of the measured and calculated flow properties which completely defined the thermodynamic state of the nozzle exit flow. An area integration of the mass flux at the nozzle exit for each survey was compared to the AHSTF mass flow meter results to provide an indication of the overall quality of the calibration performed. The percent difference between the integrated nozzle exit mass flow and the flow meter ranged from 0.0 to 1.3 percent for the six surveys. Finally, a comparison of this 1998 calibration was made with the 1986 calibration. Differences of less than 10 percent were found within the nozzle core flow while in the boundary layer differences on the order of 20 percent were quite common.

Witte, David W.↗
NASA NTRS2017

Inlet Acoustic Data from a High Bypass Ratio Turbofan Rotor in an Internal Flow Component Test Facility

In February 2017, aerodynamic and acoustic testing was completed on a scale-model high bypass ratio turbofan rotor, R4, in an internal flow component test facility. The objective of testing was to determine the aerodynamic and acoustic impact of fan casing treatments designed to reduce noise. The baseline configuration consisted of the R4 rotor with a hardwall fan case. Data are presented for a baseline acoustic run with fan exit instrumentation removed to give a clean acoustic configuration.

Turbofan↗
NASA NTRSDate not supplied

Managing Spacecraft Risk with Space Environments Testing via Process Safety Management at the NASA Neil A. Armstrong Test Facility (GRC-ATF)

The NASA Glenn Research Center’s Neil A. Armstrong Test Facility (GRC-ATF) is home to several unique, world class aerospace test facilities, including the In-Space Propulsion (ISP) Facility. The ISP Facility is NASA’s largest chamber designed to store and transfer large quantities of liquid hydrogen and liquid oxygen; and is designed to support developmental testing of upper stage chemical propulsion systems as well as fully integrated stages. The facility is also capable of providing thermal-vacuum simulation services to support testing of aerospace hardware, Cryogenic Fluid Management (CFM) systems and other In-Space propulsion programs. The U.S. Occupational Safety and Health Administration’s (OSHA) Process Safety Management (PSM) of Highly Hazardous Chemicals Standard (29 CFR 1910.119) is an analytical tool focused on preventing the release of chemicals and other energy sources. In a short timeframe, GRC-ATF was required to restore a PSM Program at the Facility. Although the summarized work is specific to the ground testing of rockets and space vehicles, the ISP Facility is used to verify system level requirements, some of these are safety requirements, and thus key to managing risks in space.

Safety↗
NASA NTRS1981

Operating characteristics of the Langley Mach 7 Scramjet Test Facility

Operating characteristics of the Langley Mach 7 Scramjet Test Facility are described. The facility is designed for testing airframe integrated scramjet (supersonic combustion ramjet) engine models. Features include duplication of the flight Mach number total enthalpy, flight altitude simulation, and simulation of engine airframe integration effects such a bow shock wave precompression and boundary layer ingestion by the engine. Data obtained from facility calibration and from tests of a hydrogen burning, airframe integrated scramjet are discussed. An adverse interaction between the facility flow and the scramjet engine flow during combustion of the fuel is described.

Guy, R. W.↗
NASA NTRS1980

Spacecraft charging technology in the satellite X-ray test facility

A satellite X-ray test facility (SXTF) is planned for studying system generated electromagnetic pulse effects on full scale, operational spacecraft. The environment created by a distant, high altitude nuclear burst can be simulated using pulsed X-ray sources. The facility is to be installed in a thermal vacuum chamber with dimensions greater then 10 m diameter and 20 m height and equipped with solar simulators and equipment for simulating the charging environment of space. The spacecraft charging system consists of several low energy electron and hydrogen ion sources (5-25 keV), one or two medium energy electron accelerators (150-300 keV), an array of vacuum ultraviolet lamps, and geomagnetic field suppression coils. Military, scientific, and commercial spacecraft can be tested before launching into the radiation environment of space. construction of SXTF is scheduled to begin in 1982 and the facility should be available for general use in 1984. Potential users are encouraged to express their needs for specific testing environments in SXTF.

Sponaugle, T. J.↗
NASA NTRS1977

ERDA/Lewis research center photovoltaic systems test facility

A national photovoltaic power systems test facility (of initial 10-kW peak power rating) is described. It consists of a solar array to generate electrical power, test-hardware for several alternate methods of power conversion, electrical energy storage systems, and an instrumentation and data acquisition system.

Forestieri, A. F.↗
NASA NTRS1994

High-speed seal and bearing test facility

The following topics are discussed in this viewgraph presentation: high speed seal/bearing rig background, project status, facility features, test rig capabilities, EMD testing advantages, and future opportunities.

Panos, Jean B.↗