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Results for “high performance”

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 1,747 records · Page 97
All sourcesNASA NTRSDOE OSTI
NASA NTRS1979

A two-dimensional thermal analysis of a new high-performance tubular solar collector

The first of two articles are presented which describe and analyze the thermal performance of a vacuum tube solar collector. The assumptions and mathematical modeling are presented. The problem is reduced to the formulation of two simultaneous linear differential equations characterizing the collector thermal behavior. After applying the boundary conditions, a general solution is obtained which is found similar to the general Hottel, Whillier and Bliss form but with a complex flow factor.

Lansing, F. L.↗
NASA NTRS1978

Acceleration sensitivity compensation in high performance crystal oscillators

Two approaches to achieving reduced acceleration sensitivity of crystal oscillators are discussed. The first involves electronic compensation within the frequency control loop. The second utilizes two resonators of comparable acceleration sensitivity to compensate each other. Problems encountered in matching and tuning the resonators are discussed, as well as orientation symmetry of the frequency deviation patterns. Results on frequency stability which reflect an improved static sensitivity are presented.

Emmons, D. A.↗
NASA NTRS1978

Ultra-thin silicon solar cells for high performance panel applications

Solar cells have been fabricated which achieved the highest power to mass ratios and radiation stability yet reported for silicon devices. The thinnest cells (.04 mm) had initial efficiencies in excess of 2 watts per gram (AMO) and 1.7 watts per gram after an irradiation of 1 x 10 to the 15th equivalent 1 MeV electrons per square centimeter. The cells have been successfully interconnected by welding and filtered using a FEP bonded, ceria-doped microsheet of six mil thickness. Handling losses during cell manufacture and panel assembly may be minimized through the use of an integral reinforcing perimeter or ribs which remove almost all restrictions on cell thickness and area. Such a cell is typically composed of a main section which can be as thin as 0.015 mm and is supported at the edge by a thicker border (0.20 mm) of silicon.

Gay, C. F.↗
NASA NTRS1978

Analytical design of a high performance stability and control augmentation system for a hingeless rotor helicopter

A stability and control augmentation system (SCAS) was designed based on a set of comprehensive performance criteria. Linear optimal control theory was applied to determine appropriate feedback gains for the stability augmentation system (SAS). The helicopter was represented by six-degree-of-freedom rigid body equations of motion and constant factors were used as weightings for state and control variables. The ratio of these factors was employed as a parameter for SAS analysis and values of the feedback gains were selected on this basis to satisfy three of the performance criteria for full and partial state feedback systems. A least squares design method was then applied to determine control augmentation system (CAS) cross feed gains to satisfy the remaining seven performance criteria. The SCAS gains were then evaluated by nine degree-of-freedom equations which include flapping motion and conclusions drawn concerning the necessity of including the pitch/regressing and roll/regressing modes in SCAS analyses.

Miyajima, K.↗
NASA NTRS1978

A systems approach to high performance oscillators

The purpose of this paper is to show how systems composed of multiple oscillators and resonators can achieve superior performance compared to a single oscillator. Experimental results are presented for two systems based on quartz crystals which provide state-of-the-art stability over a much wider range of averaging times than has been previously achieved. One system has achieved a factor of five improvement in noise floor compared to all previously reported results.

Stein, S. R.↗
NASA NTRS1979

Design and evaluation of high performance rocket engine injectors for use with hydrocarbon fuels

The feasibility of using a heavy hydrocarbon fuel as a rocket propellant is examined. A method of predicting performance of a heavy hydrocarbon in terms of vaporization effectiveness is described and compared to other fuels and to experimental test results. Experiments were done at a chamber pressure of 4137 KN/sq M (600 psia) with RP-1, JP-10, and liquefied natural gas as fuels, and liquid oxygen as the oxidizer. Combustion length effects were explored over a range of 21.6 cm (8 1/2 in) to 55.9 cm (22 in). Four injector types were tested, each over a range of mixture ratios. Further configuration modifications were obtained by reaming each injector several times to provide test data over a range of injector pressure drop.

Pavli, A. J.↗
NASA NTRS1979

Experimental Evaluation of a Low Emissions High Performance Duct Burner for Variable Cycle Engines (VCE)

An evaluation was conducted with a three stage Vorbix duct burner to determine the performance and emissions characteristics of the concept and to refine the configuration to provide acceptable durability and operational characteristics for its use in the variable cycle engine (VCE) testbed program. The tests were conducted at representative takeoff, transonic climb, and supersonic cruise inlet conditions for the VSCE-502B study engine. The test stand, the emissions sampling and analysis equipment, and the supporting flow visualization rigs are described. The performance parameters including the fuel-air ratio, the combustion efficiency/exit temperature, thrust efficiency, and gaseous emissions calculations are defined. The test procedures are reviewed and the results are discussed.

Lohmann, R. P.↗
NASA NTRS1980

Capillary acquisition devices for high-performance vehicles: Executive summary

Technology areas critical to the development of cryogenic capillary devices were studied. Passive cooling of capillary devices was investigated with an analytical and experimental study of wicking flow. Capillary device refilling with settled fluid was studied using an analytical and experimental program that resulted in successful correlation of a versatile computer program with test data. The program was used to predict Centaur D-1S LO2 and LH2 start basket refilling. Comparisons were made between the baseline Centaur D-1S propellant feed system and feed system alternatives including systems using capillary devices. The preferred concepts from the Centaur D-1S study were examined for APOTV and POTV vehicles for delivery and round trip transfer of payloads between LEO and GEO. Mission profiles were determined to provide propellant usage timelines and the payload partials were defined.

Blatt, M. H.↗
NASA NTRS1980

Field experiences with rotordynamic instability in high-performance turbomachinery

Two field situations illustrate the consequences of rotordynamic instability in centrifugal compressors. One involves the reinjection of produced gas into a North Sea oil formation for the temporary extraction of crude. The other describes on-shore compressors used to deliver natural gas from off-shore wells. The problems which developed and the remedies attempted in each case are discussed. Instability problems resulted in lost production, extended construction periods and costs, and heavy maintenance expenditures. The need for effective methods to properly identify the problem in the field and in the compressor design stage is emphasized.

Doyle, H. E.↗
NASA NTRS1979

A high performance porous flat-plate solar collector

A solar collector employing a porous matrix as a solar absorber and heat exchanger is presented and its application in solar air heaters is discussed. The collector is composed of a metallic matrix with a porous surface which acts as a large set of cavity radiators; cold air flows through the matrix plate and exchanges heat with the thermally stratified layers of the matrix. A steady-state thermal analysis of the collector is used to determine collector temperature distributions for the cases of an opaque surface matrix with total absorption of solar energy at the surface, and a diathermanous matrix with successive solar energy absorption at each depth. The theoretical performance of the porous flat plate collector is shown to exceed greatly that of a solid flat plate collector using air as the working medium for any given set of operational conditions. An experimental collector constructed using commercially available, low cost steel wool as the matrix has been found to have thermal efficiencies from 73 to 86%.

Lansing, F. L.↗
NASA NTRS1979

Design and evaluation of high performance rocket engine injectors for use with hydrocarbon fuels

An experimental program to determine the feasibility of using a heavy hydrocarbon fuel as a rocket propellant is reported herein. A method of predicting performance of a heavy hydrocarbon in terms of vaporization effectiveness is described and compared to other fuels and to experimental test results. The work was done at a chamber pressure of 4137 KN/sq M (600 psia) with RP-1, JP-10, and liquefied natural gas as fuels, and liquid oxygen as the oxidizer. Combustion length effects were explored over a range of 21.6 cm (8 1/2 in.) to 55.9 cm (22 in.). Four injector types were tested, each over a range of mixture ratios. Further configuration modifications were obtained by 'reaming' each injector several times to provide test data over a range of injector pressure drop.

Pavli, A. J.↗
NASA NTRS1980

A high performance multiplier processor for use with aerospace microcomputers

An MC68000 based microcomputer including a hardware multiplier processor has been designed and prototyped for a reentry vehicle navigation and control application. In this paper, the microcomputer is discussed with emphasis on the multiplier processor architecture, software control and theory of operation.

Pierce, P. E.↗
NASA NTRS1980

High performance cryogenic engines for orbit transfer vehicles

Evaluations of O2/H2 engine candidates in the 10K to 30K lb thrust class for Manned Orbit Transfer Vehicles (MOTV) and engine candidates using O2/H2, O2/RP-1, and O2/CH4 in the 100 to 3,000 lb thrust range for Cargo Orbit Transfer Vehicles (COTV) are discussed. Both space vehicles are part of the larger SPS concept. It is shown that the Advanced Expander Cycle O2/H2 engine for MOTV merits further study and investigations. COTV engine study has so far indicated that conventionally cooled O2/H2 and O2/CH4 engine candidates should be evaluated further, while advanced cooling schemes are required for O2/RP-1 concepts. With regard to MOTV, it is concluded that while no existing system meets the requirements of the Orbit Transfer Vehicles, the need for twin expander cycle engines is established because a single engine cannot provide a tolerable man-safety profile. With regard to COTV, it is stressed that advanced cooling concepts must be considered if other propellant combinations are to become competitive with O2/H2. Multistage centrifugal pumps are seen as the most promising concept.

Bassham, L. B.↗
NASA NTRS1981

Analysis of a high-performance tubular solar collector

This article analyzes the thermal performance of a new vacuum tube solar collector. The assumptions and mathematical modeling are presented. The problem is reduced to the formulation of two simultaneous linear differential equations characterizing the collector thermal behavior. After applying the boundary conditions, a general solution is obtained which is found similar to the general Hottel, Whillier and Bliss form, but with a complex flow factor. The details of the two-dimensional thermal model of the solar collector at steady state is also presented to include the computer simulation and the performance parameterization. Comparison of the simulated performance with the manufacturer's test data showed good agreement at wide ranges of operating conditions.

Lansing, F. L.↗
NASA NTRS1983

High-Performance Matrix Resins

State-of-the-art PMR polyimides provide good strength and light weight in wide variety of critical applications. However, improved processability and elevated temperature thermo-oxidative stability are desired in such polyimide systems. Resins, intended for use in advanced composites, adhesives, and neat resin articles, show improvements in both processability and elevatedtemperature stability over state-of-the-art PMR-15 polymers.

Pater, R. H.↗