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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 793 records · Page 44
All sourcesNASA NTRSDOE OSTI
NASA NTRS1974

Flight-test investigation of the aerodynamic characteristics and flow interference effects about the aft fuselage of the F-111A airplane

Static pressure measurements were made on the aft fuselage of an F-111A airplane to determine local flow characteristics and engine/airframe interaction effects. Data were obtained over the Mach number range from 0.5 to 2.0. Aspiration effects associated with low ejector nozzle expansion ratios reduced the local pressure coefficients particularly on the interfairing but also extending to the trailing edge of the nacelle. The presence of afterbodies also affected the behavior of the air flowing into and about the ejector nozzle. Pressures about the aft fuselage were improved by an increase in primary nozzle area at a supersonic speed. A comparison of wind-tunnel and flight-test results showed generally good agreement, although there was a large disparity in pressure level about the ejector nozzle. However, the shape of the data curves and the local flow behavior were basically similar.

Taillon, N. V.↗
NASA NTRS1973

OGO-6 experiment F-03

The results obtained with the retarding potential analyzer on the OGO-6 satellite are discussed. The information obtained during the OGO-6 flight concerned the following subjects: (1) measurement of electron flux density in the plasmasphere, (2) latitudinal variations of ion temperature, (3) heating in the nighttime ionosphere by conjugate photoelectrons, (4) longitudinal variation in equatorial ion temperature at low altitude, and (5) identification of heavy ions in the upper F region.

Hanson, W. B.↗
NASA NTRS1974

Extraction from flight data of longitudinal aerodynamic coefficients for F-8 aircraft with supercritical wing

The longitudinal aerodynamic derivatives of the F-8 aircraft with supercritical wing were obtained from flight data by a parameter-extraction algorithm at Mach numbers of 0.8, 0.9, and 0.98. A set of derivatives were obtained from which calculated aircraft responses were correlated almost identically with actual flight responses. In general, the trends of the extracted derivatives obtained by the algorithm agreed with those obtained by a Newton-Raphson method and with preliminary data from the Langley 8-foot transonic pressure tunnel. The wind-tunnel damping derivatives were, however, substantially higher than the converged damping derivatives possibly because of Reynolds number differences between flight and model tests.

Williams, J. L.↗
NASA NTRS1974

The partitioned strainrange fatigue behavior of coated and uncoated MAR-M-302 at 1000 C (1832 F) in ultrahigh vacuum

Elevated temperature (1000 C (1832 F)) vacuum fatigue tests have been conducted on uncoated and aluminide (PWA 45) coated cobalt-base MAR-M-302 alloy with the four different types of thermalmechanical reversed inelastic strain cycles (wave shapes) defined by the method of strainrange partitioning. Results of these tests indicated two major conclusions. First, there was no significant influence of the aluminide coating on the thermal-mechanical fatigue life of the MAR-M-302 alloy. Second, variations in the type of thermal-mechanical fatigue cycle applied caused significant variations of fatigue life for both coated and uncoated material. The longest lives were achieved with sigma sub pp type cycling, while the sigma sub cc cycle caused a reduction of fatigue life of about 1/2 order of magnitude with respect to the sigma sub pp life. The sigma sub cp type cycle caused a life reduction of between 1-1/2 and 2 orders of magnitude relative to the sigma sub pp life, while the sigma sub pc type cycle provided a fatigue life which appeared to be comparable to that generated by the sigma sub cc cycle.

Sheffler, K. D.↗
NASA NTRS1974

Flight-measured inlet pressure transients accompanying engine compressor surges on the F-111A airplane

Two-F-111A airplanes were subjected to conditions that caused engine compressor surges and accompanying duct hammershock pressure transients. Flight speed ranged from Mach 0.71 to Mach 2.23, and altitude varied from approximately 3200 meters to 14,500 meters. A wide range of compressor pressure ratios was covered. Stabilized free-stream, engine, and duct conditions were established before each compressor surge. Dynamic pressure instrumentation at the compressor face and in the duct recorded the pressure transients associated with the surges. Hammershock pressures were analyzed with respect to the stabilized conditions preceding the compressor surges. The hammershock transients caused large pressure rises at the compressor face and in the duct. Hammershock pressure ratios at the compressor face were not affected by free-stream Mach number or altitude but were functions of engine variables, such as compressor pressure ratio. The maximum hammershock pressure ratio of approximately 1.83 occurred at a compressor pressure ratio of approximately 21.7.

Nugent, J.↗
NASA NTRS1972

Fastening on the F-14A for cost effective fatigue resistance

Cost effectiveness airframe considerations dictated a variable geometry wing design that requires weight optimization, maximum working stress resistance and minimum fatigue concentration factors. The extensive use of titanium structural materials employed electron beam welding methods and interference fit fastening techniques as principle mechanical joining means for economic F-14A production and reliability engineering.

Beal, B. H.↗
NASA NTRS1972

Mechanical fasteners for 1800 F and above

The state-of-the-art of mechanical fasteners is reviewed for 1800 F and above. Some of the problems associated with the use of these fasteners are discussed in view of the projected requirements of the space shuttle for metallic heal shields which would be reusable for 100 cycles of orbit and reentry.

Roach, T. A.↗
NASA NTRS1974

Design and flight experience with a digital fly-by-wire control system in an F-8 airplane

A digital fly-by-wire flight control system was designed, built, and for the first time flown in an airplane. The system, which uses components from the Apollo guidance system, is installed in an F-8 airplane as the primary control system. A lunar module guidance computer is the central element in the three-axis, single-channel, multimode, digital control system. A triplex electrical analog system which provides unaugmented control of the airplane is the only backup to the digital system. Flight results showed highly successful system operation, although the trim update rate was inadequate for precise trim changes, causing minor concern. The use of a digital system to implement conventional control laws proved to be practical for flight. Logic functions coded as an integral part of the control laws were found to be advantageous. Although software verification required extensive effort, confidence in the software was achieved.

Deets, D. A.↗
NASA NTRS1974

ATS-F/GEOS-C satellite to satellite tracking data processing consideration

The satellite to satellite tracking data unique processing considerations are presented. The strategy to be employed in the application of data processing routines to the ATS-F/GEOS-C satellite to satellite tracking experiment is described. When these considerations are included, studies, analysis and simulations predict an orbital position uncertainty of less than 15 meters and a velocity uncertainty of less than 1.5 millimeters per second.

Bryan, J. W.↗
NASA NTRS1974

Development of strain gages for use to 1311 K (1900 F)

A high temperature electric resistance strain gage system was developed and evaluated to 1366 K (2000 F) for periods of at least one hour. Wire fabricated from a special high temperature strain gage alloy (BCL-3), was used to fabricate the gages. Various joining techniques (NASA butt welding, pulse arc, plasma needle arc, and dc parallel gap welding) were investigated for joining gage filaments to each other, gage filaments to lead-tab ribbons, and lead-tab ribbons to lead wires. The effectiveness of a clad-wire concept as a means of minimizing apparent strain of BCL-3 strain gages was investigated by sputtering platinum coatings of varying thicknesses on wire samples and establishing the optimum coating thickness--in terms of minimum resistivity changes with temperature. Finally, the moisture-proofing effectiveness of barrier coatings subjected to elevated temperatures was studied, and one commercial barrier coating (BLH Barrier H Waterproofing) was evaluated.

Lemcoe, M. M.↗
NASA NTRS1973

A north-south stationkeeping ion thruster system for ATS-F

A one millipound cesium ion thruster system experiment designed for the ATS-F satellite will be used to demonstrate north-south stationkeeping for synchronous satellites. Development effort leading to the present design will be described and test data for qualification and flight acceptance tests will be presented. These include a review of EMI evaluations tests made with the power conditioning subsystem and the thruster simulator, and an extended system operational test. During the extended test, 90 on-off cycles simulated thruster operation in orbit. A planned 18,000 hour ground test of a flight qualified thruster will be discussed.

James, E.↗
NASA NTRS1973

Evaluation of load-life relation with ball bearings at 500 deg F

A survey of the literature suggests that a stress-life exponent of approximately 12 is typical of vacuum-processed steels for ball bearings rather than the exponent of 9 which has been generally accepted by the bearing industry and bearing users. Tests run with vacuum-degassed AISI 52100 balls in the five-ball fatigue tester at four maximum Hertz stress levels in the range from 650000 to 875000 psi showed good agreement with the literature. However, tests run with consumable-electrode vacuum melted AISI M-50 steel angular-contact ball bearings at 500 deg F at three thrust loads did not show significant deviation from the accepted ninth power stress-life relation.

Parker, R. J.↗
NASA NTRS1974

A digital fly-by-wire technology development program using an F-8C test aircraft

A digital fly-by-wire flight control system has been installed in an F-8C test airplane and has undergone extensive ground and flight testing as part of an overall program to develop digital fly-by-wire technology. This is the first airplane to fly with a digital fly-by-wire system as its primary means of control and with no mechanical reversion capability. Forty-two test flights were made for a total flight time of 57 hours. Six pilots participated in the evaluation. This paper presents an overview of the digital fly-by-wire program and discusses some of the flight-test results.

Jarvis, C. R.↗
NASA NTRS1974

A comment on plasma 'pile-up' in the F-region

At ionospheric heights, the geomagnetic field is virtually incompressible. In consequence, an electromagnetic drift can only compress the F-region plasma by moving it in a direction in which the field becomes stronger. This paper examines the rate of compression at mid-latitudes for three different assumptions about the ion motion.

Rishbeth, H.↗
NASA NTRS1974

In situ measurements of the spectral characteristics of F region ionospheric irregularities

The retarding potential analyzer aboard Ogo 6 has provided high-resolution observations of the ion concentration along the satellite path. Changes in ion concentration as small as 0.03% and at times as small as 0.01% could be measured. Spatial resolution varied from 35 to 380 m. Samples of data have been analyzed to determine the spectral properties of the F region irregularities observed. The most common frequency spectrum observed suggests that the responsible irregularities result from the turbulent dissipation of larger irregularities. At the equator, the larger irregularities are probably produced by convective electric fields. At high latitudes, electric fields may also be involved, but other factors such as precipitating particles may contribute to, or be primarily responsible for, the production of large irregularities. Examples of other types of spectra associated with wavelike irregularities and with 'ground glass' (high-frequency noise) irregularities are also shown.

Dyson, P. L.↗
NASA NTRS1973

Pioneer F and G spacecraft

Two spacecraft, Pioneers F and G, each with a launch weight of approximately 256 kg, were launched in March 1972 and April 1973 on trajectories which will result in close Jupiter encounters in late 1973 and 1974, respectively. The Pioneer mission objectives are to investigate the interplanetary medium beyond Mars, to determine the nature of the asteroid belt, and to explore Jupiter and its environment. A review is given of the system and subsystem design with emphasis on the simplicity of design, the selective use of redundancy for reliability enhancement, and the environmental protection provided.

Obrien, B. J.↗
NASA NTRS1974

NASA Flight Research Center scale F-15 remotely piloted research vehicle program

The NASA Flight Research Center undertook a remotely piloted research vehicle (RPRV) program with a 3/8-scale model of an F-15 aircraft to determine the usefulness of the RPRV testing technique in high-risk flight testing such as spin testing. The results of the first flights of the program are presented. The program has shown that the RPRV technique, including the use of a digital control system, is a viable method for obtaining flight research data. Also presented are some negative aspects that have been learned about the RPRV technique in terms of model size, command frequency, and launch technique.

Layton, G. P.↗
NASA NTRS1974

Extraction from flight data of lateral aerodynamic coefficients for F-8 aircraft with supercritical wing

A parameter-extraction algorithm was used to determine the lateral aerodynamic derivatives from flight data for the F-8 aircraft with supercritical wing. The flight data used were the recorded responses to aileron or rudder pulses for Mach numbers of 0.80, 0.90, and 0.98. Results of this study showed that a set of derivatives were determined which yielded a calculated aircraft response almost identical with the response measured in flight. Derivatives extracted from motion resulting from rudder inputs were somewhat different from those resulting from aileron inputs. It was found that the derivatives obtained from the rudder-input data were highly correlated in some instances. Those from the aileron input had very low correlations and appeared to be the more reliable.

Williams, J. L.↗