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NORTH AMERICAN ROCKWELL CORP LOS ANGELES CALIF LOS ANGELES DIV

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Works: 47 works in 50 publications in 1 language and 50 library holdings
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Publications about NORTH AMERICAN ROCKWELL CORP LOS ANGELES CALIF LOS ANGELES DIV
Publications by NORTH AMERICAN ROCKWELL CORP LOS ANGELES CALIF LOS ANGELES DIV
Most widely held works by NORTH AMERICAN ROCKWELL CORP LOS ANGELES CALIF LOS ANGELES DIV
Boron-Epoxy Wing Skins F-100D Aircraft Structural Design and Analysis ( Book )
3 editions published in 1971 in English and held by 3 libraries worldwide
This document constitutes the final report on the structural analysis and design of boron-epoxy wing skins. The design and fabrication of boron composite laminate skins to replace the upper and lower structural covers of the F-100D wing. This report presents the final design of these boron-epoxy wing skins and the material properties and structural analysis. (P.S.-PL)
Fatigue Test and Analysis of the F-100 Landing Gear. Appendix D ( Book )
2 editions published in 1969 in English and held by 2 libraries worldwide
Diffusion bonding --a process for manufacture of titanium aerospace structural components by J Melill( Book )
1 edition published in 1969 in English and held by 1 library worldwide
Fracture toughness testing for qualification and verification of metallic materials ( Book )
1 edition published in 1971 in English and held by 1 library worldwide
Fatigue Test and Analysis of the F-100 Landing Gear. Volume III ( Book )
1 edition published in 1969 in English and held by 1 library worldwide
The F-100 Aircraft Structural Integrity Program was designed to fatigue test the basic wing, fuselage and empennage structure of the air vehicle. In conjunction with these tests, actual nose and main gears were used as loading jigs to introduce ground loads into the structure. Consequently, the major portion of the test effort on the landing gear was completed on that program. The incomplete testing of the nose gear was concluded on the F-100 Landing Gear Fatigue Test Program. The results of the gear tests conducted on both programs are presented in this section of the report
In-Place Tube Welding Manufacturing Technology ( Book )
1 edition published in 1971 in English and held by 1 library worldwide
A welding system, comprising a weld tool and a programer control unit, was designed, fabricated, and tested. The system is capable of producing consistent aircraft quality butt welds in 1/2-inch diameter by 0.035-inch wall and 1-inch diameter by 0.070-inch wall 6Al-4V titanium alloy tubing. Test specimens in these tube sizes have been welded and tested in flexure fatigue, impulse cycled and ultimate burst pressure tested at 500F. The test results indicate this tube joining technique to be equal or superior to any other method available for service conditions of 4,000 psi working pressure and 500F temperature. (Author)
SAMPE EXPO 70 ( Book )
1 edition published in 1970 in English and held by 1 library worldwide
DISLOCATION DYNAMICS IN ALPHA TITANIUM ( Book )
1 edition published in 1969 in English and held by 1 library worldwide
Dislocation motion measurement in commercially pure alpha titanium (A-55) were performed at a plastic strain of 2 x 10-3 in the temperature range 300K-500K employing a stress relaxation technique. (Author)
Relaxation Processes in Metastable Beta Titanium Alloys ( Book )
1 edition published in 1971 in English and held by 1 library worldwide
Extensive observations have been made on an internal friction peak in a series of metastable beta Ti-Mo and -V alloys. The peak was observed at two frequencies (10 to the 4th c/s and 10 to the 7th c/s) in temperature ranges of 120K to 140K and 153K to 210+K respectively depending on alloy compositions as well as frequency. In both alloy systems, the peak strength passed through a maximum with increasing alloy content at or near the upper compositional bound for athermal omega formation. In both alloy systems, the peak persisted at compositions well above the upper compositional bound for athermal omega formation although it was greatly diminished in height. The peak's strength was severely reduced by annealing in the thermal omega precipitation temperature range. The results of the work will be compared to the properties of a similar internal friction peak reported earlier in Zr base alloys. (Author)
Fatigue Test and Analysis of the F-100 Landing Gear. Volume I ( Book )
1 edition published in 1969 in English and held by 1 library worldwide
A static strength analysis is performed using revised and up-dated ground loads for the new F-100 landing gear, as redesigned under the direction of OOAMA, Hill Air Force Base, Ogden, Utah. No zero or negative margins of safety are found. The fatigue life of the redesigned portions of the gear is found to meet the requirement of 7,000 hours of trouble free service upon the basis of the results of full scale fatigue tests. A computer program using Miner's Rule is used to predict the laboratory fatigue failures which did occur as well as to predict a service life for sections not having a laboratory failure history. Strain gages and photostress were used to obtain experimental stress concentration factors
Peierls:nabarro hardening in the presence of point obstacles ( Book )
1 edition published in 1969 in English and held by 1 library worldwide
The report discusses a mechanism for the work hardening phenomena occurring in iron base alloys
Nuclear Effects Analysis D1-S-1800 Aerial Radiac System AN/ADR-6(XE-4) (V) ( Book )
1 edition published in 1972 in English and held by 1 library worldwide
This preliminary report summarizes the analysis effort performed to date on the Aerial Radiac System (ARS) to assure proper ARS operation following exposure to nuclear radiation. To facilitate the analysis effort, the ARS has been subdivided into several subcircuits. Each subcircuit will be analyzed and/or tested to assure proper performance following exposure to radiation at specification level. The ARS is used to measure ground dose radiation level (Rads/hr). The Power Supplies convert aircraft 28 volts dc to regulated +15 and -15 volts dc and -1000 volts dc. Gamma dose rate is measured by the Photomultiplier Tube and converted to a voltage level by a log amplifier. This voltage when scaled by EMAX in the subtractor circuit becomes the air dose level. The Ground Dose Computer provides the ground dose level by combining a signal proportional to the altitude as furnished by a radar altimeter with the air dose level signal. The ground dose level signal is displayed, recorded and/or can be telemetered. A self test feature is also provided
Propulsion System Flow Stability Program (Dynamic). Part XI. Lift Engine Compressor Tests and Response to Steady-State Distortion ( Book )
1 edition published in 1968 in English and held by 1 library worldwide
A four-stage lift engine type compressor was tested over its complete operating range with and without combined circumferential and radial distortion of inlet total pressure. The compressor rig was equipped with interstage instrumentation at each rotor exit and the test procedure was such that a circumferential and radial survey of interstage data were obtained at each test point. Analysis of the data showed that interstage flow mixing and distortion attenuation was related to the slope of the characteristics of the individual stages. Detailed observations of the interstage data are presented which provide considerable insight into distorted compressor operation. A simple analytical procedure to describe compressor events is proposed. Recommendations are made for additional analytical and empirical investigations to corroborate the analysis and conclusions. (Author)
Propulsion System Flow Stability Program (Dynamic). Part XIV. Propulsion System Stability Margin Performance Penalties for an RA-5C Aircraft ( Book )
1 edition published in 1968 in English and held by 1 library worldwide
Steady state propulsion system and aircraft performance penalties due to control margins required for transient operation were studied for the RA-5C aircraft/J79 engine configuration. Significant performance gains were made when these margins could be reduced and a smaller turbine used. (Author)
Analysis of Relaxed Static Stability and Maneuver Load Control Applications to a Large Bomber ( Book )
1 edition published in 1972 in English and held by 1 library worldwide
Application of two control configured vehicle concepts, relaxed static stability and maneuver load control, is made using a large bomber as the test configuration. The objectives are to obtain vehicle weight reduction and/or performance benefits resulting from the relaxation of normal vehicle design constraints made possible by application of control techniques. In the longitudinal axis, both static stability margins and horizontal tail size reductions are examined. In the directional axis, vertical tail size reductions are assessed. Acceptability criteria are based on MIL-F-8785B flying qualities requirements and both maneuver and upset conditions. The maneuver load control study aims to reduce wing weight by reducing wing bending moment during discrete load conditions. Wing lift distribution is modified by deflection of wing mounted control devices such that the wing center of pressure moves inboard. (Author)
A Study of Dislocation: Hydrogen Interaction in Titanium Aluminum Alloys via Internal Friction Measurements ( Book )
1 edition published in 1972 in English and held by 1 library worldwide
Hydrogen-dislocation interactions in alpha titanium-aluminum alloys were studied via internal friction measurements in the temperature range 200K to 500K. Employing a series of titanium-aluminum binary alloys (0 %, 1 at. % and 3 at. %Al) these interactions were monitored in terms of observation of a damping peak which centers around 390 K at 10 MHz. The activation energy and attempt frequency of the damping peak in pure titanium were found to be 0.28 eV and 4x10 to the 10th power/sec, respectively. Both room temperature plastic deformation and the presence of hydrogen are required to generate this peak. The relaxation strength of the peak in each of the alloys increases at this peak. The relaxation strength of the peak in each of the alloys increases at low hydrogen levels with the square of hydrogen concentration and reaches a plateau when a critical hydrogen concentration is attained. (Author)
Supersonic unsteady aerodynamics for wings with trailing edge control surfaces and folded tips ( Book )
1 edition published in 1968 in English and held by 1 library worldwide
A Mach box digital computer program, MBOX, has been developed and written for surfaces with trailing edge control surfaces. It is a very versatile and reliable method for obtaining steady and unsteady supersonic aerodynamic coefficients that may be used in response and flutter analyses of rather general lifting surfaces. Wing configurations can include those with folded tips, cranked leading and trailing edges, and supersonic or subsonic leading and trailing edges. At the option of the user, MBOX will also calculate steady or unsteady lifting pressure distributions, and if the generalized mass and stiffness matrices are provided, it will obtain solutions of flutter equations in one computer run. (Author)
Microstructures and Mechanical Properties of Thermomechanically Treated High Strength Beta-Titanium ( Book )
1 edition published in 1972 in English and held by 1 library worldwide
Solution treated and water quenched beta titanium alloys, Beta-III (11.5Mo, 6 Zr, 4.5 SN) and a binary Ti-18% Mo alloy, were thermomechanically processed and their tensile properties determined as a function of prior treatment. Correlations of strength to internal structure were made utilizing thin film electron microscopy. (Author)
Life Support Systems Requirements. Volume I. Section I. System Analysis ( Book )
1 edition published in 1970 in English and held by 1 library worldwide
The volume includes the system engineering analysis as applied to the development of life support system requirements. This effort was directed at operationally defining basic analytic objectives through the identification of fundemental system constraints and developing appropriate methodologies for the derivation, documentation, and implementation of basic life support requirements. The analyses presented translate basic system requirements into detail life support system functional requirements for air vehicle/mission and support operations. (Author)
 
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