Effect of Variables in Welding Technique on the Strength of Direct-current Metal-arc-welded Joint s in Aircraft Steel II : Repeated-stress Tests of Joint s in SAE 4130 Seamless Steel Tubing
Document ID: 19930081881NTRS Full-Text: Click to View [PDF Size: 37.3 MB]
Author: Voldrich, C B; ARMSTRONG E T
Abstract: No Abstract Available
Publication Year: 1948Report/Patent Number: NACA-TN-1262Date Acquired: Sep 01, 1996
Strength of Welded Aircraft Joint s
Document ID: 19930091659NTRS Full-Text: Click to View [PDF Size: 30.6 MB]
Author: Brueggeman, W C
Abstract: This investigation is a continuation of work started in 1928 and described in NACA-TR-348 which
shows that the insertion of gusset plates was the most satisfactory way of strengthening a joint . Additional tests of the present series show that joint s of this type could be improved by cutting out the portion of the plate between the intersecting tubes. T and lattice joint s in thin-walled tubing 1 1/2 by 0.020 inch have somewhat lower strengths than joint s in tubing of greater wall thickness because of failure by local buckling. In welding the thin-walled tubing , the recently developed "carburizing flux" process was found to be the only method capable of producing joint s free from cracks. The "magnetic powder" inspection was used to detect cracks in the joint s and flaws in the tubing .
Publication Year: 1937Report/Patent Number: NACA-TR-584Date Acquired: Sep 01, 1996
Weldability of High-tensile Steel s from Experience in Airplane Construction, with Special Reference to Welding Crack Susceptibility
Document ID: 19930094638NTRS Full-Text: Click to View [PDF Size: 16.9 MB]
Author: Muller, J
Abstract: The concept of welding crack tendency is explained and illustrated with practical examples. All
pertinent causes are enumerated, and experimental measures are given through which the secondary effects can be removed and the principal causes analyzed: 1) welding stresses; and 2) material defects. The variations in length and stresses incident to welding a small bar as free weld, with restrained elongation and restrained elongation and contraction, are explored in three fundamental experiments.
Publication Year: 1935Report/Patent Number: NACA-TM-779Date Acquired: Jan 06, 1997
Strength of Welded Joint s in Tubular Members for Aircraft
Document ID: 19930091420NTRS Full-Text: Click to View [PDF Size: 34.4 MB]
Author: Whittemore, H L; Brueggeman, W C
Abstract: The object of this investigation is to make available to the aircraft industry authoritative
information on the strength, weight, and cost of a number of types of welded joint s. This information will, also, assist the aeronautics branch in its work of licensing planes by providing data from which the strength of a given joint may be estimated. As very little material on the strength of aircraft welds has been published, it is believed that such tests made by a disinterested governmental laboratory should be of considerable value to the aircraft industry. Forty joint s were welded under procedure specifications and tested to determine their strengths. The weight and time required to fabricate were also measured for each joint .
Publication Year: 1931Report/Patent Number: NACA-TR-348Date Acquired: Sep 01, 1996
The Bristol "Bulldog" (British): A Single-Seat All-Steel Fighter
Document ID: 19930090373NTRS Full-Text: Click to View [PDF Size: 1.4 MB]
Abstract: No Abstract Available
Publication Year: 1929Report/Patent Number: NACA-AC-103Date Acquired: Sep 01, 1996
Welding of high chromium steel s
Document ID: 19930081018NTRS Full-Text: Click to View [PDF Size: 584 KB]
Author: Miller, W B
Abstract: A brief description is given of different groups of high chromium
steel s (rustless iron and
stainless steel s) according to their composition and more generally accepted names. The welding procedure for a given group will be much the same regardless of the slight variations in chemical composition which may exist within a certain group. Information is given for the tensile properties (yield point and ultimate strength) of metal sheets and welds before and after annealing on coupons one and one-half inches wide. Since welds in rustless iron containing 16 to 18 percent chromium and 7 to 12 percent nickel show the best combination of strength and ductility in the 'as welded ' or annealed condition, it is considered the best alloy to use for welded construction.
Publication Year: 1928Report/Patent Number: NACA-TN-290Date Acquired: Sep 01, 1996
Tensile Strength of Welded Steel Tubes : First Series of Experiments
Document ID: 19930090755NTRS Full-Text: Click to View [PDF Size: 11.6 MB]
Author: Rechtlich, A
Abstract: The purpose of the experiments was to determine the difference in the strength of
steel tubes
welded
by different methods, as compared with one another and also with unwelded , unannealed tubes, including; moreover, a comparison of the results obtained by experienced and inexperienced welders.
Publication Year: 1928Report/Patent Number: NACA-TM-445Date Acquired: Sep 01, 1996
Accelerations and Passenger Harness Loads Measured in Full-Scale Light-Airplane Crashes
Document ID: 19930083730NTRS Full-Text: Click to View [PDF Size: 34.3 MB]
Author: Eiband, A. Martin; Simpkinson, Scott H.; Black, Dugald O.
Abstract: Full-scale light-airplane crashes simulating stall-spin accidents were conducted to determine the
decelerations to which occupants are exposed and the resulting harness forces encountered in this type of accident. Crashes at impact speeds from 42 to 60 miles per hour were studied. The airplanes used were of the familiar steel -tube, fabric-covered, tandem, two-seat type. In crashes up to an impact speed of 60 miles per hour, crumpling of the forward fuselage structure prevented the maximum deceleration at the rear-seat location from exceeding 26 to 33g. This maximum g value appeared independent of the impact speed. Restraining forces in the seatbelt - shoulder-harness combination reached 5800 pounds. The rear-seat occupant can survive crashes of the type studied at impact speeds up to 60 miles per hour, if body movement is restrained by an adequate seatbelt-shoulder-harness combination so as to prevent injurious contact with obstacles normally present in the cabin. Inwardly collapsing cabin structure, however, is a potential hazard in the higher-speed crashes.
Publication Year: 1953Document Type: Technical ReportReport/Patent Number: NACA-TN-2991Date Acquired: Sep 01, 1996
Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine. 7: Rotor-Blade Fabrication Procedures
Document ID: 19730065472NTRS Full-Text: Click to View [PDF Size: 7.2 MB]
Author: Long, Roger A.; Esgar, Jack B.
Abstract: An experimental investigation was conducted to determine the cooling effectiveness of a wide variety
of air-cooled turbine-blade configurations. The blades, which were tested in the turbine of a - commercial turbojet engine that was modified for this investigation by replacing two of the original blades with air-cooled blades located diametrically opposite each other, are untwisted, have no aerodynamic taper, and have essentially the same external profile. The cooling-passage configuration is different for each blade, however. The fabrication procedures were varied and often unique. The blades were fabricated using methods most suitable for obtaining a small number of blades for use in the cooling investigations and therefore not all the fabrication procedures would be directly applicable to production processes, although some of the ideas and steps might be useful. Blade shells were obtained by both casting and forming. The cast shells were either welded to the blade base or cast integrally with the base. The formed shells were attached to the base by a brazing and two welding methods. Additional surface area was supplied in the coolant passages by the addition of fins or tubes that were S-brazed. to the shell. A number of blades with special leading- and trailing-edge designs that provided added cooling to these areas were fabricated. The cooling effectiveness and purposes of the various blade configurations are discussed briefly.
Publication Year: 1951Document Type: Technical ReportReport/Patent Number: NACA-RM-E51E23, REPT-2203Date Acquired: Dec 12, 1995
Column strength of tubes elastically restrained against rotation at the ends
Document ID: 19930091702NTRS Full-Text: Click to View [PDF Size: 2.9 MB]
Author: Osgood, William R
Abstract: Report presents the results of a study made of the effects of known end restraint on commercially
available round and streamline tubing of chromium-molybdenum steel , duralumin, stainless steel , and heat-treated chromium-molybdenum steel ; and a more accurate method than any previously available, but still a practical method, was developed for designing compression members in riveted or welded structures, particularly aircraft. Two hundred specimens were tested as short, medium-length, and long columns with freely supported ends or elastically restrained ends. Tensile and compressive tests were made on each piece of original tubing from which column specimens were cut.
Publication Year: 1938Report/Patent Number: NACA-TR-615Date Acquired: Sep 01, 1996
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