In this investigation it was found that the instability failure of curved sheet is nearly independent of the type of loading and is primarily a function of the maximum stress, radius-thickness ration and modulus of elasticity. A method of correlating the critical stress of thin sheet under several different types of loading is given. An explanation for the experimental critical stress of thin walled cylinders under bending being greater than that for pure compression is given. The strength of unstiffened thin walled circular nose sections under pure bending was found to be controlled by local instability of the section, rather than a large scale instability. The equation of local instability of curved sheet gives values which are in fair agreement with those found experimentally.
The strength of elliptical cylinders supported at the minor axis under bending plus shear loads is governed primarily by the bending strength, and is little effected by the sheer force unless the amount of shear is quite large with respect to the moment. The effect of increasing the amount of elliptically greatly reduces the bending and shear strength of nose sections. Under torsional loads the stress at buckling falls off as the ration of the major to minor axis increases but the failure stress decreases at a slower rate than the buckling stress. The length effect of semi-circular sections under torsion is similar to that of a circular tube, and can be obtained by Donnell’s theoretical equation.
}, address = {1200 East California Boulevard, Pasadena, California 91125}, advisor = {Von Karman, Theodore}, } @mastersthesis{10.7907/CVB4-7510, author = {Young, Bradley Hobart}, title = {A Two-Parameter Wind Tunnel Rigging System}, school = {California Institute of Technology}, year = {1937}, doi = {10.7907/CVB4-7510}, url = {https://resolver.caltech.edu/CaltechETD:etd-03242005-100937}, abstract = {
In January of 1935, definite steps were taken in a two part program to modernize the ten-foot wind tunnel of the Guggenheim Aeronautical Laboratory at the California Institute of Technology. Part one of the program was the design and construction of a new wind tunnel rigging system based on concepts originally laid down by Dr. A. L. Klein, Associate Professor at the same institution. Part two of the program, to be carried on intensively immediately after completion of part one, will be the development of an entirely new force measuring system to replace the present modified steelyard type balances.
In this paper the general problem of wind tunnel testing and equipment will be briefly outlined with the bulk of the discussion then given over to the problems concerning the evolution and design of a specific wind tunnel rigging system. As the system is not yet complete in its final form obviously there can be no description of the project as a finished piece of work. Also, it has been thought inadvisable to present only the system as it exists at present, therefore all the various features or principles that have been considered will be discussed and reason for their discard or adoption made clear. The result should then be a guide or at least an aid to the completion of part one of the modernizing program
In a latter section of the paper some of the desired features of the contemplated force measuring system will be set down in the hope that they may be a skeletal set of requirements for the second part of the modernizing program.
}, address = {1200 East California Boulevard, Pasadena, California 91125}, advisor = {Klein, Arthur Louis}, } @mastersthesis{10.7907/R62Z-6P10, author = {Smith, Joe Nelson and Murphy, Joseph Nathaniel}, title = {Investigation of Extended Bulb Angle Sections Under Compression: Part One: as Euler Columns ; Part Two: As Stiffeners Attached to Sheet}, school = {California Institute of Technology}, year = {1937}, doi = {10.7907/R62Z-6P10}, url = {https://resolver.caltech.edu/CaltechETD:etd-04252008-093950}, abstract = {
No abstract.
}, address = {1200 East California Boulevard, Pasadena, California 91125}, advisor = {von Kármán, Theodore and Klein, Arthur Louis and Sechler, Ernest Edwin}, } @mastersthesis{10.7907/K872-W635, author = {Allardt, Frederick Hamilton}, title = {The Brinelling of Small Ball Bearings}, school = {California Institute of Technology}, year = {1937}, doi = {10.7907/K872-W635}, url = {https://resolver.caltech.edu/CaltechETD:etd-10132005-103946}, abstract = {The brinelling of ball bearings is a subject which has had comparatively little study. Since ball bearings have found most of their applications in such things as rotating shafts, there has been little reason to study their action under static loading conditions. This research was suggested by the Fafnir Ball Bearing Company because of the increasing use of ball bearings for static loads in aircraft. In the aircraft business, the designers, because of strict weight requirements, have used ball bearings up to their rated loads. Not infrequently these bearings brinelled. (A brinelled bearing is one in which a dent has been formed in one of the races by a ball). It is therefore evident that more should be known about the brinelling of bearings.}, address = {1200 East California Boulevard, Pasadena, California 91125}, advisor = {Klein, Arthur Louis and Sechler, Ernest Edwin}, } @mastersthesis{10.7907/MWT3-P557, author = {Magden, John Leslie}, title = {A Preliminary Investigation of Rivets and Riveted Joints in Metal Airplane Construction}, school = {California Institute of Technology}, year = {1934}, doi = {10.7907/MWT3-P557}, url = {https://resolver.caltech.edu/CaltechETD:etd-07172007-081411}, abstract = {No abstract.}, address = {1200 East California Boulevard, Pasadena, California 91125}, advisor = {Klein, Arthur Louis and Sechler, Ernest Edwin}, } @mastersthesis{10.7907/5P3S-7022, author = {Rassieur, William Theodore}, title = {Hinge Moments}, school = {California Institute of Technology}, year = {1934}, doi = {10.7907/5P3S-7022}, url = {https://resolver.caltech.edu/CaltechETD:etd-04152008-090606}, abstract = {The matter herein presented represents the results of an investigation on hinge moments of ailerons on a 1/12.5 scale model of a main wing airfoil of the XP3D-l Navy Patrol Boat.
The data obtained were then employed in the calculation of stick forces due to aileron moments on the full scale airplane, the calculations covering a flying range of eighty to one hundred eighty miles per hour.
}, address = {1200 East California Boulevard, Pasadena, California 91125}, advisor = {von Kármán, Theodore and Klein, Arthur Louis}, }