Survey and Evaluation of Sonic Fatigue Testing Facilities
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Report Number: ASD TR 61-185
Author(s): Bianchi, Ralph A., Bradshaw, Ronald T., Farrell, James H., Reed, F. Everett
Corporate Author(s): CONESCO Consultants in Engineering Science
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1962-03
Pages: 364
Contract: AF 33(616)-7003
DoD Project: 1370
DoD Task: 13963
Identifier: AD0277124
AD Number: AD277124
Abstract:
A survey and evaluation of the sonic fatigue testing facilities throughout the country has been made to establish present methods and techniques of testing and to determine the necessity of performing other environmental tests in combination with high intensity noise.Fifteen facilities were visited and detailed descriptions of these facilities are presented. The facilities are considered in terms of their functions as design, proof testing, and research tools, and such things as sound sources, the theoretical background of sonic fatigue work, test methods and specimen arrangements, instrumentation and data acquisition, time and costs, and combined environments are discussed and evaluated. In addition, what are considered the most feasible design and proof testing procedures, within the framework of present theory and equipment, are presented. A few of the general conclusions are that: 1. The most economical procedure for developing sonic fatigue resistant structures consists of the general steps: (a) Design panels with discrete frequency siren methods (b) Perform semi-qualification tests with broad band sources such as broad band sirens or modulated air flaw speakers (not jet engines). (c) Perform a full scale proof test. 2. The effects of temperature and pressure (and perhaps corrosion) can only be assessed by combined tests.3 Combined tests for nuclear radiation should not be considered in the foreseeable future.4. In many instances the effects of correlation can be approximated in a discrete frequency siren test by orienting a specimen in a manner determined by consideration of the sound level contours existing on the aircraft.
Provenance: Bombardier/Aero
Author(s): Bianchi, Ralph A., Bradshaw, Ronald T., Farrell, James H., Reed, F. Everett
Corporate Author(s): CONESCO Consultants in Engineering Science
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1962-03
Pages: 364
Contract: AF 33(616)-7003
DoD Project: 1370
DoD Task: 13963
Identifier: AD0277124
AD Number: AD277124
Abstract:
A survey and evaluation of the sonic fatigue testing facilities throughout the country has been made to establish present methods and techniques of testing and to determine the necessity of performing other environmental tests in combination with high intensity noise.Fifteen facilities were visited and detailed descriptions of these facilities are presented. The facilities are considered in terms of their functions as design, proof testing, and research tools, and such things as sound sources, the theoretical background of sonic fatigue work, test methods and specimen arrangements, instrumentation and data acquisition, time and costs, and combined environments are discussed and evaluated. In addition, what are considered the most feasible design and proof testing procedures, within the framework of present theory and equipment, are presented. A few of the general conclusions are that: 1. The most economical procedure for developing sonic fatigue resistant structures consists of the general steps: (a) Design panels with discrete frequency siren methods (b) Perform semi-qualification tests with broad band sources such as broad band sirens or modulated air flaw speakers (not jet engines). (c) Perform a full scale proof test. 2. The effects of temperature and pressure (and perhaps corrosion) can only be assessed by combined tests.3 Combined tests for nuclear radiation should not be considered in the foreseeable future.4. In many instances the effects of correlation can be approximated in a discrete frequency siren test by orienting a specimen in a manner determined by consideration of the sound level contours existing on the aircraft.
Provenance: Bombardier/Aero