Temperature Compensation of High-Temperature Strain Gages

    Published: Jan 1958

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    Recent investigations on the thermal behavior of aircraft structures undertaken for the Wright Air Development Center by Allied Research Associates, Inc., included a series of laboratory tests on the Baldwin-Lima-Hamilton Nichrome V foil high-temperature strain gage, type HFN-3. The test results indicated that biaxial strain conditions make it impractical, for high-intensity transient thermal loading of aircraft structures, to attempt compensation for the effects of temperature on strain gage readings by the use of a temperature-compensating dummy gage. Therefore, a temperature-compensation calibration curve was prepared for the Nichrome V foil gage. For this purpose, thermal strain data were compiled with this gage bonded to a free aluminum plate. Temperature-compensated data taken from similar gages mounted on a simple cantilever aluminum strip subjected to combined mechanical and thermal inputs were then compared with the strain measurements obtained by the free-plate method with favorable results. Sufficient data were obtained to permit the construction of a calibration curve for application of this gage bonded to other metals as well. The results of these tests are presented graphically accompanied by a brief description of the experimental procedure.

    Author Information:

    Gray, Edward I.
    Project Engineer, Allied Research Associates, Inc., Boston, Mass.

    Grossman, Arthur
    Research Engineer, Allied Research Associates, Inc., Boston, Mass.

    Rubin, Melvin R.
    Staff Engineer, Allied Research Associates, Inc., Boston, Mass.

    Committee/Subcommittee: E28.14

    DOI: 10.1520/STP45031S

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