Abstract
According to the mechanical structure and the load characteristics of a fighter airplane main undercarriage, the arrangement of the measuring strain gages and the type of the strain gage bridges were decided. Considering the variation of application of the loads and the influence of the landing gear compression stroke, an influence factor of landing gear compression stroke was defined and introduced in the calibration equation as a parameter. The equation between the load imput and the strain gage output was established on a test bench by aid of the multi-variable regression and optimization method. The measured load spectrum of the main undercarriage was derived by means of the calibration equation, providing an important reference for estimating and enhancing the fatigue life and conducting the reliability-based design.
| Original language | English |
|---|---|
| Pages (from-to) | 1025-1028 |
| Number of pages | 4 |
| Journal | Jilin Daxue Xuebao (Gongxueban)/Journal of Jilin University (Engineering and Technology Edition) |
| Volume | 36 |
| Issue number | 6 |
| State | Published - Nov 2006 |
| Externally published | Yes |
Keywords
- Airplane
- Calibration equation
- Engineering mechanics
- Load spectrum
- Main undercarriage
- Strain gage
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