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Strain gage load calibration of the wing interface fittings for the adaptive compliant trailing edge flap flight test
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Miller, Eric J. Holguin, Andrew C. Lokos, William A. Cruz, Josue |
| Copyright Year | 2014 |
| Description | The safety-of-flight parameters for the Adaptive Compliant Trailing Edge (ACTE) flap experiment require that flap-to-wing interface loads be sensed and monitored in real time to ensure that the structural load limits of the wing are not exceeded. This paper discusses the strain gage load calibration testing and load equation derivation methodology for the ACTE interface fittings. Both the left and right wing flap interfaces were monitored; each contained four uniquely designed and instrumented flap interface fittings. The interface hardware design and instrumentation layout are discussed. Twenty-one applied test load cases were developed using the predicted in-flight loads. Pre-test predictions of strain gage responses were produced using finite element method models of the interface fittings. Predicted and measured test strains are presented. A load testing rig and three hydraulic jacks were used to apply combinations of shear, bending, and axial loads to the interface fittings. Hardware deflections under load were measured using photogrammetry and transducers. Due to deflections in the interface fitting hardware and test rig, finite element model techniques were used to calculate the reaction loads throughout the applied load range, taking into account the elastically-deformed geometry. The primary load equations were selected based on multiple calibration metrics. An independent set of validation cases was used to validate each derived equation. The 2-sigma residual errors for the shear loads were less than eight percent of the full-scale calibration load; the 2-sigma residual errors for the bending moment loads were less than three percent of the full-scale calibration load. The derived load equations for shear, bending, and axial loads are presented, with the calculated errors for both the calibration cases and the independent validation load cases. |
| File Size | 1120797 |
| Page Count | 24 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20140003965 |
| Archival Resource Key | ark:/13960/t38103d40 |
| Language | English |
| Publisher Date | 2014-01-13 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Design, Testing And Performance Flight Tests Calibrating Strain Gages Regression Analysis Axial Strain Load Tests Finite Element Method Fittings Wings Bending Trailing Edge Flaps Wing Loading Loads Forces Shear Strain Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
