A full-scale aircraft structural test restraint system

Abstract

The invention provides a restraint system for a full-scale aircraft structure test, which is characterized in that it comprises a restraint beam (2), a top connection device (3), a support lever (4), an upward restraint device (5), an upward restraint sensor (6 ), the downward restraint device (7), the downward restraint sensor (8) and the ground fixing device (9), the restraint beam (2) located above is suspended and connected with the support lever (4) through the top connecting device (3); One end of the support lever (4) is connected to the ground fixing device (9) through the upward restraint device (5) with adjustable stroke, and the other end is connected to the upper end of the landing gear dummy wheel (1) through the upward restraint force sensor (6), forming a vertical Upward restraint; the lower end of the dummy wheel (1) of the landing gear is connected with the ground fixing device (9) through the downward restraint force sensor (8) and the downward restraint device (7) with adjustable stroke in turn, forming a vertical downward restraint.

Description

technical field [0001] The invention belongs to the aircraft ground strength test technology, and relates to a full-scale aircraft structure test restraint system. Background technique [0002] In the static / fatigue test of the full-scale aircraft structure, the vertical three-point restraint is generally realized through the front landing gear, left and right main landing gear, and two lateral restraints and one directional restraint or one lateral restraint are supplemented at the landing gear. Two course constraints are constrained to meet the requirements of statically indeterminate constraints for the whole machine. Among them, the vertical restraint of the landing gear is usually achieved by lifting the dummy wheel through the column-crowbar device and using the connecting piece to ground the dummy wheel, such as figure 1 . [0003] During the test, the landing gear will produce lateral or directional deformation when subjected to passive loads, and correspondingly g...

AI Technical Summary

Problems solved by technology

For the aircraft with less rigidity in the connection area between the landing gear and the fuselage, the deformation of the landing gear is relatively large. figure 1 Due to the small distance between the connection point of the dummy wheel of the landing gear and the connection point of the lever end, the additional constraints have a significant impact, and the whole machine is in a statically indefinite constraint state, which affects the accuracy of the test results

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