Full-size airplane structure test restraint system

Abstract

The invention provides a full-size airplane structure test restraint system. The full-size airplane structure test restraint system is characterized by comprising a restrained beam (2), a top end connecting device (3), a supporting lever (4), an upward restraint device (5), an upward restraint sensor (6), a downward restraint device (7), a downward restraint sensor (8) and ground fixing devices (9); the restrained beam (2) located at the upper portion is in hanging connection with the supporting lever (4) through the top end connecting device (3); one end of the supporting lever (4) is connected with one ground fixing device (9) through the stroke-adjustable upward restraint device (5), the other end of the supporting lever (4) is connected with the upper end of an undercarriage fake wheel (1) through the upward restraint sensor (6), and the vertical upward restraint situation is formed; and the lower end of the undercarriage fake wheel (1) is connected with the other ground fixing device (9) sequentially through the downward restraint sensor (8) and the stroke-adjustable downward restraint device (7), and the vertical downward restraint situation is formed.

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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