The invention discloses a fatigue test device for a tail undercarriage rocking arm mounting connector. The fatigue test device comprises a main mounting stand on which the tail undercarriage rocking arm mounting connector is arranged, a first actuator cylinder, a second actuator cylinder assembly, and a third actuator cylinder assembly, wherein a cylinder body of the first actuator cylinder is mounted on the main mounting stand, a piston rod of the first actuator cylinder is connected with the tail undercarriage rocking arm mounting connector, the second actuator cylinder assembly comprises a second actuator cylinder, a piston rod of the second actuator cylinder is connected with the tail undercarriage rocking arm mounting connector, the third actuator cylinder assembly comprises a third actuator cylinder, and a piston rod of the third actuator cylinder is connected with the tail undercarriage rocking arm mounting connector. The fatigue test device is advantaged in that boundary conditions of the tail undercarriage rocking arm mounting connector during mounting and loading can be accurately simulated, fatigue test on the tail undercarriage rocking arm mounting connector can be carried out, and the excellent effect is acquired through test verification and test data analysis.

Fatigue test device for tail undercarriage rocking arm mounting connector

A comprehensive testing apparatus and a testing method for simulating the impact of an arresting hook to a deck and the drop shock of an undercarriage belong to the testing apparatuses and testing methods, and especially relate to the technical fields of dynamic response load test used for the impact of a carrier aircraft to a deck and drop shock test of an undercarriage. The apparatus mainly comprises a testing rack system constituted of a rack (3), a vertical guide rail (2), a lift motor (1) and a hanging basket (4); and the apparatus also comprises a buffering system constituted of an undercarriage (5), a force testing platform (6) and a foundation (7); and an impact testing system is constituted of an arresting hook system (L) and an impact platform (P). By adopting the apparatus provided herein, the simulation of the impact of the arresting hook to the deck in the landing process and the test of drop shock of the undercarriage can be realized at the same time; and the dynamic response loads of the arresting hook and the undercarriage in the landing process can be acquired simply and conveniently, thus the problems of high risk, great difficulties and high cost when acquiring the datum of the on-aircraft test or land-based test are avoided; and the problem that the dynamic response of the impact of the arresting hook to the deck is hard to be acquired in a laboratory is solved.

Comprehensive testing apparatus and testing method for simulating impact of arresting hook to deck and drop shock of undercarriage

The invention discloses an elastic component large-load fatigue test device, a test method and an installation method. The elastic component large-load fatigue test device includes a test device pedestal, four stand columns and a movable beam, one end of each stand column is arranged on the test device pedestal, the other end penetrates through the movable beam and the movable beam can move back and forth vertically along the stand column, and the test device pedestal, the four stand columns and the movable beam form a frame type structure; a fixed platform used for fixing an elastic component clamp is also arranged on the test device pedestal, a vertical loading oil cylinder mechanism with a sensor is arranged on the movable beam, the vertical loading oil cylinder mechanism is utilized to press downwards and move to apply large-load excitation to an elastic component on the elastic component clamp and the collector is utilized to collect data, thereby performing a large-load static rigidity test and a dynamic fatigue test. The elastic component large-load fatigue test device provided by the invention can perform the large-load static rigidity test and the dynamic fatigue test on the elastic component, thereby satisfying test requirements before vehicle loading operation.

Elastic component large-load fatigue test device, test method and installation method

The invention provides an aircraft landing gear load calibration method and a test fake wheel structure. The load calibration method comprises the steps of replacing a test fake wheel with a genuine wheel, and transferring a calibration load including the heading torque; establishing a mechanical model of the test fake wheel load transfer, and enabling the external force to the test fake wheel to be equivalent to a concentrated load of the center of the test fake wheel, the concentrated load including all components determined by the degree of freedom; and carrying out data processing and the like. The test fake wheel structure comprises a cylindrical structure (1) at the center, four circumferentially distributed outrigger structures (2) extending out radially along the cylindrical structure (1) at the center, and a flange structure (3) extending out from one end of the cylindrical structure (1) at the center and being used for connection with a landing gear.

Aircraft landing gear load calibration method and test fake wheel structure

The invention discloses a fatigue testing apparatus for a mounting joint of a damper post of a main gear. The fatigue testing apparatus comprises a test bed, an actuator cylinder, and a test clamp. The test bed includes standing posts and a cross beam connected with the standing posts. A cylinder body of the actuator cylinder is installed on the cross beam; the actuator cylinder has a locking state and a motion state; and in the locking state, the cylinder body and the cross beam are connected firmly; and in the motion state, the cylinder body can move on the cross beam. The fatigue testing apparatus provided by the invention is simple and practical; and the processing and maintenance costs are low. The mounting and stress states of the mounting joint of the damper post of the main gear on the helicopter can be simulated accurately; and the fatigue characteristics of the mounting joint of the damper post of the main gear can be examined effectively.

Fatigue testing apparatus for mounting joint of damper post of main gear

The invention provides a plane type ejection launch carrier-borne aircraft front undercarriage static force test loading apparatus. The apparatus comprises a plane type test bench rack, an undercarriage, a lateral load loading device, a course load loading device, a vertical load loading device, an ejection load loading device, a hamper load loading device and a mooring load loading device. Based on a conventional loading technology, a set of loading equipment capable of applying ejecting, hampering and mooring loads is designed, and the vertical, course, lateral, ejection, hampering and mooring load loading of an ejection launch carrier-borne aircraft is finished on a single test bench, no replacement of tools is needed, all the loading points are fixed in the frame type test bench, a self-balance bearing system is formed when loading is performed, the bearing of the test bench is quite small, the fixation is facilitated, and the precision is high.

Plane type ejection launch carrier-borne aircraft front undercarriage static force test loading apparatus

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Plane type ejection launch carrier-borne aircraft front undercarriage static force test loading apparatus