Servo motor type undercarriage retractile follow-up loading system and loading method of loading system

Abstract

The invention relates to a servo motor type undercarriage retractile follow-up loading system and a loading method of the loading system, belonging to the field of test technology of undercarriages. The servo motor type undercarriage retractile follow-up loading system mainly comprises a test bed (1), a hanger plate (4), a main supporting pole clamp (5) and a retractile actuator cylinder clamp (6), which form a clamping bearing mechanism; the servo motor type undercarriage retractile follow-up loading system also comprises a support frame (2), a vertical servo motor (25), a ball screw (16) and a lifting table (19), which form a loading direction follow-up mechanism; the servo motor type undercarriage retractile follow-up loading system also comprises a fixed table (14), a horizontal servo motor (10), a speed reducer (11), a disc (12), a steel rope (13), a steering pulley (17), a steering pulley support (18), a loading plate (9) and a fixed pulley (8), which form a load size simulation mechanism. According to the invention, the difficult problem of asymmetrical load in the retractile process is solved, the loading direction of loads is ensured to be horizontal all the time, the test precision is improved and the test reliability is enhanced.

Description

technical field [0001] The invention relates to a servo motor type landing gear retractable follow-up loading system and a loading method thereof, which belong to the technical field of a landing gear test. technical background [0002] The landing gear retractable system is an important part of the aircraft, and the working performance of the system directly affects the maneuverability and safety of the aircraft. In order to improve the aerodynamics of the aircraft in flight, the landing gear of modern aircraft is usually designed to be retractable. It is stored inside the fuselage or wing when flying in the air, and is lowered to bear the ground load when taking off and landing. Furthermore, the air-to-ground cycle of modern aircraft is short, and the ground movement distance is long during the service life, resulting in more failures of the landing gear structure. Therefore, it is an important part of aircraft design to verify the retractable function of the aircraft on ...

AI Technical Summary

Problems solved by technology

[0007] The load direction of this scheme is better, but it has its shortcomings: first, the structure is complicated, the ropes are too many and the pulling lines are messy, which is not conducive to the retraction and retraction of the landing gear; second, for the larger size of the landing gear, Due to space constraints, it may not be possible to install the mass block loading mechanism; third, the accuracy of the mass block loading method is not high; fourth, during the retraction process, the mass block will sway due to its own inertial force and cause collisions. Hidden dangers; Fifth, the designed cam has a unique shape and can only correspond to one load condition, and it may not be possible to design a corresponding cam under certain conditions

[0009] The tracking performance of the load simulation of this scheme is better, but its disadvantage is that it has higher requirements on the hydraulic actuator: first, the stroke of the loading actuator is limited, which may not meet the required height of the large-sized landing gear; Second, the speed of loading the actuator is relatively small, which may not be able to meet the speed required when the landing gear is retracted; third, the moment equivalent method will generate additional force, resulting in an inaccurate force model during the retraction process; fourth, A complete set of hydraulic servo control system needs to be built, and the test cost is high and the cycle is long

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