Loading test device for electric folding and unfolding mechanism of airplane illuminating lamp

Abstract

The invention relates to a loading test device for the electric folding and unfolding mechanism of an airplane illuminating lamp. The loading test device comprises a support; a load loading mechanismis fixedly installed on one side of the support; a product fixing clamp fixedly connected with the airplane illuminating lamp is arranged on the other side of the support; the output end of the load loading mechanism is connected with a loading frame; the loading frame is provided with an abutting clamp abutting against the lampshade of the airplane illuminating lamp; the load loading mechanism comprises a torque sensor; one end of the torque sensor is connected with a torque motor; the other end of the torque sensor is connected with a loading shaft A; one side of the loading frame is connected with the loading shaft A; the other side of the loading frame is connected with a loading shaft B; the loading shaft A and the loading shaft B are connected with the support through a bearing seatA and a bearing seat B; and an angle encoder is arranged on the loading shaft B. According to the loading test device of the invention, the constant torque loading of the electric folding and unfolding mechanism of the aircraft illuminating lamp in the rotating angle range of the electric folding and unfolding mechanism can be realized; and a moment rotating angle curve of a wind resistance momentchanging along with an angle can be simulated, so that simulation loading can be carried out, and therefore, test items are comprehensive, and no test blind areas exist.

Description

technical field [0001] The invention relates to the technical field of testing, in particular to a loading test device for an electric retractable mechanism of an aircraft lighting lamp. Background technique [0002] The electric retractable mechanism of the aircraft lighting is mainly to release the lighting from the fuselage when the aircraft is landing at night, refueling, etc., so that the pilot can observe the surrounding environment. After the operation is completed, retract the light to the inside of the fuselage. During the high-speed flight of the aircraft, the resistance of the wind is applied to the lampshade, so that when the lamp is released and retracted, its electric retractable mechanism is subjected to an additional wind resistance torque. This just needs electric retractable mechanism to be able to provide enough moment, except the moment of overcoming self mechanism, also will overcome wind resistance moment. [0003] Therefore, when the lighting lamp le...

AI Technical Summary

Problems solved by technology

The loading device currently used is traditional purely mechanical loading, which is realized by hanging balance weights. When the lighting is retracted and retracted, it is loaded by overcoming the moment generated by the component force of weight gravity. Therefore, different types of aircraft lighting Due to the different loading moments required by the product, it is necessary to hang weights of different weights, resulting in a product loading corresponding to a loading device, which cannot be compatible

[0004] What is important is that, due to the limitations of the loading structure, the loading method of hanging balance weights, the torque generated by overcoming the component force of weight gravity is a variable curve torque that changes with the change of the retracting angle of the electric retractable mechanism, and this variable The curve torque is very different from the actual wind resistance torque curve, which cannot simulate the loading of the actual wind resistance torque

Therefore, the reliability of the performance of the tested electric retractable mechanism cannot be guaranteed

[0005] In addition, the loading method of hanging the balance weight can only realize the loading in the direction of releasing the lighting of the electric retractable mechanism of the aircraft lighting lamp, and cannot realize the loading in the direction of recovering the lighting lamp

Similarly, the loading method of hanging balance weights cannot achieve fixed angle loading, constant moment loading, and overload loading, nor can it automatically calculate the test and inspection of aircraft lighting retraction time and service life testing, resulting in incomplete testing. There is a test blind area, which affects the reliability of the use of aircraft lighting

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