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Inertia load simulation apparatus

A technology of simulating device and inertial load, applied in measurement devices, motor generator testing, instruments, etc., can solve the problems of inaccurate acceleration value, cumbersome operation, low frequency, etc. The effect of reliability

Inactive Publication Date: 2017-05-10
BEIJING RES INST OF PRECISE MECHATRONICS CONTROLS +1
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The existing inertial load simulation device uses a low-frequency large-deflection adjustable inertial load simulation part, and its load is a solar panel. Compared with the nozzle or rudder load, the frequency is low, and it is not suitable for the working conditions of high-frequency and large-scale movement of aerospace servo motors. Moreover, in the current inertial load simulation devices, the inertia simulation is realized by single loading or combined loading of the loading plate or inertia block, which requires continuous assembly and disassembly, tedious operation, time-consuming and laborious
For acceleration measurement, the current inertial load simulator uses velocity differentiation to obtain acceleration, which is too much affected by noise and the acceleration value is inaccurate

Method used

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Embodiment Construction

[0027] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.

[0028] Such as figure 1 As shown, the inertial load simulation device involved in the present invention is built in the dynamic loading system of the servo motor. The dynamic loading system of the servo motor includes the motor to be tested 1, the first bracket 2, the first coupling 3, the torque sensor 4, the second Bracket 5, acceleration sensor 6, second coupling 7, electric slip ring 8, third bracket 9, loading motor 10, screw 11, ground rail 12, tested motor driver 13, loading driver 14, first signal line 15 , the second signal line 16, the third signal line 17, the fourth signal line 18, and the control cabinet 19. The first coupling 3, the torque sensor 4, the second bracket 5, the acceleration sensor 6, the second coupling 7, the electric slip ring 8, the third bracket 9, and the loading motor 10 form an inertial load loading device. ...

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Abstract

The invention belongs to the field of a spaceflight servo motor loading test and specifically discloses an inertia load simulation apparatus. The apparatus comprises a first shaft coupling, a torque sensor, an acceleration transducer, a second shaft coupling, an electric slip ring and a loading motor, wherein the output end of the first shaft coupling is connected with the input shaft of the torque sensor, the output shaft of the torque sensor is connected with one end of the second shaft coupling, the second shaft coupling is internally provided with the accelerated speed sensor, and the other end of the second shaft coupling is connected with one end of the electric slip ring. Inertia simulation of the apparatus is simple and is easy to operate, the acceleration measurement is accurate and highly reliable, and the apparatus has the advantages of noise isolation function, compact structural layout and integrated design.

Description

technical field [0001] The invention belongs to the field of loading test of an aerospace servo motor, and in particular relates to an inertial load simulation device for an aerospace servo motor. Background technique [0002] Servo motors for aerospace, as the key power components of electromechanical servo systems, receive position commands from the control system and drive air rudders or nozzle loads. Its typical working condition is frequent acceleration and deceleration, in addition to bearing the elastic load and friction load that drives the load movement, it also bears inertial load. The dynamic characteristics of the motor have become an important technical index to measure the performance of the servo motor, which is directly related to the output capability of the electromechanical servo system to drive the nozzle or rudder surface load and the fast response capability of acceleration and deceleration. [0003] In order to fully assess the dynamic performance of ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01R31/34
CPCG01R31/343
Inventor 闫海媛郑再平魏娟朱晓荣王一鹏
Owner BEIJING RES INST OF PRECISE MECHATRONICS CONTROLS
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