Solar wing flexible simulator

Abstract

The invention discloses a solar wing flexible simulator. The solar wing flexible simulator comprises a base, a first simulating part, a second simulating part, a third simulating part and a torque sensor, wherein the first simulating part, the second simulating part and the third simulating part are sequentially connected and are installed on an air floating platform through the base connected with the first simulating part; the first simulating part is used for simulating the rotating inertia and the frequency of the first-order mode of a solar wing; the second simulating part is used for simulating the rotating inertia and the frequency of the sixth-order mode of the solar wing; the third simulating part is used for simulating the rotating inertia and the frequency of the twelfth-order mode of the solar wing; and the torque sensor is arranged at the position, close to the air floating platform, of the simulator and is used for measuring the torque output by the simulator to the air floating platform. The solar wing flexible simulator can analyze influences of different rotating inertias and different mode frequencies on a spacecraft body structure, and on the basis, the solar wing structure can be subjected to optimized design.

Description

Technical field [0001] The invention relates to the field of aerospace technology, in particular to a solar wing flexibility simulator. Background technique [0002] With the continuous increase in functions and complexity of modern spacecraft, flexible accessories such as large solar panels are also increasing. Because the flexible attachment is made of low-rigidity lightweight materials, the spacecraft is susceptible to various propulsive forces to produce large vibrations when flying in orbit. The vibration of the flexible attachment is coupled with the motion of the spacecraft body. It will affect the attitude stability and orientation accuracy of the spacecraft, and even damage the instrument and cause the spacecraft to fail. Therefore, it is of great significance to design a solar wing flexible simulator to conduct physical simulation experiments on the ground to study the influence of flexible accessories on the main structure of the spacecraft. [0003] The solar wing has...

AI Technical Summary

Problems solved by technology

[0004] (1) The active simulator generates the required vibration form through the exciting parts, and its moment of inertia is almost unchanged when the vibration changes, so it cannot simulate the characteristics of different modes of spacecraft solar wings corresponding to different moments of inertia, and the simulation reliability is low

[0005] (2) The solar wing of the spacecraft has low stiffness, high modal order and dense low frequency. The existing simulators generally have small geometric dimensions and high modal frequencies, so it is difficult to achieve accurate simulation of frequency

In addition, there is no external resistance in the space environment, and the modal amplitude of each order of the solar wing is relatively large. The vibration of the existing simulator weakens rapidly with the modal order, and it is impossible to realize the true simulation of the modal amplitude of each order.

[0006] (3) In the actual test, it is often not necessary to pay attention to most of the modes of the solar wing, and it is only necessary to simulate the modes that have a greater impact on the system. The existing technology cannot provide the above-mentioned selective mode simulation

[0007] (4) In practical applications, it is often necessary to set the modal parameters such as torsion and bending separately, which cannot be realized by the existing technology

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