Large-load low-stiffness suspension system for spacecraft on-orbit weightlessness simulation

Abstract

The invention provides a large-bearing low-rigidity suspension system for simulating an on-orbit weightless environment of a spacecraft. The large-bearing low-rigidity suspension system adopts a manner of centralized hanging, and comprises a foundation plate (6), a rack stand column (8), a lifting crossbeam (1), an elastic rope mounting disc (3), a hanging platform (4), load cells (9), a dragging mechanism (5), a dragging counter weight (7) and steering pulleys (12), wherein the elastic rope mounting disc (3) and the lifting crossbeam (1) are elastically connected through an elastic rope; the elastic rope mounting disc (3) is connected with the hanging platform (4) through a rigidity rod; the load cells (9) are mounted on the rigidity rod; the rack stand column (8) is fixedly connected to the foundation plate (6); and the dragging mechanism (5) and the dragging counter weight (7) are connected with the steering pulleys (12) through a steel wire rope (11). According to the large-bearing low-rigidity suspension system disclosed by the invention, the on-orbit weightless environment of the spacecraft can be more veritably simulated.

Description

technical field [0001] The invention relates to a large-load low-rigidity suspension system for the simulation of the weightlessness environment of a spacecraft on orbit, especially to provide an advanced means of isolating the vibration interference transmitted from the outside to the product for the simulation of the weightlessness environment of the spacecraft on orbit, and specifically relates to a spacecraft in the orbit of weightlessness environment. Large-load low-stiffness suspension system for rail weightlessness environment simulation. Background technique [0002] The spacecraft is subjected to single or combined effects of disturbance sources such as attitude and momentum wheel adjustment, thruster attitude adjustment, solar panel adjustment, camera scanning mechanism work, etc., which will cause the spacecraft to malfunction in systems that are sensitive to micro-vibration environments. The kinetic energy of the vibration is small, the frequency is wide, and the...

AI Technical Summary

Problems solved by technology

[0002] The spacecraft is subjected to single or combined effects of disturbance sources such as attitude and momentum wheel adjustment, thruster attitude adjustment, solar panel adjustment, camera scanning mechanism work, etc., which will cause the spacecraft to malfunction in systems that are sensitive to micro-vibration environments. The kinetic energy of the vibration is small, the frequency is wide, and the attitude control system is difficult to measure and control, and it will cause micro-deformation or micro-displacement between the parts that make up the structure of the space camera and the optical system, and affect the imaging quality.

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