Anti-vibration self-resetting satellite antenna supporting rod structure

Abstract

The invention discloses an anti-vibration self-resetting satellite antenna supporting rod structure, which comprises a self-resetting elastic support friction damping component for controlling axial vibration of an unfolding component, a volute spiral spring for providing unfolding driving force for an antenna supporting rod, a hinge and a carbon fiber rod for connecting all parts. The self-resetting elastic support friction damping structure control component has the same axis, a groove is formed in the inner cylinder baffle, the radial movement is limited through limiting screws, and the twosymmetrically-arranged hexagon socket head cap screws play a clamping role and are used for preventing axial movement of the inner cylinder baffle. The two metal rubber blocks playing a role in energy consumption are arranged between the inner cylinder and the outer cylinder and are symmetrically distributed on the two sides of the inner cylinder bafflee; one end of the inner cylinder is connected with the internal thread connecting piece which is connected with the carbon fiber rod; and the other ends of the outer cylinder and the inner cylinder are connected with external thread connectingpieces. When the inner cylinder and the outer cylinder generate relative motion due to vibration, axial vibration of the unfolding component is restrained through friction energy consumption of the metal rubber blocks.

Description

technical field [0001] The invention relates to the technical field of large-scale flexible self-deploying antenna structures, in particular to an anti-vibration self-resetting satellite antenna support rod structure. Background technique [0002] With the development of aerospace, communication and other industries, antennas, as an important means of transmitting electromagnetic wave signals, are more and more widely used in various fields. Due to the limitation of the space and capacity of the spacecraft, the large antenna should be sent into space in a folded state, and after reaching the predetermined orbit, it will be unfolded into the required geometric configuration after receiving instructions. In order to ensure that the large-scale self-deploying antenna not only meets the carrying conditions, but also ensures high resolution and high stability, the structural characteristics of the large-scale self-deploying antenna in space need to have light weight, high deploym...

AI Technical Summary

Problems solved by technology

However, the structural shape of the satellite antenna has very significant differences and time-varying properties from the retracted state to the deployed state, which leads to the dynamic characteristics of the drive control system during the antenna deployment process and the time-varying dynamic characteristics of the satellite dynamic characteristics and the antenna structure during the deployment process. It is easy to be coupled and generate severe vibration, which brings difficulties to the design of the drive system

The structural shape of the large-scale flexible self-deploying antenna changes continuously during the deployment process and is a multi-degree-of-freedom multi-mode vibration system. Due to the weak stiffness and low natural frequency of the large-scale deployment size, coupling resonance is prone to occur during the deployment process, antenna locking action and attitude control engine Dynamic interference will also produce random vibrations in a wide frequency band. Satellite antennas still have to withstand many vibration excitations during the orbital phase. Although these vibration excitations are not large in magnitude, they are likely to affect the normal operation of key components of the antenna.

Traditional passive vibration control methods are difficult to reliably and effectively control the multi-degree-of-freedom and multi-mode time-varying structural vibrations during the entire deployment process of the antenna, while the active vibration control methods developed in recent years cannot avoid the shortcomings of the closed-loop control model being difficult to accurately establish and control time delay. The effect of vibration control in practical applications is greatly reduced

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