Damping component of large self-unfolding satellite antenna

A satellite antenna and self-deploying technology, which is applied to antenna components, antennas, folding antennas, etc., can solve the problems of large energy consumption due to nonlinear frictional vibration, control frequency bandwidth, etc., and meet the requirements of ensuring lightweight, control frequency bandwidth, and power consumption can have a big effect

Active Publication Date: 2020-05-08
BEIJING UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Aiming at the coupling vibration problem that is easy to occur during the deployment process of the satellite antenna and when the attitude is adjusted after deployment, the present invention designs a structural rod assembly, mainly by adding two kinds of friction dampers to the satellite support rods to absorb energy and absorb vibrations components to achieve the effect of vibration suppression, using the characteristics of large energy consumption of nonlinear friction vibration and wide frequency control, can effectively improve the effectiveness, stability and reliability of vibration control of large flexible self-deploying devices

Method used

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  • Damping component of large self-unfolding satellite antenna
  • Damping component of large self-unfolding satellite antenna
  • Damping component of large self-unfolding satellite antenna

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specific Embodiment approach 1

[0032] Specific implementation mode one: combine Figure 1-Figure 9To illustrate, take the radial rib satellite antenna as an example to introduce the vibration damping member of the large self-deploying satellite antenna of the present invention. The damping member of the large-scale self-deploying satellite antenna of the present invention comprises four parts: a self-resetting axial damper 1, a multi-finger flap friction damper 2, a folding hinge assembly 3, and a support rod 12; the support rod 12 serves as The basic structural parts are respectively connected to the self-resetting axial damper 1 and the folding hinge assembly 3, and serve as the base body of the multi-finger valve pressure plate 11, and are connected to the multi-finger valve pressure plate 11 through the outer ring locking ring 10 to jointly form a multi-finger valve Damper assembly 2. The radial rib assembly A is formed by sequentially connecting the shock-absorbing components of six large self-deployi...

specific Embodiment approach 2

[0033] Specific implementation mode two: combination Figure 4 , Figure 5 Explain that the self-resetting axial damper 1 of the present embodiment is composed of an outer sleeve 8, a damping energy dissipation element 9, a shape memory alloy wire 7 and a guide shaft 19. The two outer sleeves 8 are butted, and the annular metal rubber 9 is passed and fixed between the two outer sleeves as a damping energy dissipation element by a guide shaft 19. The guide shaft 19 can ensure the radial stiffness and vibration direction of the damper. The shape memory alloy wire 7 has superelastic mechanical properties, and provides axial preload for the metal rubber 9 of the axial damper 1 by being wound on the two outer sleeves 8. When vibration occurs, the vibration will cause the two outer sleeves to The relative position between the sleeves 8 changes, thereby causing the stretching or compression of the metal rubber 9, and the thin metal wires in the metal rubber 9 rub against each other ...

specific Embodiment approach 3

[0034] Specific implementation mode three: combination image 3 , Figure 6 Explain that the multi-finger flap damper 2 of the present embodiment adopts the carbon fiber multi-finger flap thin-walled ring cross-section structure of the same material as the support rod 12 as the multi-finger flap pressure plate 11, and the root of one end of the damping structure is not divided into flaps, and is fixed to the hinged end of the expansion member. Together, the remaining parts are multi-finger valve structures, and are pre-pressed on the outer wall of the expansion member through the outer ring locking ring 10 . When the support bar 12 vibrates laterally, because the vibration and deformation of the multi-finger platen 11 and the structural bar 6 are different in size, relative displacement will occur between the two, and the outer locking ring 11 will be multi-finger through the pre-tightening force. The damper 2 exerts a frictional force, so frictional energy will be generated ...

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Abstract

The invention discloses a damping component of a large self-unfolding satellite antenna, and aims to solve a problem of profile precision errors caused by vibration in an unfolding process of an existing unfolding antenna mechanism and in a posture adjusting process after unfolding. The component comprises a multi-finger-petal friction damper, a self-resetting elastic support friction damper, an elastic driving hinge and a satellite structure rod piece. The multi-finger-petal friction damper controls transverse vibration of the satellite unfolding antenna and comprises a multi-finger-petal rodwhich is pressed on a structural rod piece through an adjustable pressing ring. The self-resetting elastic support friction damper controls axial vibration and comprises a metal rubber, a guide rod,an SMA pull wire and an outer sleeve. The elastic driving hinge provides unfolding power through a volute spring, and an unfolding speed and synchronism are controlled through a gear. The satellite structure rod piece is fixedly connected with other assemblies so that integrity of the unfolded antenna is ensured. The component is used for satellites and space detectors.

Description

technical field [0001] The invention relates to the technical field of satellite flexible deployment mechanism, in particular to a vibration damping component of a large self-deploying satellite antenna, which belongs to the technical field of aerospace equipment and equipment. Background technique [0002] The development of mobile communication satellites equipped with large-aperture antennas, astronomical exploration satellites, geosynchronous observation satellites, and military reconnaissance satellites is the core technology for establishing high-resolution earth observation systems and space-based earth observation and detection systems. With the development of satellite technology, large-scale flexible self-deploying antennas are gradually developing towards the two technical characteristics of large deployment size and high surface accuracy, and the design requirements are getting higher and higher. Due to the limitation of the payload of the launch vehicle and the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01Q1/00H01Q1/28H01Q1/08H01Q1/12
CPCH01Q1/005H01Q1/08H01Q1/12H01Q1/288
Inventor 王民刘钦达赵婷婷刘佳星
Owner BEIJING UNIV OF TECH
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