Low-impact hinge unfolding mechanism

Abstract

The invention discloses a low-impact hinge unfolding mechanism. The low-impact hinge unfolding mechanism comprises a first hinge, a center shaft, a second hinge, a power spring, a resistance spring, aflexible grinding piece and a friction box. The first hinge is connected with the center shaft through a bearing. The second hinge is arranged on the center shaft through a spline. The power spring and the resistance spring are arranged at one end of the center shaft, and the other end of the center shaft is connected with the flexible grinding piece through a planetary gear train. The flexible grinding piece makes contact with the inner wall of the friction box. According to the low-impact hinge unfolding mechanism, two volute spiral springs are adopted for providing power and resistance correspondingly, and the resultant force is kept stable in the whole unfolding action process by adjusting parameters of the two springs; the unfolding angular speed of a planetary gear train amplifyingmechanism is adopted, and the flexible grinding piece is driven to conduct friction energy dissipation along the inner wall of the friction box; and when the unfolding angular speed is too large, thefriction resistance of the flexible grinding piece is increased under the action of centrifugal force, more resistance torque is provided for the mechanism, and accordingly, the unfolding speed is reduced, and impact is reduced.

Description

Technical field [0001] The invention relates to the technical field of spacecraft passive deployment mechanisms, and in particular to a low-impact hinge deployment mechanism. Background technique [0002] The antenna on the satellite needs to be unfolded from the folded state to the working state after the satellite is in orbit. Usually such unfolding tasks are one-time. The hinge unfolding mechanism has the advantages of low cost and high reliability, so it is widely used in satellite antenna unfolding tasks. middle. However, as the size of satellite antennas increases and the mass of the antennas becomes lighter, the disadvantage of the traditional hinge deployment mechanism is that the impact is too large at the end of the deployment action. Due to the lack of resistance in space, the vibration of the antenna caused by a large impact is difficult to dissipate quickly, which can easily cause instability in the performance of the antenna. Excessive instantaneous impact may...

AI Technical Summary

Problems solved by technology

However, with the increase in the size of the satellite antenna and the reduction in the quality of the antenna, the traditional hinge deployment mechanism has the disadvantage of excessive impact at the end of the deployment action.

Due to the lack of resistance in the space, it is difficult to quickly dissipate the vibration of the antenna caused by a large impact, which may easily cause the instability of the antenna's performance. Excessive instantaneous impact may damage the weak support rods on the antenna, causing the antenna to fail. This is detrimental to the reliability of the entire satellite extravehicular mechanism

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