Stable hanging and separating mechanism of pod rod for spacecraft

Abstract

The invention discloses a stable hanging and separating mechanism of a pod rod for a spacecraft, wherein the mechanism comprises an upper fixing ring, a lower fixing ring, an upper and lower ring connecting device, a sliding pin locking device, an action sensing device, a pin detacher and a pop-up separator. When the pod rod is fully extended to be in place, the lower end of a locking pin of the sliding pin locking device penetrates through a through hole formed in the pod rod and slides into a locking hole of the lower fixing ring, and the pod rod is locked by the mechanism; meanwhile, the action sensing device generates a triggering electric signal, on one hand, a retractable pin of the pin detacher is triggered to withdraw, the upper fixing ring moves downwards, and thus, the pod rod hugging is achieved; on the other hand, the pop-up separator is triggered to be started, and separation of the structure is achieved. According to the stable hanging and separating mechanism of the pod rod for the spacecraft, two technical means of using the sliding pin locking device and the movable upper fixing ring structure are combined, stable hanging of a film structure on the pod rod can be achieved, and meanwhile, the stable hanging and separating mechanism has the advantages of being simple, effective, sensitive and reliable.

Description

technical field [0001] The invention relates to the technical field of aerospace structure and mechanism design, in particular to a stable suspension and separation mechanism of a pod rod for a spacecraft. Background technique [0002] Solar sail spacecraft is a spacecraft that uses the reflected light pressure of sunlight on the film sail surface to provide flight power. The structure of the film sail surface is usually realized by forming a square or hexagonal structure through support rods and films. . Because the pod pole has the advantages of light weight, high rigidity, high storage efficiency, reliable deployment process, and small thermal expansion coefficient, it is a good structural form that can be used as a support pole for solar sail spacecraft. In order to further reduce the structural mass of the solar sail spacecraft so that it can achieve greater acceleration, after the solar sail spacecraft is fully deployed, it is a better solution to throw the retractabl...

AI Technical Summary

Problems solved by technology

[0003] However, in the design of the jettisonable solar sail spacecraft, the following technical problem is faced: on the one hand, when the pod poles are fully deployed in place, the membrane structure should be stably suspended on the ends of the pod poles, so that the connection points of the membrane structures It is firmly connected to the pod rod; on the other hand, while achieving stable suspension, the stable suspension mechanism must also be reliably separated from the retractable mechanism, which is conducive to the abandonment of the retractable mechanism. Therefore, it is necessary to design a stable suspension with separation mechanism

So far, there is no literature report on this type of stable suspension and separation mechanism

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