A kind of rotary locking mechanism for launch vehicle

Abstract

The invention discloses a rotational locking mechanism for a carrier rocket. The rotational locking mechanism for the carrier rocket comprises a first folding rod, a second folding rod, a rotating shaft, a locking pin, a spring, bearings, a limiting pin and a nut; the first folding rod and the second folding rod both adopt blocky structures and are hinged through the rotating shaft, and the rotating shaft is fixedly connected with the nut; a recessed hole for installing the locking pin and the spring is formed in one end of the first folding rod, a round hole for installing the bearings is formed in the other end of the first folding rod, a through groove for installing the limiting pin is formed in the side surface of the first folding rod, and a counter hole for installing the limiting pin is formed in the side surface of the locking pin; and a recessed hole for installing the locking pin is formed in one end of the second folding rod, and a round hole for installing the bearings isformed in the other end of the second folding rod. According to the rotational locking mechanism for the carrier rocket, the folding rods, the rotating shaft, the locking pin, the spring, the bearings, the limiting pin and the nut are cooperated with each other, the design requirements of structural optimization, rapid folding and reliable supporting are achieved, and the defects of the complex structure and the weak carrying capacity of the traditional mechanical rotational secondary locking / release mechanisms are made up.

Description

Technical field [0001] The invention relates to a rotary locking mechanism for a launch vehicle, belonging to the technical field of mechanical rotary auxiliary locking structures. Background technique [0002] Due to the limitation of space structure, some structural products of the rocket need to be folded. When working, it is rotated and opened, and then locked in place to withstand various loads. [0003] In recent years, the design requirements for lightweight and high reliability of the internal micromechanical structure of the launch vehicle have become a common technical problem faced by designers in the industry. Conventional design schemes usually use linkage mechanisms, especially parallel multi-link structures. [0004] In the prior art, if the traditional mechanical rotating pair locking / release mechanism is to be applied to a launch vehicle, the following problems mainly exist: [0005] First, the structure is relatively complex. On the one hand, the carrier rocket invol...

AI Technical Summary

Problems solved by technology

[0007] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, the present invention provides a rotary locking mechanism for launch vehicles, through the first folding rod, the second folding rod, the rotating shaft, the locking pin, the spring, the bearing, The cooperation of the limit pin and the nut realizes the design requirements of structural optimization, fast folding and reliable support, and makes up for the defects of the traditional mechanical rotary pair locking / release mechanism with complex structure and weak bearing capacity

Images