High rigidity deploy-in-position locking device

Abstract

The invention provides a high-rigidity expansion in-place locking device. The high-rigidity expansion in-place locking device comprises an upper support, a lower support, at least one lock hook and at least one lock tongue assembly, wherein the upper support is connected with the lower support through a bearing, the upper support can rotate relative to the lower support, the lock hooks are connected to the upper support, the lock tongue assemblies are connected to the lower support, and the lock hooks can be matched with the lock tongue assemblies to lock relative rotation between the upper support and the lower support. Compared with the prior art, the high-rigidity expansion in-place locking device achieves the high-rigidity expansion in-place locking function of an expansion mechanism, expansion locking movement is simple, the requirement for moving accuracy is low, the locking rigidity is high, and the locking reliability is high.

Description

technical field

[0001] The invention relates to a locking device for an aerospace vehicle deployment mechanism, in particular to a high-rigidity deployment-in-position locking device for a solar battery wing and a satellite antenna deployment mechanism. Background technique

[0002] The solar battery wings and satellite antennas of aerospace vehicles need to be compressed before launch to overcome the vibration and shock load during the launch into orbit stage. on-orbit fundamental frequency.

[0003] At present, the deployment and locking methods commonly used by aerospace vehicles include self-locking worm gear methods and latch methods. The disadvantage of the worm gear method is that the working load is generally only a few tens of Nm, which cannot meet the needs of the large inertia load of hundreds to thousands of Nm to expand and lock, and under the influence of the load impact, a motion gap will gradually occur. The locking stiffness is reduced. In addition, due to...

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