Cabin body outer folding wing system with large aspect ratio

Abstract

The invention discloses a cabin body outer folding wing system with a large aspect ratio. The system comprises a mounting base, a rotating shaft support, a rotating shaft, a shaft end top cover, a spring support, a missile wing, a locking pin assembly, an axial compression spring, a drive extension spring and a steel wire rope assembly. In the initial state, the missile wing is enabled to be in acollapsed and folded state, after a constraint is relieved, the unfolding function of the missile wing is realized under the action of the drive extension spring and the axial compression spring, andlocking of the missile wing unfolding state is realized through the locking pin assembly. According to the cabin body outer folding wing system with the large aspect ratio, the defects in the prior art are overcome, the design process is parameterized, rapid transplantation can be realized according to requirements of different weapon systems, the system has the characteristics that the mechanismis easy, locking is reliable, the outer enveloping size of the folded state is small, the unfolding state is good in pneumatic shape, the cabin body internal space occupied by the mechanism is small,and the working process is smooth and non-impact, and the system can be used as a large-aspect-ratio folding wing assembly of an airborne launched missile and a ground barrel-mounted launched missile.

Description

technical field [0001] The present invention relates to a novel large-aspect-ratio cabin external folding wing system, in particular to a projectile external-flap wing deployment system that effectively reduces storage space and greatly increases weapon range, and can be applied to various It can be used for airborne and ground tube-launched missiles with a wing layout, as well as aircraft with similar aerodynamic shapes such as cruisers and unmanned aerial vehicles. Background technique [0002] In order to meet the operational requirements of standoff strikes and low collateral damage in modern warfare, the range and flight range requirements of flying missiles are constantly increasing. At the same time, weapons should have as compact a structural shape as possible when mounted on a carrier aircraft or launched from the ground. The requirements of long range and small size make more and more combat weapons adopt the layout of folding wings. [0003] Traditional folding w...

AI Technical Summary

Problems solved by technology

The outer envelope size of the horizontal folding method is affected by the wingspan of the projectile, so it is not suitable for aerodynamic layout with large aspect ratio

The structural layout of the longitudinal folding method is greatly affected by the chord length of the wings. The longitudinal in-line groove on the cabin or the torsion spring mounting seat outside the cabin will have a great impact on the structural strength and aerodynamic shape. The wings also greatly squeezed the interior space of the cabin

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