Louver type cracking composite wing

Abstract

The invention discloses a shutter-typed cracking composite wing, comprising a wing mainbody which is internally provided with a main wing beam and a rear wing beam; the main wing beam consists of an inclinable section and a non-inclinable section which are connected with each other; the wing mainbody is connected with an aircraft main bearing frame; the left side and the right side of the wing mainbody are respectively provided with two through spaces; the inclinable section of the main wing beam is provided with two groups of inclined power devices; each through space is respectively provided with a group of shutter-typed cracking composite envelope which consists of an upper shutter-typed cracking composite envelope and a lower shutter-typed cracking composite envelope; the upper shutter-typed cracking composite envelope and the lower shutter-typed cracking composite envelope are respectively connected with the wing mainbody. The wing leads the unbalanced moment during the vertical lifting of the aircraft and the wind-facing resistance during the transitional flying of the aircraft to be reduced to the minimum; meanwhile, the whole wing, especially for the external wing of the large wing keeps horizontal and still fixedly all the time, thus ensuring the stability during the vertical lifting of the aircraft and successful transition to the flat flying state.

Description

technical field [0001] The invention relates to an aircraft wing, in particular to a louver type split composite wing. Background technique [0002] At present, various existing vertical take-off and landing aircrafts that use propellers, counter-rotating propellers, rotors or ducted fans as tilting power devices all install these tilting power devices on the wingtips of the wings, or together with the entire The wings are tilted together, which results in a very large unbalanced moment during vertical take-off and landing, which is prone to instability and rolls, or the wind resistance of the entire wing is particularly large during transitional flight, making it impossible to transition smoothly to This is also one of the main reasons why this type of aircraft has seldom been successful so far. Therefore, the wing configuration of the existing vertical take-off and landing aircraft cannot meet the needs of people. Contents of the invention [0003] The object of the pr...

AI Technical Summary

Problems solved by technology

[0002] At present, various existing vertical take-off and landing aircrafts that use propellers, counter-rotating propellers, rotors or ducted fans as tilting power devices all install these tilting power devices on the wingtips of the wings, or together with the entire The wings are tilted together, which results in a very large unbalanced moment during vertical take-off and landing, which is prone to instability and rolls, or the wind resistance of the entire wing is particularly large during transitional flight, making it impossible to transition smoothly to This is one of the main reasons why this type of aircraft has seldom been successful so far.

Therefore, the wing configuration of the existing vertical take-off and landing aircraft cannot meet the needs of people.

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