Folding wing for hypersonic flight vehicle
A hypersonic, aircraft technology, applied in supersonic aircraft, aircraft, wings and other directions, can solve the problems of inability to meet the design requirements of hypersonic folding wings, complex aerodynamic thermal environment, large deployment thrust, etc., to reduce the impact, Small size, easy to design effect
Pending Publication Date: 2021-06-18
INST OF MECHANICS - CHINESE ACAD OF SCI
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Problems solved by technology
For the design of a hypersonic folding wing, its aerodynamic and thermal environment is complex. In order to deploy reliably, a large deployment thrust is required, which in turn easily causes a large impact force
Therefore, the folding wings designed in the prior art cannot meet the design requirements of hypersonic folding wings
Method used
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[0017] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention more clear, the following will clearly and completely describe the technical methods in the embodiments of the present invention in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments It is only some embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative labor achievements belong to the protection scope of the present invention.
[0018] It should be noted that if there is a directional indication (such as up, down, left, right, front, back, etc.) in the embodiment of the present invention, the directional indication is only used to explain the relationship between the components in a certain posture. Relative positional relationship, movem...
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The embodiment of the invention relates to a folding wing for a hypersonic aircraft, and the folding wing comprises an internal wing, an external wing and a folding locking device; the folding locking device is arranged at a rotating shaft between the internal wing and the external wing, and the internal wing is connected with the external wing through the folding locking device. And the unfolding of the external wing and the locking after folding are controlled through a rotating mechanism arranged in the folding locking device. According to the embodiment of the invention, the folding locking mechanism is arranged along the rotating shaft between the internal wing and the external wing, so that stable locking can be realized after the wings are unfolded. Meanwhile, the device also has the characteristics of small size and good bulge, is convenient for designing a fairing, reduces the influence of aerodynamic performance on the wing unfolding process, meets the requirements of a hypersonic aircraft, and can adapt to a complex flight environment.
Description
technical field [0001] Embodiments of the present invention relate to the technical field of aircraft design, in particular to a folding wing for a hypersonic aircraft. Background technique [0002] Traditional folding wings are generally used in tactical bombs with a Mach number below Ma<5, and the application of folding wings has not yet been seen in high-flying aircraft (Ma>5). However, with the rapid development of aerospace in various countries, the application of deformable wings such as folding wings on hypersonic vehicles will become the development trend of hypersonic vehicles and wide-area vehicles in the future. For the folding wing, the design of its unfolding and locking mechanism is one of the keys to the overall structure design of the folding wing. For tactical bombs with low Mach numbers, the aerodynamic and thermal environment is not harsh, so the design requirements for the unfolding and locking mechanism are not high. , The deployment mechanism can...
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IPC IPC(8): B64C3/54B64C3/36B64C30/00
CPCB64C3/546B64C3/36B64C30/00
Inventor 申亮胡灯亮龙丽平杨正茂宫钇成
Owner INST OF MECHANICS - CHINESE ACAD OF SCI