Thermal self-adaptive variable configuration wing

Abstract

The invention discloses a thermal self-adaptive variable configuration wing, and relates to the field of reusable hypersonic aircraft thermal protection. The thermal self-adaptive variable configuration type wing comprises a high temperature heat pipe structure, a high temperature shape memory alloy structure, a telescopic structure, a connecting rod system and a wing leading edge. The wing leading edge is of a hollow-rod structure. One axial end of the wing leading edge is fixedly mounted on the outer wall of an outer aircraft body. The high temperature heat pipe structure is fixedly mountedon one side of the wing leading edge. The high temperature heat pipe structure is located at the connecting position of the wing leading edge and the outer aircraft body. The telescopic device is fixedly mounted on the outer wall of the outer aircraft body, and is fixedly connected with one axial end of the high temperature heat pipe structure. The shape memory alloy structure is arranged on the outer wall of the high temperature heat pipe structure in a sleeving mode. The telescopic device is connected with the wing leading edge by the connecting rod system. A traditional motor driving systemis not required. The structure is simple, the weight is low, and a control feedback system is not needed. Variable configuration design of aircraft wing surfaces is achieved by a thermal self-adaptive variable configuration principle, and therefore overall performance of a hypersonic aircraft can be improved.

Description

technical field [0001] The invention relates to the thermal protection field of a reusable hypersonic aircraft, in particular to a thermal adaptive variable configuration wing. Background technique [0002] The new hypersonic aircraft represented by the new generation of hypersonic aircraft in the future, hypersonic gliding in adjacent space, and space shuttle aircraft have important development value. The flight speed range and airspace of this type of hypersonic aircraft are relatively wide. The design is based on a single state point (a certain Mach number and angle of attack), and its aerodynamic performance will be affected when it deviates from the design state point. In addition, this type of hypersonic vehicle is subjected to severe aerodynamic heating. In the hypersonic state, in order to achieve non-ablative thermal protection design, a blunt leading edge is required. However, in the low-speed flight state, the blunt leading edge greatly affects the Due to the aer...

AI Technical Summary

Problems solved by technology

Early aerodynamic shape change technologies such as variable-sweep wing technology and other deformable aircraft (such as F-14 fighter, MiG-23 fighter, XB-70 bomber, etc.) Disadvantages such as high maintenance costs greatly limit the development of deformable aircraft

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