The invention relates to a cabin thermal protection structure and an aircraft. A second part and a first part which are the same are connected to form a thermal insulation layer; the second part sequentially comprises a windward part, a transition part and a leeward part from bottom to top; in the extending track direction from the windward part to the leeward part, the thicknesses of any two positions of the windward part are equal, and the thicknesses of any two positions of the leeward part are equal and are smaller than the thickness of the windward part; the thickness of the transition part is gradually reduced from the joint of the transition part and the windward part to the joint of the transition part and the leeward part; according to the characteristics that the thermal environment of the windward area of the cabin body is severe and the thermal environment of the leeward area of the cabin body is relatively good, the windward area is designed to be the large-thickness heat-proof and heat-insulating layer, the leeward area is designed to be the small-thickness heat-proof and heat-insulating layer, the effect that the temperature of the inner wall is equivalent after heat-proof and heat-insulating is achieved, and the overall mass is reduced; and the refined gradient density design of the inner layer and the outer layer of the heat-proof and heat-insulating layer solves the problem of inharmonious heat matching.
本申请涉及一种舱体热防护结构及飞行器,其相同的第二部分和第一部分连接形成防隔热层;第二部分从下至上依次包括迎风部、过渡部和背风部;在迎风部至背风部的延伸轨迹方向上,迎风部任意两处位置的厚度相等,背风部的任意两处位置的厚度相等,且小于迎风部的厚度;过渡部的厚度自与迎风部的连接处向与背风部的连接处逐渐减小;以上根据舱体迎风区域热环境恶劣、背风区域的热环境相对良好的特点,将迎风区域设计为大厚度防隔热层、背风区域设计为小厚度防隔热层,达到防隔热后内壁温度相当的效果,减小整体质量,防隔热层为整体注塑固化制成,减小气动剥离对整体结构的影响,防隔热层内外层精细化的梯度密度设计解决了热匹配不协调的问题。
Cabin thermal protection structure and aircraft
一种舱体热防护结构及飞行器
2024-07-19
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
Integrated cabin section local thermal protection structure, aircraft and machining method
European Patent Office | 2024
|European Patent Office | 2018
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