A thermal protection system for an aircraft
A technology for aircraft and heat protection, applied in the direction of fuselage insulation, etc., can solve problems such as rectification blocks increasing the weight of the aircraft and affecting the aerodynamic parameters of the aircraft, achieving good heat resistance and reliability, improving anti-ablation performance, and improving heat resistance performance effect
Active Publication Date: 2021-11-30
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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Problems solved by technology
However, the increase of the rectifying block will first increase the weight of the aircraft itself, and secondly, because the rectifying block has a certain volume, it will affect the aerodynamic parameters of the aircraft under high-speed flight to a certain extent
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Embodiment Construction
[0020] Embodiments of the present invention will be described in further detail below in conjunction with the accompanying drawings.
[0021] see figure 1 As shown, the embodiment of the present invention provides a thermal protection system for an aircraft, including an aircraft body 1, the outer wall of the aircraft body 1 is laid with a heat insulation layer 2 and a heat protection layer 3 from the inside to the outside, and the heat protection layer 3 is far away from the heat insulation layer 2 is provided with an air rudder 4 on one side, and the heat-proof layer 3 includes a first heat-proof zone and a second heat-proof zone. The second heat-proof zone is located below the rudder tip of the air rudder 4. Both are the first heat protection zone, and the first heat protection zone and the second heat protection zone are laid with multiple layers of prepreg 30 , and the laying density of the second heat protection zone is greater than that of the first heat protection zone...
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The invention discloses a thermal protection system of an aircraft, and relates to the technical field of aircraft thermal protection. The device comprises an aircraft main body, the outer wall of which is laid with a heat-insulating layer and a heat-proof layer from the inside to the outside, and an air rudder is arranged on the side of the heat-proof layer away from the heat-insulating layer, and the heat-proof layer includes a first A heat protection area and a second heat protection area, the second heat protection area is located below the rudder tip of the air rudder, the remaining area of the heat protection layer is the first heat protection area, the first heat protection area Both the heat protection zone and the second heat protection zone are laid with multiple layers of prepreg, and the laying density of the second heat protection zone is greater than that of the first heat protection zone. The thermal protection system of an aircraft provided by the present invention improves the local anti-ablation performance by increasing the laying density of the second heat protection zone, and avoids additionally adding rectifying blocks in the second heat protection zone to affect the aerodynamic parameters and parameters of the aircraft. The problem of shape.
Description
technical field [0001] The invention relates to the technical field of aircraft thermal protection, in particular to an aircraft thermal protection system. Background technique [0002] In order to adapt to the harsh aerodynamic and thermal environment of aerospace vehicles with long endurance and high Mach number, the thermal protection design of aerospace vehicles is becoming more and more important. It is becoming more and more complex, especially the heat-resistant layer near the tip of the air rudder of the aircraft needs special consideration in the performance of heat protection. There will be a large shock wave interference at the tip, and the aerodynamic thermal environment of the aircraft heat shield here will be worse than that of other parts of the heat shield, so it is necessary to improve the anti-ablation performance of the heat shield here The requirements of the aircraft will be much higher than other parts of the aircraft, so as to ensure that the aircraft...
Claims
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IPC IPC(8): B64C1/40
CPCB64C1/40
Inventor 范开春杨攀胡善刚王辉陈兴峰
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD