Hypersonic aircraft dredging-type rudderpost heat protection structure

Abstract

The invention relates to a hypersonic aircraft dredging-type rudderpost heat protection structure. The rudderpost is designed as a hollow structure, the upper surface of the hollow cavity is positioned above the rudderpost mounting gap and is isolated from the control surface through a heat-insulation layer, and the lower surface is positioned inside the aircraft body and is isolated from the control actuator through a phase-change material or heat sink. The side wall of the hollow cavity is provided with a channel which is parallel to the rudderpost bus, a capillary core is welded with the surface of the channel, the hollow cavity is filled with a working medium, and the heat quantity of aerodynamic heating at the rudderpost gap is dredged to the inner wall of the whole hollow cavity through the phase change and dispersion of the working medium in the hollow cavity. The part of the rudderpost inside the aircraft body and the external surface of the control surface part are respectively provided with a heat-insulation layer.

Description

technical field [0001] The invention relates to a rudder shaft dredging type heat protection structure, which belongs to the technical field of thermal protection of hypersonic aircraft. Background technique [0002] During the flight of a hypersonic vehicle, when the rudder shaft is directly aerodynamically heated, due to the small radius of curvature of the rudder shaft and the gap interference effect at the gap between the rudder surface and the body, the exposed external rudder shaft surface is very small at the gap. There will be a local high heat flow area in the area, causing high temperature "hot spots" to appear locally on the rudder shaft, and the highest temperature may even exceed the allowable temperature of the superalloy material. At the same time, a large local temperature gradient will cause a large The thermal stress poses a great challenge to the high-temperature strength of the rudder shaft, which is especially serious for full-motion rudders. Existing h...

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Problems solved by technology

Existing high-speed aircraft mainly use C / C, C / SiC and other composite materials to prepare the rudder shaft to ensure its heat resistance performance. However, the composite material has oxidation problems, and has high requirements for the preparation process and high cost; the metal material rudder shaft It has good load-bearing characteristics, high damage tolerance, high reliability, and better performance in terms of reusability, but compared with composite materials, the service temperature is lower; through the composite material heat-proof structure and metal The combined structure of the connection structure needs to solve the problem of thermal matching of different materials, and there are certain restrictions on the layout and structural form of the rudder, which makes the rudder structure complicated and affects the reliability

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