High-temperature-resistant laminate based on steel wire gauze pad damping structure

Abstract

The invention discloses a high-temperature-resistant laminate based on a steel wire gauze pad damping structure. The high-temperature-resistant laminate based on the steel wire gauze pad damping structure comprises an outer protective layer (1), a middle heat insulating layer (2) and an inner structural layer (3). The high-temperature-resistant laminate based on the steel wire gauze pad damping structure is mainly characterized by further comprising the steel wire gauze pad damping structure (4), wherein the steel wire gauze pad damping structure (4) is arranged between the protective layer (1) and the structural layer (3) and is nested in the middle of the heat insulating layer (2), the steel wire gauze pad damping structure (4) is provided with an outer cylinder (41), a first steel wire gauze pad (44) and a second steel wire gauze pad (45), wherein the first steel wire gauze pad (44) and the second steel wire gauze pad (45) are horizontally arranged in the outer cylinder (41) with one above the other, and the second steel wire gauze pad (45) is arranged on a base plate (46) with the lower surface being contact with the upper surface of the structural layer (3). The high-temperature-resistant laminate based on the steel wire gauze pad damping structure has the advantages that the heat insulating effect, the vibration isolation effect and the damping effect are remarkable, and the heat stress generated due to the fact that the temperature of a load-carrying structure of an aircraft can be reduced; the structure is simple, maintenance is easy and cost is low.

Description

technical field [0001] The invention belongs to the field of aerospace technology, and relates to a high-temperature-resistant laminated board used in high-speed aircraft in a high-temperature environment, in particular to a high-temperature-resistant laminated board based on a steel wire mesh cushion damping structure. Background technique [0002] When a hypersonic vehicle enters and exits the atmosphere or continues to fly in space, it will bear huge aerodynamic force and aerodynamic heat. The use of a complete thermal structure can avoid the inability to perform the flight tasks it undertakes due to structural ablation or failure, and can also avoid the use of thermal protection to increase the weight of the aircraft. The aerodynamic thermal energy reduces the mechanical properties of the structural material, reduces the acting stress and causes creep; while the mutual restraint between thermal structural components, under the action of thermal load, will generate stre...

AI Technical Summary

Problems solved by technology

The defect of this technology is that its metal heat protection structure only has the function of heat insulation, and other functions such as vibration isolation and vibration reduction have not been considered: when the "outer panel" is heated, it will produce thermal deformation, and the inner layer structure is due to the successful insulation. The corresponding thermal deformation will not occur when the heat is heated. When the "connector" and "fastener" are bent to adapt to the position change of the connection point of the upper and lower layers, the thermal stress of the lower "inner panel" and "body structure" is caused ; Unable to reduce the vibration level; Can not be disassembled separately, which brings inconvenience to maintenance, inspection and replacement, and the cost of the whole life cycle of the structure is high

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