Tool and method for sleeving rigid thermal protection layer on non-closed equal-diameter revolving body cabin section

Abstract

The invention relates to the technical field of thermal protection materials, in particular to a tool and method for sleeving a rigid thermal protection layer on a non-closed equal-diameter revolvingbody cabin section. The tool comprises a bottom plate, a front extension part, a rear extension part, a plurality of stand columns and at least one sliding die; one end of each stand column is perpendicularly connected to the bottom plate; the front extension part and the rear extension part are installed at the front end and the rear end of the cabin section correspondingly; the sliding dies areinstalled on the stand columns, can move in the axial direction of the stand columns and can be adjusted to a certain degree in the radial direction; the overall profile tolerance of the thermal protection layer can be guaranteed within a certain range, an interference area can be avoided, and therefore the cabin body or the thermal protection layer is prevented from being damaged; and in addition, in the process of sleeving the thermal protection layer, the thermal protection layer can be efficiently and accurately connected to the non-closed equal-diameter revolving body cabin section in a sleeving mode without an additional positioning tool, the structure is simple, and operation is convenient. The method uses the tool for auxiliary installation, is easy and convenient to implement andhigh in operability, and suitable for batch production.

Description

technical field [0001] The invention relates to the technical field of heat protection materials, in particular to a tool and a method for a rigid heat protection layer to be sleeved on a non-enclosed equal-diameter revolving cabin section. Background technique [0002] When a hypersonic vehicle cruises at high speed for a long time in the atmosphere, the surface will be subjected to more severe thermal load and airflow erosion. [0003] The heat insulation scheme of the aircraft in the early stage is mainly to prepare heat protection materials in blocks, and then bond them to the surface of the aircraft piece by piece. The problem with this method is that, on the one hand, there will inevitably be gaps at the joints of the heat protection materials, and more heat will be transferred to the interior of the aircraft, which will bring hidden dangers to the normal operation of components; on the other hand, when bonding Each piece of thermal protection material needs to be ali...

AI Technical Summary

Problems solved by technology

The problem with this method is that, on the one hand, there will inevitably be gaps at the joints of the heat protection materials, and more heat will be transferred to the interior of the aircraft, which will bring hidden dangers to the normal operation of components; on the other hand, when bonding Each piece of thermal protection material needs to be aligned and positioned, and has high requirements on the profile of the aircraft, and the assembly process is complex, difficult, and inefficient

Although this method avoids too many joints in the block scheme, there are still some problems: the preparation of the thermal protection layer and the preparation of the cold structure of the cabin cannot be carried out in parallel, and the thermal protection must be carried out after the processing of the cold structure is completed. In addition, when the thermal protection layer is prepared, the cabin section will experience temperature and pressure changes with the glue, and there is a certain risk. Once the cabin section is damaged, it will seriously affect the task progress of the product.

[0006] However, the non-enclosed equal-diameter revolving body section generally has a "C"-shaped cross section, and is generally made of machined or welded metal material. When welding is formed, the contour is difficult to guarantee, and there is a risk of out-of-tolerance, which may even cause The product is damaged, and for the cabin section of the equal-diameter rotary body, it is easy to scrape the glue between the thermal protection layer and the cabin during the socketing. How to efficiently and accurately connect the thermal protection layer to the non-closed equal-diameter rotary cabin section is an urgent problem to be solved

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