Segmented molding method of thermal protection layer of combined cabin

Abstract

The invention discloses a segmented molding method of a thermal protection layer of a combined cabin and belongs to a composite material molding method which is used for solving the problem that a thermal protection layer at an opening part easily peels in an existing integral molding mode, so that the bonding and sleeving quality of the thermal protection layer can be ensured. The segmented molding method comprises the steps of segmented molding of the thermal protection layer, trial assembling of the thermal protection layer and bonding and sleeving of the thermal protection layer. According to the invention, a plurality of different modes are adopted for segmented molding of the thermal protection layer of the combined cabin, and the front segment of the thermal protection layer is molded by adopting a winding and sleeving mode; the middle segment of the thermal protection layer comprises a plurality of individual thermal protection sheets, and each thermal protection sheet is molded by adopting a mold pressing mode; the rear segment of the thermal protection layer is molded by adopting a winding and sleeving mode; meanwhile, the bonding and sleeving sequence of each segment of the thermal protection layer is optimized; according to the molded cabin provided by the invention, a product is reliable in quality, the sleeving clearance is controlled within 0.7mm, and the butt clearance is controlled within 0.2mm. By the check of the flight test, the technical difficulty of layering of the thermal protection layer is overcome, and the product sleeving and bonding quality meets the use requirement.

Description

technical field

[0001] The invention belongs to a composite material molding method, in particular to a segmented molding method for a heat-proof layer of a composite cabin section. Background technique

[0002] In order to ensure that the cabin section has a good aerodynamic shape throughout the flight, as well as heat resistance performance, structural strength and rigidity in various operating environments, the cabin section is composed of a heat-resistant layer and a metal shell. At present, the forming method of the heat-proof layer is as follows: one of the methods of winding, molding or layering is used for integral forming, and then the opening is machined. The forming methods of the heat-proof layer are simple and mature; the disadvantage is that when the product opening size is large, the processing allowance is large, the process cycle is long, and the cost is high; when the heat-proof layer is integrally formed by winding or layering, the opening position is heat...

Examples

Embodiment Construction

[0019] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0020] Such as figure 1 As shown, a composite cabin section is a hollow rotating body, and its bulkhead is composed of a metal shell b and a heat-proof layer a. 1. The heat-proof layer 2 in the middle section and the heat-proof layer 3 in the rear section are connected to form.

[0021] Embodiments of the present invention, for figure 1 The segmental forming of the heat-proof layer of the composite cabin shown includes the following steps:

[0022] (A) Heat-proof layer segmentation forming step: according to the structure of the composite cabin shell, the heat-proof layer is divided into a front heat-proof layer, a middle heat-proof layer and a rear heat-proof layer;

[0023] The heat-proof layer in the front section is hollow conical, and its inner hole shape matches the front section of the metal shell. The prepreg cloth of phenolic resin reinforce...

technical field

[0001] The invention belongs to a composite material molding method, in particular to a segmented molding method for a heat-proof layer of a composite cabin section. Background technique

[0002] In order to ensure that the cabin section has a good aerodynamic shape throughout the flight, as well as heat resistance performance, structural strength and rigidity in various operating environments, the cabin section is composed of a heat-resistant layer and a metal shell. At present, the forming method of the heat-proof layer is as follows: one of the methods of winding, molding or layering is used for integral forming, and then the opening is machined. The forming methods of the heat-proof layer are simple and mature; the disadvantage is that when the product opening size is large, the processing allowance is large, the process cycle is long, and the cost is high; when the heat-proof layer is integrally formed by winding or layering, the opening position is heat...

Examples

Embodiment Construction

[0019] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0020] Such as figure 1 As shown, a composite cabin section is a hollow rotating body, and its bulkhead is composed of a metal shell b and a heat-proof layer a. 1. The heat-proof layer 2 in the middle section and the heat-proof layer 3 in the rear section are connected to form.

[0021] Embodiments of the present invention, for figure 1 The segmental forming of the heat-proof layer of the composite cabin shown includes the following steps:

[0022] (A) Heat-proof layer segmentation forming step: according to the structure of the composite cabin shell, the heat-proof layer is divided into a front heat-proof layer, a middle heat-proof layer and a rear heat-proof layer;

[0023] The heat-proof layer in the front section is hollow conical, and its inner hole shape matches the front section of the metal shell. The prepreg cloth of phenolic resin reinforce...

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