CN214190063U

CN214190063U - Composite material hybrid structure of stealth aircraft

Info

Publication number: CN214190063U
Application number: CN202023282028.9U
Authority: CN
Inventors: 刘豫; 田鼎; 高伟
Original assignee: AVIC First Aircraft Institute
Current assignee: Xian Aircraft Design and Research Institute of AVIC; AVIC First Aircraft Institute
Priority date: 2020-12-29
Filing date: 2020-12-29
Publication date: 2021-09-14
Anticipated expiration: 2030-12-29

Abstract

The utility model belongs to aircraft structural design field, concretely relates to combined material hybrid structure of stealthy aircraft. The method comprises the following steps: the invisible part (3) and the non-invisible part (2), wherein the invisible part (3) and the non-invisible part (2) are both made of composite materials and are formed by splicing. The carbon fiber composite material part of the structural member of the utility model has strong bearing capacity and light weight, and the stealth composite material part meets the stealth performance requirement; the invisible design separation surface does not need to additionally increase the load transmission of parts, and the weight of the structure is reduced on the whole.

Description

Composite material hybrid structure of stealth aircraft

Technical Field

The utility model belongs to aircraft structural design field, concretely relates to combined material hybrid structure of stealthy aircraft.

Background

For an airplane with stealth design requirements, the structural stealth design usually achieves the purpose of improving the stealth performance of the airplane in a mode of combining multiple parts such as structural appearance optimization, stealth coating, stealth materials and the like. Meanwhile, due to the fact that the stealth material and the stealth coating with high density are used in a large area, great structural weight loss can be caused. Stealth materials and non-stealth materials are respectively used on two sides of a stealth design separation surface, a support part is required to be additionally arranged on the separation surface to transfer load, and the weight cost is high.

SUMMERY OF THE UTILITY MODEL

Utility model purpose: the composite material hybrid structure of the stealth aircraft is provided, and the weight of the stealth structure is reduced.

The technical scheme is as follows:

in a first aspect, there is provided a hybrid composite structure for a stealth aircraft, comprising: the invisible part 2 and the non-invisible part 3, wherein the invisible part 2 and the non-invisible part 3 are both made of composite materials and are formed by splicing.

Further, the stealth part 2 and the non-stealth part 3 are spliced and formed through the stealth sub-layer 5 and the non-stealth sub-layer 4.

Further, the stealth sub-layer 5 is composed of a plurality of stealth material single layers, the non-stealth sub-layer 4 is composed of a plurality of non-stealth material single layers, and the thicknesses of the stealth sub-layer 5 and the non-stealth sub-layer 4 are the same.

Further, the length of the splice fault is greater than a predetermined threshold.

Further, the splicing surface of the stealth sublayer 5 and the non-stealth sublayer 4 is in a V shape.

Further, the splicing surfaces of the invisible sublayer 5 and the non-invisible sublayer 4 are step-shaped.

Has the advantages that:

the composite material is spliced to manufacture an integral structural member. The carbon fiber composite material part of the structural member manufactured by the method has strong bearing capacity and light weight, and the stealth composite material part meets the stealth performance requirement; the invisible design separation surface does not need to additionally increase the load transmission of parts, and the weight of the structure is reduced on the whole.

Drawings

Fig. 1 is a schematic diagram of a splicing structure according to an embodiment of the present invention;

fig. 2 is a schematic diagram of a splicing relationship between a non-stealth sub-layer and a stealth sub-layer according to an embodiment of the present invention;

fig. 3 is a schematic diagram of a spliced fault according to an embodiment of the present invention.

Wherein, stealth design parting surface 1, non-stealth part 2, stealth part 3, non-stealth sublayer 4, stealth sublayer 5, and concatenation fault 6.

Detailed Description

1. As shown in fig. 1, the hybrid stealth structure manufactured by the composite manufacturing process comprises a stealth design separation plane 1, a non-stealth portion 2 such as (epoxy/bismaleimide) carbon fibre, and a stealth portion 3 such as (epoxy/bismaleimide) glass/aramid fibre.

2. As shown in fig. 2, the non-stealth part 2 is formed by paving a plurality of non-stealth sub-layers 4 consisting of (epoxy/bismaleimide resin) carbon fiber unidirectional tapes/fabrics; the stealth part 3 is formed by paving and pasting a plurality of stealth sublayers 5 consisting of (epoxy/bismaleimide resin) glass/aramid fiber unidirectional tapes/fabrics. The non-stealth sublayer 4 is connected with the stealth sublayer 5 in a splicing mode.

3. The non-stealth sublayer 4 is formed by paving and pasting 1-3 (epoxy/bismaleimide resin) single-layer carbon fiber unidirectional tapes/fabrics with the thickness of t1, and the stealth sublayer 5 is formed by paving and pasting 1-3 (epoxy/bismaleimide resin) single-layer glass/aramid unidirectional tapes/fabrics with the thickness of t 2. The thickness N · t1 of the non-stealth sublayer 4 should be approximately equal to the thickness M · t2 of the stealth sublayer 5, where N is 1, 2, 3 and M is 1, 2, 3.

4. As shown in fig. 3, the number of the splice fault 6 should be more than 80 times larger than the thickness of the

features

4 and 5 to obtain better mechanical properties.

The utility model discloses with low density carbon-fibre composite and stealthy combined material (aramid fiber, epoxy glass steel etc.) use the stealthy design parting surface of structure as the border, through combined material manufacturing process, adopt two kinds of different combined material concatenations or lapped form, make structure as an organic whole. The carbon fiber composite material part of the structural member manufactured by the method has strong bearing capacity and light weight, and the stealth composite material part meets the stealth performance requirement; the invisible design separation surface does not need to additionally increase the load transmission of parts, and the weight of the structure is reduced on the whole. Meanwhile, a fastener for connecting split structural members is eliminated, and the cost and the weight are further reduced.

The utility model discloses but wide application in various stealthy aircraft structure.

Claims

1. A hybrid composite structure for a stealth aircraft, comprising: the invisible part (3) and the non-invisible part (2), wherein the invisible part (3) and the non-invisible part (2) are both made of composite materials and are formed by splicing.

2. Hybrid structure according to claim 1, characterized in that the stealth (3) and the non-stealth (2) portions are formed by stitching of a stealth sublayer (5) and a non-stealth sublayer (4).

3. The hybrid structure according to claim 2, characterized in that the stealth sublayer (5) consists of several monolayers of stealth material, the non-stealth sublayer (4) consists of several monolayers of non-stealth material, and the thickness of the stealth sublayer (5) and the non-stealth sublayer (4) is the same.

4. Hybrid structure according to claim 3, characterized in that the length of the splice faults (6) is greater than a predetermined threshold.

5. Hybrid structure according to claim 3, characterized in that the splicing faces of the stealth sublayer (5) and the non-stealth sublayer (4) are V-shaped.

6. The hybrid structure according to claim 3, characterized in that the joint surfaces of the stealth sublayer (5) and the non-stealth sublayer (4) are stepped.