High-intensity high-rigidity light-weight integral machine body structure
A high-rigidity, high-strength technology, applied in the direction of the fuselage frame, chords/longitudinal beams, etc., can solve the problems of long manufacturing cycle, difficult to guarantee the quality of the shape, thick wall panels, etc., to achieve optimal stiffness and strength, and realize Integrity requirements, effect of reducing assembly effort
Inactive Publication Date: 2017-01-11
JIANGXI HONGDU AVIATION IND GRP
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Problems solved by technology
[0002] A large number of fasteners are used to connect the structural skeleton and wall panels of the traditional aircraft fuselage and wings. There are too many parts, the coordination relationship is complicated, the assembly workload is large, and the assembly path problem needs to be considered, and the manufacturing cycle is long; Thin-walled metal structures have problems such as poor rigidity and difficulty in ensuring the quality of the shape; thick aluminum plates are used for machining, and the overall machined metal siding has good shape quality and overall rigidity. Good strength, but due to the machining method, limited by the minimum machining thickness of the machine tool, the thickness of the wall plate is relatively thick, and the material utilization rate in the part manufacturing process is low
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[0019] In order to make the technical means, creative features, goals and effects achieved by the present invention easy to understand, the present invention will be further described below in conjunction with specific illustrations.
[0020] see Figure 1~Figure 2 A high-strength, high-rigidity and light-weight overall body structure, including an outer skin 1, a core material 2, an inner skin 3, a stringer 4 and a frame 5, wherein the outer skin 1, the core material 2 and the inner skin 3 are co-glued The sandwich panel can be connected to form a sandwich panel, which can improve the rigidity of the panel and reduce the structural weight. The sandwich panel can also be separated left and right or up and down according to the actual assembly situation. Co-curing obtains a high-strength, high-rigidity and light-weight overall body structure.
[0021] In this embodiment, beams are used instead of the girders 4 .
[0022] In this embodiment, the surface layer of the sandwich p...
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The invention relates to a high-intensity high-rigidity light-weight integral machine body structure, which comprises a sandwich wall plate, a long purlin and a frame, wherein the sandwich wall plate is formed by an outer skin, a core material and an inner skin through co-bonding; through the sandwich wall plate, the wall plate rigidity can be improved, and the structure weight can be reduced; in addition, the sandwich wall plate can be horizontally separated or vertically separated according to practical assembly conditions; after the single curing forming of the long purlin and the frame, the bonding and co-curing is performed with the sandwich wall plate to obtain the high-intensity high-rigidity light-weight integral machine body structure. The invention provides the fire-new type high-intensity high-rigidity light-weight integral machine body structure for aeronautics and astronautics devices. On the precise of meeting the use function of the conventional machine body structure, the requirements of light weight, good rigidity and good strength of the machine body are met; high anti-impact capability is realized; meanwhile, the integral machine body structure uses stitching / RFI process or bonding co-curing process so as to reduce the mechanical connection; therefore the assembly workload is reduced; further, the structure completeness requirements are met.
Description
technical field [0001] The invention relates to the technical field of aircraft structures, in particular to a high-strength, high-rigidity and light-weight integral airframe structure. Background technique [0002] A large number of fasteners are used to connect the structural skeleton and wall panels of the traditional aircraft fuselage and wings. There are too many parts, the coordination relationship is complicated, the assembly workload is large, and the assembly path problem needs to be considered, and the manufacturing cycle is long; Thin-walled metal structures have problems such as poor rigidity and difficulty in ensuring the quality of the shape; thick aluminum plates are used for machining, and the overall machined metal siding has good shape quality and overall rigidity. The strength is good, but due to the machining method, the thickness of the wall plate is relatively thick due to the limitation of the minimum processing thickness of the machine tool, and the m...
Claims
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Login to View More IPC IPC(8): B64C1/06B64C3/18
CPCB64C1/06B64C3/18
Inventor姜晓春王强付杰斌袁平湘陈龙辉吉先武徐环宇胡定红李伟东张伟李灿山王斌
OwnerJIANGXI HONGDU AVIATION IND GRP