Optimization method of temporary fastener layout for composite wing box pre-attachment stage
A composite material and layout optimization technology, applied in aircraft assembly, chord/longerons, etc., can solve problems such as damage, failure to control wing box flutter amplitude and burr height within the specified range, and inability to obtain optimal configuration, etc.
Active Publication Date: 2022-04-12
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology
[0006] Traditionally, the type and placement of temporary fasteners used in pre-attachment operations has been determined primarily empirically, often suboptimally
For wing boxes of various sizes and structures, traditional empirical methods may cause damage due to excessive assembly stress, or fail to control the flutter amplitude of the wing box and the height of burrs between contact surfaces within the specified range
Method used
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Embodiment
[0024] In the wing box assembly, the assembly method of the upper wall plate and the lower wall plate is basically the same, so this example only performs the pre-connection operation of the upper wall plate. Usually, the process of pre-connection operation is as follows: First, after completing the positioning and clamping of the upper wall plate, gap measurement and gap filling, keep the constraint conditions unchanged, and assemble the initial hole according to the design position in the unshielded area; then dismantle The shape clamps or pressure heads, suction cups, etc. used to compress the wall panels will block part of the clamping device for the hole making operation, and there will be a gap between the upper wall panel and the frame. At this time, use temporary fasteners for pre-connection operations, and fix the upper The relative position of the wallboard and the skeleton makes the upper wallboard and the skeleton completely fit; then make holes, expand holes, and c...
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Abstract
The invention relates to a method for optimizing the layout of temporary fasteners used in the pre-connection stage of a composite material wing box. The method uses various types of temporary fasteners such as through-hole clips and temporary steel structure bolts to make holes for the composite material wing box The pre-connection at the front fixes the relative position of the wallboard and the skeleton, and makes the wallboard and the skeleton fit closely, avoids violent vibration during drilling, and prevents burrs on the contact surface between the wallboard and the skeleton. This method can obtain a better pre-connection scheme within a given interval of the number of temporary fasteners, improve the drilling accuracy and assembly quality, and ensure that the composite material panel does not generate damage.
Description
technical field [0001] The invention relates to a method for optimizing the layout of temporary fasteners used in the pre-connection stage of a composite material wing box, and belongs to the technical field of aircraft assembly. Background technique [0002] Composite materials have the advantages of high specific strength and specific stiffness, strong fatigue and impact resistance, and long service life, and are widely used in aircraft manufacturing. However, unlike metal components, composite material components have high rigidity, brittle matrix, and weak interlayer strength. They are prone to damage due to excessive assembly stress and affect their working life. Therefore, the traditional forced assembly method cannot be used during assembly. Perform stress and damage analysis during fabrication and assembly to avoid component scrapping. [0003] Composite wing boxes usually consist of front beams, rear beams, three wing ribs and upper and lower panels. During assemb...
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Login to View More IPC IPC(8): B64C3/18B64F5/10
CPCB64C3/18B64F5/10
Inventor 黎雪婷安鲁陵岳烜德赵聪周来水卫炜
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS