Wing beam rigidity configuration method of double-beam wing
A configuration method and wing technology, applied in design optimization/simulation, geometric CAD, etc., can solve problems such as time-consuming and manpower-consuming, low design efficiency, etc., and achieve the goal of avoiding complicated processes, efficient design, and reasonable distribution of front and rear beam stiffness Effect
Active Publication Date: 2020-05-12
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology
[0004] In order to solve the above technical problems, the embodiment of the present invention provides a method for configuring the stiffness of the wing beams of a double-spar wing to solve the stiffness design of the existing front and rear beams of the wing. Ratio, resulting in low efficiency of the entire process design, consuming a lot of time and manpower
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[0034] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined arbitrarily with each other.
[0035] The following specific embodiments provided by the present invention can be combined with each other, and the same or similar concepts or processes may not be repeated in some embodiments.
[0036] figure 1 It is a flow chart of a method for configuring wing spar stiffness of a double-spar wing provided by an embodiment of the present invention. The wing spar stiffness configuration method of the twin-spar wing provided in this embodiment may include the following steps:
[0037] S110, establishing the front and rear beam plate element models, the front and rear beam...
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The embodiment of the invention discloses a wing beam rigidity configuration method for a double-beam wing, and the method comprises the steps of building a front and rear beam plate element model which comprises a plurality of partitioning plate elements; according to the established front and rear beam plate element model, setting a plurality of front and rear beam plate element thickness interval groups, wherein each front and rear beam plate element thickness interval group comprises a front beam plate element thickness interval and a rear beam plate element thickness interval; and applying a load to the front and rear beam plate element model corresponding to each front and rear beam plate element thickness interval group, and performing topological optimization analysis to obtain a thickness distribution result of the front and rear beam block plate elements. According to the embodiment of the invention, the problems of low design efficiency and high time and labor consumption inthe whole process due to the fact that the rigidity ratio of the front and rear beams of the wing needs to be determined after multiple rounds of iteration in the existing rigidity design of the front and rear beams of the wing, are solved.
Description
technical field [0001] The present application relates to but is not limited to the technical field of aircraft design, in particular to a method for configuring the stiffness of the wing spar of a double-spar wing. Background technique [0002] The double-spar wing structure is widely used in aircraft design. The front and rear beams of the double-spar wing structure are the main load-bearing structure. Due to the different load sizes, the stiffness of the front and rear beams is often different. Therefore, it is particularly important to design a reasonable stiffness ratio of the front and rear beams. [0003] In the double-spar wing structure, a reasonable front-to-back beam stiffness ratio can not only optimize the load transfer path, improve the load transfer efficiency, but also reduce the weight of the aircraft. The existing technology is mainly to carry out the digital model design of the front and rear beams of the wing first, and then carry out the strength check a...
Claims
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IPC IPC(8): G06F30/15G06F30/23
CPCY02T90/00
Inventor 李驰侯瑞李明强
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA