Aerodynamic load processing method based on pod cabin structure design
A technology of aerodynamic load and structural design, applied to ground installations, transportation and packaging, aircraft parts, etc., can solve problems such as complex aerodynamic load distribution, inconvenient cabin structural strength design, difficult determination and implementation of static test programs, etc., to achieve The effect of shortening the development cycle, determining and simplifying the implementation
Active Publication Date: 2022-02-22
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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[0002] Aircraft external pods bear aerodynamic loads in three directions, and the distribution of aerodynamic loads in each direction is relatively complicated, which is not convenient for the structural strength design of the cabin, and it is difficult to determine and implement the static test plan
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[0018] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...
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The application discloses an aerodynamic load processing method based on the pod cabin structure design, which includes the following steps: judging whether the load peak point of the aerodynamic load in different working conditions is greater than the first predetermined peak value; Whether the cabin structure at the load peak point of the first predetermined peak value is continuous; leveling the load peak points greater than the first predetermined peak value in the aerodynamic loads of different working conditions; judging whether the load peak points of the aerodynamic loads of different working conditions are is less than the second predetermined peak value; performing linear straightening processing on the load peak points smaller than the second predetermined peak value among the aerodynamic loads of different working conditions. The aerodynamic load processing method based on the structural design of the pod cabin body of the present application can obtain an aerodynamic distributed load that is more convenient for the structural design of the pod cabin body, and can simplify the determination and implementation of the static scheme. Further, it can also The development cycle of the pod structure is greatly shortened.
Description
technical field [0001] The application belongs to the field of aircraft structure design, and in particular relates to an aerodynamic load processing method based on pod cabin structure design. Background technique [0002] Aircraft external pods bear aerodynamic loads in three directions, and the distribution of aerodynamic loads in each direction is relatively complex, which is not convenient for the structural strength design of the cabin, and it is difficult to determine and implement the static test program. Contents of the invention [0003] In order to solve at least one of the above technical problems, the present application provides an aerodynamic load processing method based on the pod cabin structure design. [0004] The application discloses a method for processing aerodynamic loads based on the pod cabin structure design, comprising the following steps: [0005] Step 1. Judging whether the load peak points of aerodynamic loads in different working conditions...
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IPC IPC(8): B64F5/00B64D47/00
CPCB64D47/00B64F5/00
Inventor 杨方
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA