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Problems solved by technology
[0004] The embodiment of the present invention provides a method and device for checking the static strength to at least solve the technical problem in the prior art that manually checks the static strength of key parts or under severe working conditions, resulting in incomplete checks
Method used
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Embodiment 1
[0025] According to an embodiment of the present invention, a method embodiment of a static strength calibration method is provided. It should be noted that the steps shown in the flow chart of the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, Also, although a logical order is shown in the flowcharts, in some cases the steps shown or described may be performed in an order different from that shown or described herein.
[0026] figure 1 is a flow chart of a static strength checking method according to an embodiment of the present invention, such as figure 1 As shown, the method includes the following steps:
[0027] Step S102, constructing a component unit corresponding to the structure according to the structure of the aircraft to be checked, wherein the component unit includes one or more component elements of the same category.
[0028] An aircraft is a complex equipment composed of tens of thousands of parts....
Embodiment 2
[0066] According to an embodiment of the present invention, a method embodiment of a static strength checking method is provided, image 3 is a schematic diagram of a static strength device according to an embodiment of the present invention, combined with image 3 As shown, the device includes:
[0067] The construction module 30 is configured to construct a component unit corresponding to the structure according to the structure of the aircraft to be checked, wherein the component unit includes one or more component elements of the same category.
[0068] The acquiring module 32 is configured to acquire attribute parameters and check parameters corresponding to each component element, wherein the check parameters are used to characterize preset indicators that need to be achieved by the aircraft to be checked.
[0069] The determination module 34 is configured to determine the strength margin of each component element according to the determined attribute parameters of each...
Embodiment 3
[0075] According to an embodiment of the present invention, a storage medium is provided, and the storage medium includes a stored program, wherein, when the program is running, the device where the storage medium is located is controlled to execute any one of the static strength checking methods in Embodiment 1.
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Abstract
The invention discloses a static strength checking method and device. The method comprises the following steps of: constructing a constitutional unit corresponding to a structure of a to-be-checked airplane according to the structure, wherein the constitutional unit comprises one or more elements of a same category; obtaining an attribute parameter and a check parameter corresponding to each element, wherein the check parameter is used for representing a preset index that the to-be-checked airplane needs to achieve; and determining a strength margin of each element according to the attribute parameter and check parameter of each element, wherein the strength margin is used for representing whether the element satisfies the preset index or not. According to the method and device, the technical problem that the check is incomprehensive as static strength check is artificially carried out on airplanes at key parts or under severe working conditions in the prior art is solved.
Description
technical field [0001] The invention relates to the field of aircraft static strength check, in particular to a static strength check method and device. Background technique [0002] The static strength check of the aircraft is a necessary work link for the assessment of the aircraft's carrying capacity and structural safety. The aircraft static strength check will involve different failure criteria, different working conditions and structures. If the check tasks are all Considering these three dimensions, the number of analysis checks is the relationship between the multiplication of three quantities, and the number of operating conditions of the aircraft ranges from a few hundred to as many as thousands, and the number of structures (units) is tens of thousands, and so Many calibration tasks are not simple accumulation and repetition, but each analysis task has its specific structural geometric properties / material properties / section properties / connection properties and loa...
Claims
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