Fatigue load spectrum determination method for external aircraft accessory casing fixing device
A technology of fatigue load spectrum and accessory casing, which is applied in the field of aircraft structure design to achieve the effect of improving calculation accuracy
Active Publication Date: 2020-01-17
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology
[0004]
The purpose of this application is to provide a method for determining the fatigue load spectrum of the external aircraft accessory casing fixing device, so as to solve or alleviate at least one of the problems in the background technology
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[0041] 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.
[0042] Such as figure 2 As shown, the fatigue load spectrum calculation method of the external aircraft accessory receiver fixing device of the present application comprises the following steps:
[0043] S1. According to the load spectrum of the center of gravity of the aircraft, the typical flight subjects and the corresponding overload spectrum of the center of gravity of the aircraft can be determined.
[0044] Flight parameters include overload, angular velocity, angular acceleration, altitude, speed, engine speed, etc. The above flight parameters will affect the load of the external aircraft accessory casing fixing device, such as image 3 As shown, according to the load spectrum of the center of grav...
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The invention relates to a fatigue load spectrum determination method for an external aircraft accessory case fixing device. The fatigue load spectrum determination method comprises the steps of determining a flight subject and an aircraft gravity center overload spectrum and flight parameters under the corresponding flight subject according to an aircraft gravity center load spectrum; determininga ground use subject of the external aircraft accessory casing according to the engine ground test curve; determining an aerial flight load spectrum at the gravity center of the external aircraft accessory case according to the working characteristics of the external aircraft accessory case and the load factor of the external aircraft accessory case under the typical flight subject; determining aground test load spectrum at the gravity center of the external aircraft accessory case according to the working characteristics of the external aircraft accessory case and the load factor of the external aircraft accessory case under the ground use subject; and according to the force transmission characteristic of the external aircraft accessory case installation structure, calculating the aerial flight and ground test fatigue load spectrum of the external aircraft accessory case fixing device through a finite element method. According to the method, the calculation accuracy of the fatigue load spectrum can be improved.
Description
technical field [0001] The application belongs to the technical field of aircraft structure design, and in particular relates to a method for determining a fatigue load spectrum for an external aircraft accessory casing fixing device. Background technique [0002] Such as figure 1 As shown, the external aircraft accessory casing 2 is used for the installation and fixed use of accessories on the aircraft, on which a hydraulic pump 3, a fuel pump 4, a generator 5, and a gas turbine starter 6 are installed. When the engine 1 is started on the ground, the power of the gas turbine starter 6 is transmitted to the engine accessory casing 7 through the flexible rotating shaft 8, and when the engine 1 is working, the engine power is transmitted to the aircraft accessories. The external aircraft accessory casing 2 provides a second power source for the aircraft, and its function is very important. The external aircraft accessory receiver fixing device 10 is used to fix the external ...
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IPC IPC(8): G06F30/23G06F30/15G01M13/00G06F119/14
CPCG01M13/00Y02T90/00
Inventor 刘汉海杨忠会单兴业王海龙李新
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA