Instrument installation structure assembly dynamic envelope interference test and improvement method
A technology for installing structures and instruments, which is applied in the testing of machines/structural components, vibration testing, measuring devices, etc. It can solve problems such as mission failure, low strength and stiffness margin, and affect the normal operation of aircraft, so as to improve accuracy, Reduce dynamic displacement and solve the effect of structural dynamic interference
Pending Publication Date: 2022-03-11
CHINA ACAD OF LAUNCH VEHICLE TECH
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[0002] In the process of aircraft structure design and assembly, due to the dimensional relationship and space constraints, there are more cases of static interference and less dynamic interference. This is mainly because strength and stiffness checks are carried out during the general structural design process. With the development of lightweight aircraft, the strength and stiffness margins are getting lower and lower, and then they experience low-frequency vibration environments during the ascent of the rocket, which may lead to dynamic interference between internal structures, which will have an immeasurable impact on the successful flight of the aircraft
At least it will affect the normal operation of the aircraft, and at the worst it will lead to the failure of the mission
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[0027] In order to make the object, technical solution and advantages of the present invention clearer, the implementation manner of the present invention will be further described in detail below in conjunction with the accompanying drawings.
[0028] A dynamic envelope interference test and improvement method for an instrument installation structure component, comprising the following steps:
[0029] Step (1), determining the instrument installation structure component scheme;
[0030] Step (2), using the hammer excitation method to carry out the modal test of the instrument installation structural components, and determine that the boundary condition is fixed support at the connection position with the aircraft;
[0031] Step (3), carry out the sinusoidal sweep low-frequency vibration test of the instrument installation structural components, the test direction is three orthogonal directions of X, Y, Z; the coordinate system adopts the whole aircraft coordinate system;
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The invention discloses a dynamic envelope interference test and improvement method for an instrument installation structure assembly. The method comprises the following steps: determining a scheme of the instrument installation structure assembly; adopting a hammering excitation method to carry out a modal test on the instrument mounting structure assembly; carrying out a sine scanning low-frequency vibration test on the instrument mounting structure assembly; according to a modal test result and a vibration test result, a frequency sine scanning curve mutation method and a theoretical calculation method are adopted to recognize possible dynamic envelope interference of the instrument installation structure assembly; when the dynamic envelope interference exists in the identification result, a method for improving the first-order frequency of the structure is used for improvement; and verifying the improved instrument installation structure assembly until the instrument installation structure assembly does not have dynamic envelope interference.
Description
technical field [0001] The invention relates to a dynamic envelope interference test and improvement method of an instrument installation structure component, belonging to the field of structural load and mechanical environment of aerospace vehicles. Background technique [0002] In the process of aircraft structure design and assembly, due to the size relationship and space constraints, there are more cases of static interference and less dynamic interference. This is mainly because strength and stiffness checks are carried out during the general structural design process. With the development of lightweight aircraft, the strength and stiffness margins are getting lower and lower, and then they experience low-frequency vibration environments during the ascent of the rocket, which may lead to dynamic interference between internal structures, which will have an immeasurable impact on the successful flight of the aircraft. In the slightest, it will affect the normal operation ...
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IPC IPC(8): G01M7/02
CPCG01M7/025Y02T90/00
Inventor 张家雄张华山陈雅曦周正阳韩金鹏杜志博周晓丽王彬谭珏穆星科罗臻黄喜元满益明曹晓瑞杨勇朱永贵
Owner CHINA ACAD OF LAUNCH VEHICLE TECH