Investigating method for impact loading spectrum of aircraft laminated structure and its investigating device

A laminated structure and impact load technology, which is applied in the direction of machine/structural component testing, measuring devices, and mechanical devices, can solve the problems of narrow frequency response range of acceleration sensors, large influence of dynamic characteristics, and many measurement sensors. Achieve the effects of large dynamic range, fast calculation speed and high sensitivity

Inactive Publication Date: 2007-07-18
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, since this method requires many measuring sensors, and the frequency response range of the acceleration sensor is narrow and has a certain mass and volume, it has a great influence on the dynamic characteristics of the structure itself. Obviously, this method is not suitable for Laminated structures on aircraft

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  • Investigating method for impact loading spectrum of aircraft laminated structure and its investigating device

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Embodiment Construction

[0012] Fig. 1 is a schematic diagram of a monitoring device for realizing the monitoring method of the impact load spectrum of an aircraft laminated structure. In Figure 1, 1 is the laminated structure of the aircraft, 2 is the discrete piezoelectric sensor (P1-P6), 3 is the computer, 4 is the data collector, 5 is the charge amplifier; k is the assumed position of the impact load. The discrete piezoelectric sensor 2 pasted or pre-embedded on the surface of the laminated structure 1 of the aircraft is electrically connected to the charge amplifier 5, and the charge amplifier 5 is connected to the computer 3 through the data collector 4; the discrete piezoelectric sensor 2 includes P1, P2, P3, P4, P5, and P6 are six piezoelectric sensing units (generally using PVDF film) pasted on the lower surface of the laminated structure of the aircraft. The electrode surfaces of each piezoelectric sensing unit are insulated from each other, so that when When an impact load acts on the lamin...

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Abstract

The invention discloses aircraft laminate structure striking -load spectrum monitoring method. It includes the following steps: cling or pre-embedding many piezoelectricity sensing elements on the surface of the laminate structure as diverging piezoelectricity board unit; while suffering random striking, data collecting processing integration board collects the dynamic response of the sensor; calculating out structure modality response coordinate; using unconditional stability fine step-by-step integration method to find out modality dynamics differential equation; iteration calculating out striking load time course by modality coordinate. The monitoring device of the invention includes computer, diverging piezoelectricity sensor and is connected with charge amplifier which is connected with computer by data collecting machine. The computer main board expanding groove is inserted data collecting processing integrating board.

Description

technical field [0001] The invention relates to the technical field of aircraft structure damage monitoring, in particular to a method for monitoring the time history of impact loads on the surface of aircraft laminated structures. The invention also relates to a monitoring device implementing the method. Background technique [0002] With the application of laminated structures on engineering components such as aircraft wings, in order to ensure the safe operation of the structure, the problem of delamination damage caused by uncertain impact energy has attracted people's attention, because delamination damage occurs in the material The interior cannot be detected from the surface and has the potential for sudden and catastrophic failure. The impact damage mechanism of composite laminated structures is very complex, and the research in this area is still in the development stage. Experimental research shows that the dynamic response of composite laminated structures is si...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/00G01N19/00G01L5/00G01M19/00G01M99/00
Inventor 周晚林
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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