scholarly journals Numerical Simulation of Projectile Oblique Impact on Microspacecraft Structure

2017 ◽  
Vol 2017 ◽  
pp. 1-9 ◽  
Author(s):  
Zhiyuan Zhang ◽  
Runqiang Chi ◽  
Baojun Pang ◽  
Gongshun Guan
Keyword(s):  
Sandwich Panel ◽  
Incident Angle ◽  
Hypervelocity Impact ◽  
Face Sheet ◽  
Front Face ◽  
Rear Face ◽  
Damage Area ◽  
Honeycomb Sandwich ◽  
Debris Cloud ◽  
Honeycomb Panel

In the present study, the microspacecraft bulkhead was reduced to the double honeycomb panel, and the projectile oblique hypervelocity impact on the double honeycomb panel was simulated. The distribution of the debris cloud and the damage of a honeycomb sandwich panel were investigated when the incident angles were set to be 60°, 45°, and 30°. The results showed that as incident angle decreased, the distribution of debris cloud was increased gradually, while the maximum perforation size of the rear face sheet was firstly increased with the decrease of the incident angle and then decreased. On the other hand, the damage area and the damage degree of the front face sheet of the second honeycomb panel layer were increased with the decrease of the incident angle. Finally, the critical angle of front and rear face sheets of the honeycomb sandwich panel was obtained under oblique hypervelocity impact.

Numerical analysis of face sheet buckling for a CFRP/ Nomex honeycomb sandwich panel subjected to bending loading

2021 ◽  
pp. 114037
Author(s):  
Mae Oiwa ◽  
Toshio Ogasawara ◽  
Hajime Yoshinaga ◽  
Tsuyoshi Oguri ◽  
Takahira Aoki
Keyword(s):  
Numerical Analysis ◽  
Sandwich Panel ◽  
Face Sheet ◽  
Honeycomb Sandwich ◽  
Nomex Honeycomb ◽  
Bending Loading

Dynamic Response of Metallic Y-Frame Core Sandwich Panels Subjected to Air Blast Loading: Numerical Investigation

2019 ◽  
Author(s):  
Ting Liu ◽  
Yuansheng Cheng ◽  
Jun Liu ◽  
Ganchao Chen ◽  
Changhai Chen ◽  
...  
Keyword(s):  
Dynamic Response ◽  
Sandwich Panel ◽  
Sandwich Panels ◽  
Face Sheet ◽  
Front Face ◽  
Sandwich Plates ◽  
Air Blast ◽  
Solid Plate ◽  
Blast Performance ◽  
Air Blast Loading

Abstract In this paper, the dynamic response of metallic Y-frame core sandwich plates subjected to air blast loading was investigated by employing the LS-DYNA software. The blast wave was generated by the directly detonation of TNT explosives. The deformation/failure modes and associated structural response were identified and analyzed in detail. Main attention was paid to explore the effects of face sheet thicknesses and core web thickness on the deformation response of Y-frame core sandwich plates. A comparison on the blast performance were drawn among the Y-frame core sandwich panel, corrugated core sandwich panel and solid plate in equal areal mass. Numerical results revealed that the Y-frame core sandwich panel experienced indent deformation in the front face, strut buckling in the core and large bending deformation in the back face under the stand-off distance of 100 mm. Increasing the face sheets and core web thicknesses could improve the blast performance of Y-frame core sandwich panels. The deflections of face sheets were sensitive to the variation of front face sheet and core thicknesses. Moreover, Y-frame sandwich panel has comparable anti-blast capacity with the corrugated counterparts and exhibits superior blast resistance than the solid plate.

scholarly journals Comparative application analysis and test verification on equivalent modeling theories of honeycomb sandwich panels for satellite solar arrays

2020 ◽  
Vol 29 ◽  
pp. 096369352096312
Author(s):  
Wei Wang ◽  
Haitao Luo ◽  
Jia Fu ◽  
Haochen Wang ◽  
Changshuai Yu ◽  
...  
Keyword(s):  
Sandwich Panel ◽  
Sandwich Panels ◽  
Theory Model ◽  
Solar Array ◽  
Response Analysis ◽  
Frequency Error ◽  
Test Results ◽  
Solar Arrays ◽  
Honeycomb Sandwich ◽  
Honeycomb Panel

Due to the difficulty of direct finite-element modeling for honeycomb sandwich panels, it is more common to apply equivalent modeling theories. It is necessary to compare their equivalent precision and then to determine the method with the best equivalent performance so as to prepare for the application in satellite solar arrays. The first 10 natural frequencies are obtained by analyzing the dynamic characteristics of sandwich panel theory model, honeycomb panel theory model, and equivalent panel theory model. The equivalent errors of different equivalent methods are obtained by comparison with the analysis results of real honeycomb panel model. Then, the sandwich panel theory and the Hoff theory with high precision are used to simulate the solar array panel. The two methods are further verified and compared by simulation and experiment. Finally, the sandwich panel theory with the highest accuracy is selected to simulate the vibration response of the solar array panel based on the above work. By comparing the frequency response analysis results with the test results, it is found that the maximum acceleration response error is within 7%, and the corresponding frequency error of the main direction is within 3%. The comparison between random analysis results and test results shows that the root mean square response errors of acceleration in three directions are within 13.7%. It is proved that the sandwich panel theory has high accuracy in the honeycomb structure. Based on the background of a specific space project, this study innovatively applies the test results to compare several typical equivalent theories of honeycomb sandwich panels so as to get a theory with the highest equivalent precision. The final conclusion has been applied to the design of related space products and proved to be feasible. This provides important reference and basis for the structural design of the satellite.

The Expansion Model of Debris Cloud Induced by Oblique Hypervelocity Impact

2012 ◽  
Vol 13 (3-4) ◽  
Author(s):  
Qing-Ming Zhang ◽  
Y. H. Chen ◽  
F. L. Huang ◽  
Z. Z. Gong
Keyword(s):  
Conservation Law ◽  
Mass Conservation ◽  
Hypervelocity Impact ◽  
Polar Coordinates ◽  
Dynamic Evolution ◽  
Nonlinear Integral Equations ◽  
Simulation Code ◽  
Debris Cloud ◽  
Expansion Model ◽  
Energy Conservation Law

AbstractFor describing the dynamic evolution of debris cloud formed in oblique hypervelocity impact, a model (expressed in polar coordinates) for the shape, the velocity distribution and the mass distribution is developed according to the results of experiments and numerical simulation, and parameters of the Model are identified by nonlinear integral equations which are derived from mass conservation law and energy conservation law. Afterwards, the model has been verified by another simulation code.

Impact Analysis of Honeycomb Core Sandwich Panels

2020 ◽  
Author(s):  
Shah Alam ◽  
Damodar Khanal
Keyword(s):  
Sandwich Panels ◽  
Sheet Thickness ◽  
Composite Panel ◽  
Face Sheet ◽  
Impact Behavior ◽  
Front Face ◽  
Geometrical Parameters ◽  
Honeycomb Core ◽  
Back Face ◽  
The Impact

Abstract The goal of this paper is to analyze the impact behavior among geometrically different sandwich panels shown upon impact velocities. Initially, composite model with aluminum honeycomb core and Kevlar (K29) face sheets is developed in ABAQUS/Explicit and different impact velocities are applied. Keeping other parameters constant, model is simulated with T800S/epoxy face sheets. Residual velocities, energy absorption (%), and maximum deformation depth is calculated for sandwich panel for both models at five different velocities by executing finite element analysis. Once the better material is found for face sheets, process is extended by varying the ratio of front face sheet thickness to back face sheet thickness keeping other geometrical parameters constant to find the better geometry. Also, comparison of impact responses of sandwich composite panel on different ratio of front face sheet thickness to back face sheet thickness is done and validated with other results available in literature.

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