Thermochemical destruction of a carbon epoxy composite under multiple pulse loading

1993 ◽  
Vol 29 (1) ◽  
pp. 82-89 ◽  
Author(s):  
A. M. Grishin ◽  
A. D. Parashin ◽  
A. S. Yakimov
Keyword(s):  
Epoxy Composite ◽  
Pulse Loading ◽  
Multiple Pulse ◽  
Thermochemical Destruction

scholarly journals ELECTRON MICROSCOPE STUDIES ON THE ACTIVE ACCUMULATION OF SR++ BY RAT-LIVER MITOCHONDRIA

1966 ◽  
Vol 29 (1) ◽  
pp. 37-61 ◽  
Author(s):  
John W. Greenawalt ◽  
Ernesto Carafoli
Keyword(s):  
Rat Liver ◽  
Liver Mitochondria ◽  
Pulse Loading ◽  
Rat Liver Mitochondria ◽  
Granule Formation ◽  
Thin Sections ◽  
Multiple Pulse ◽  
Dense Granules ◽  
Mineral Deposition

Electron-opaque granules are deposited in isolated rat-liver mitochondria concomitant with the energy-linked accumulation of Sr++ by these organelles. High temperature microincineration (600°C) of thin sections of mitochondria containing different amounts of Sr++ shows that a clear qualitative correlation exists between the number of inorganic residues remaining after incineration and the amount of Sr++ translocated into the mitochondria. By loading the mitochondria with consecutive pulses of small amounts of Sr++ ("multiple-pulse" loading), very early stages of granule formation can be detected; the first detectable deposits are seen closely associated with the cristae. The evidence presented supports the hypothesis that mineral deposition following or during the in vitro accumulation of ions by mitochondria occurs, at least initially, at sites on these membranes and not as nonspecific precipitates in the mitochondrial matrix. The large number of electron-opaque deposits (100 to 200) seen in single thin sections of individual mitochondria having accumulated intermediate levels of Sr++ clearly exceeds the number of normal dense granules in rat-liver mitochondria, indicating that the normal matrix granules per se do not constitute sites essential for deposition. At the highest levels of Sr++ uptake studied in the multiple-pulse loading experiments, needlelike deposits are seen, a result which suggests that the structural form ("crystallinity") of the mineral deposits may be determined by the rate of accumulation.

Distribution of the strength deviations of plastics under multiple pulse loading

1973 ◽  
Vol 7 (3) ◽  
pp. 504-505
Author(s):  
M. L. Bogorad ◽  
P. P. Binder
Keyword(s):  
Pulse Loading ◽  
Multiple Pulse

Analysis of the performance of a phase alternated multiple pulse sequence in spin I = 7/2 zero-field NQR spectroscopy

1997 ◽  
Vol 92 (6) ◽  
pp. 1035-1038 ◽  
Author(s):  
A. RAMAMOORTHY
Keyword(s):  
Pulse Sequence ◽  
Zero Field ◽  
Multiple Pulse

EFFECT OF HOLE-NOTCH ON THE TENSILE AND COMPRESSIVE BEHAVIOR OF CARBON-EPOXY COMPOSITE LAMINATES

2014 ◽  
Vol 5 (4) ◽  
pp. 305-317
Author(s):  
Muhammad-Umar Saeed ◽  
Zhao Feng Chen ◽  
Zhao Hai Chen ◽  
Bin Bin Li ◽  
Mohsin Ali
Keyword(s):  
Composite Laminates ◽  
Epoxy Composite ◽  
Compressive Behavior

Deformation of Aluminum Alloy and Delamination of CF/epoxy Composite by Soft-body Impact with Various Projectile Shapes

2018 ◽  
Vol 17 (0) ◽  
pp. 289-297
Author(s):  
Takehiko UCHIYAMA ◽  
Kazuaki MATSUMOTO ◽  
Takito TOKITA ◽  
Kazuyoshi ARAI
Keyword(s):  
Aluminum Alloy ◽  
Epoxy Composite ◽  
Soft Body

Validation of Numerical Models Used for Designing the Composite Blade for ILX-27 Rotorcraft

2019 ◽  
Vol 2019 (4) ◽  
pp. 23-31
Author(s):  
Jakub Wilk ◽  
Radosław Guzikowski
Keyword(s):  
Epoxy Composite ◽  
Numerical Models ◽  
Experimental Studies ◽  
Strength Analysis ◽  
Laminate Glass ◽  
Composite Blade ◽  
Real Objects ◽  
Validation Procedure ◽  
Research Objects ◽  
Comparison Of The Results

Abstract The paper presents the validation procedure of the model used in the analysis of the composite blade for the rotor of the ILX-27 rotorcraft, designed and manufactured in the Institute of Aviation, by means of numerical analyses and tests of composite elements. Numerical analysis using finite element method and experimental studies of three research objects made of basic materials comprising the blade structure – carbon-epoxy laminate, glass-epoxy composite made of roving and foam filler – were carried out. The elements were in the form of four-point bent beams, and for comparison of the results the deflection arrow values in the middle of the beam and axial deformations on the upper and lower surfaces were selected. The procedure allowed to adjust the discrete model to real objects and to verify and correct the material data used in the strength analysis of the designed blade.

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