Strained Molecules: Insights from Force Distribution Analysis

2011 ◽  
pp. 301-310
Author(s):  
Frauke Gräter
2014 ◽  
Vol 10 (1) ◽  
pp. e1003444 ◽  
Author(s):  
Zoltan Palmai ◽  
Christian Seifert ◽  
Frauke Gräter ◽  
Erika Balog

2011 ◽  
Vol 100 (3) ◽  
pp. 310a-311a
Author(s):  
Christian Seifert ◽  
Frauke Graeter

2019 ◽  
Vol 40 (Supplement_1) ◽  
Author(s):  
E Ovcharenko ◽  
K Y U Klyshnikov ◽  
A Kokov ◽  
T Glushkova ◽  
L S Barbarash

Abstract Purpose To evaluate forces distribution, local stresses and deformation of mitral annuloplasty rings in response to annuloplasty. Methods Seguin (St. Jude Medical), Physio I (Edwards LifeScience), Memo 3D (Sorin) and Future SG (Medtronic) MAR of size 30 mm were included in the study. The study group included 4 males patients aged 52–68 years who underwent isolated mitral valve annuloplasty for ischemic mitral regurgitation. All surgeries were performed by the same experienced operator according to the standardized protocol. The mechanical properties of the similar set of MAR were evaluated under uniaxial compression by 15% in the longitudinal and transverse directions on the Testing Machines Z5.0 (Zwick/Roell). Biomechanics was assessed with MSCT. The MAR frame models at the initial state and at the ventricular ejection and atrial systole phases were obtained from DICOM-data using computer tomography Sensation Somatom 64 (Siemens). The models were compared using the innovative numerical algorithm in MatLab (Mathworks) by forming pairs for “systole – diastole”, “initial state – diastole” for all four types of MAR. We compared the mobility of the implanted devices and changes in the physiological saddle shape geometry of the mitral annulus in response to annuloplasty. We performed the quantitative analysis of the movement of each point of the reconstructed model between two states with the subsequent calculation of the required forces based on the finite element analysis. Results Future CG MAR has the greatest longitudinal and transverse stiffness (18.1N and 4.8N, respectively), whereas Memo 3D demonstrates the lowest values (2.3N and 1.5N). The rest two models show intermediate values of 4.2 - 11.3 N to 2.0 - 4.3N. The comparative analysis of MAR before and after implantation shows that Physio demonstrates the most pronounced deviations from normal physiological shape with significant annular compression along the intercommissural diameter by 1.36 mm resulted in a rounded annulus shape. None significant geometrical deformity among the other prosthetic rings. MEMO 3D demonstrates an average deformation by 0.18 mm across all zones, Seguin - 0.42 mm, Future CG - 0.34 mm. The force distribution analysis demonstrated the least forces of MEMO 3D, whereas the largest ones (up to 1.5N) are shown by Future SG, leading to the induction of locally elevated stress in surrounding tissues, potentially triggering the development of paravalvular fistulae. Conclusion Preliminary results demonstrate that the use of flexible rings with initially mobile structure allows preserving the native mitral annulus mobility after annuloplasty and reducing the stress (forces) acting on the surrounding tissues. The presented non-invasive method for estimating the stress of mitral annulus is crucial for advanced clinical practice as it allows further studying of the underlying pathologic mechanisms of developing paravalvular fistulae.


ChemPhysChem ◽  
2013 ◽  
Vol 14 (12) ◽  
pp. 2687-2697 ◽  
Author(s):  
Wenjin Li ◽  
Scott A. Edwards ◽  
Lanyuan Lu ◽  
Tomas Kubar ◽  
Sandeep P. Patil ◽  
...  

2009 ◽  
Vol 96 (10) ◽  
pp. 3997-4005 ◽  
Author(s):  
Senbo Xiao ◽  
Wolfram Stacklies ◽  
Murat Cetinkaya ◽  
Bernd Markert ◽  
Frauke Gräter

2020 ◽  
Vol 18 (2) ◽  
pp. 129
Author(s):  
Angga Septiyana ◽  
Ardian Rizaldi ◽  
Kurnia Hidayat ◽  
Yusuf Giri Wijaya

This research focuses on calculating the force distribution on the wings of the LSU 05-NG aircraft by several numerical methods. Analysis of the force distribution on the wing is important because the wing has a very important role in producing sufficient lift for the aircraft. The numerical methods used to calculate the lift force distribution on the wings are Computational Flow Dynamics (CFD), Lifting Line Theory, Vortex Lattice Method and 3D Panel Method. The numerical methods used will be compared with each other to determine the accuracy and time required to calculate wing lift distribution. Because CFDs produce more accurate estimates, CFD is used as the main comparison for the other three numerical methods. Based on calculations performed, 3D Panel Method has an accuracy that is close to CFD with a shorter time. 3D Panel Method requires 400 while CFD 1210 seconds with results that are not much different. While LLT and VLM have poor accuracy, however, shorter time is needed. Therefore to analyze the distribution of lift force on the wing it is enough to use the 3D Panel Method due to accurate results and shorter computing time.


2014 ◽  
Vol 635-637 ◽  
pp. 772-775
Author(s):  
Zhi Jun Wang ◽  
Jing He ◽  
Wan Yu Liu ◽  
Li Zhan Xian

This study proposes a pre-stressed dual-layer six-axis force sensor with eight limbs, and discusses the structure analysis of the sensor. The number of measuring limbs is determined and the structure characteristics are introduced. Force distribution analysis of the sensor is presented based on the mathematical model and force mapping matrix. The forces on the measuring limbs are decomposed into particular solution and homogeneous solution. The results of the paper are useful for the development and further research of the pre-stressed six-axis force sensor.


2013 ◽  
Vol 6 (1) ◽  
Author(s):  
Bogdan I Costescu ◽  
Frauke Gräter

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