1,721,109 research outputs found
A new division algorithm based on lookahead of partial-remainder (LAPR) for high-speed/low-power coding applications
No full textA nem polynomial division algorithm in finite field GF(2(m)) based on the lookahead of partial-remainder (LAPR) is proposed. Since our algorithm is based on partial division on group basis and lookahead technique exploiting the linearity in finite field arithmetic, it is possible to completely eliminate polynomial multiplications leading to highly increased throughput per unit time. The inherent regularity and feedforward nature of our algorithm make it possible to be fully pipelined, When pipelined, its throughput is one quotient and one remainder per clock cycle, regardless of the degree of dividend polynomial, which is orders of magnitude faster than the conventional architecture using linear feedback shift register. An area-efficient sequential architecture based on LAPR is also presented. Although the throughput rate of sequential architecture is lower than that of the pipelined one, it is still higher than that of any division architecture ever reported. Those will be shown to be efficient, regular, and easily expandable, and hence, naturally suitable for very large scale integration implementation. In systems requiring modest speed, the high-speed nature of our proposed architecture can be traded for low-power consumption by reducing clock rate. We verified the general validity of the division algorithm based on LAPR bg mathematical manipulation and simulation. The superiority of our proposed architecture compared with other reported ones is demonstrated,vith regard to its throughput, latency delays, and power
A stabilized covolume method for the Stokes problem
No full textWe present a covolume method for the modified Stokes problem using the simplest approximation spaces, Q(1)-P-0. This scheme turns out the stabilized covolume method for the Stokes problem. We prove that the covolume method in this paper has a unique solution and O(h) convergence order in H-1 semi-norm for the velocity and in L-2 norm the pressure approximants, respectively. We also present numerical results corresponding to our analysis. (C) 2001 Elsevier Science B.V. All rights reserved
Parasitic leiomyoma in the trocar site after laparoscopic myomectomy: A case report
Full text linkBACKGROUND: Laparoscopic myomectomy is increasingly used for resecting gynecological tumors. Leiomyomas require morcellation for retrieval from the peritoneal cavity. However, morcellated fragments may implant on the peritoneal cavity during retrieval. These fragments may receive a new blood supply from an adjacent structure and develop into parasitic leiomyomas. Parasitic leiomyomas can occur spontaneously or iatrogenically; however, trocar-site implantation is an iatrogenic complication of laparoscopic uterine surgery. We describe a parasitic leiomyoma in the trocar-site after laparoscopic myomectomy with power morcellation. CASE SUMMARY: A 50-year-old woman presented with a palpable abdominal mass without significant medical history. The patient had no related symptoms, such as abdominal pain. Computed tomography findings revealed a well-defined contrast-enhancing mass measuring 2.2 cm, and located on the trocar site of the left abdominal wall. She had undergone laparoscopic removal of uterine fibroids with power morcellation six years ago. The differential diagnosis included endometriosis and neurogenic tumors, such as neurofibroma. The radiologic diagnosis was a desmoid tumor, and surgical excision of the mass on the abdominal wall was successfully performed. The patient recovered from the surgery without complications. Histopathological examination revealed that the specimen resected from the trocar site was a uterine leiomyoma. CONCLUSION: Clinicians should consider the risks and benefits of laparoscopic vs laparotomic myomectomy for gynecological tumors. Considerable caution must be exercised for morcellation to avoid excessive tissue fragmentation
Frequency and time domain flutter computations of a wing with oscillating control surface including shock interference effects
No full textIn this study, the nonlinear aeroelastic characteristics of a wing with an oscillating control surface have been examined in transonic and supersonic regimes. The various effects of rotational stiffness on flutter have also been observed. A modified transonic small-disturbance (TSD) theory is used to more effectively analyze the unsteady aerodynamics of a wing with an oscillating control surface. In the flutter analysis, a coupled time integration method (CTIM) and a transient pulse method (TPM) were used to examine the effects of rotational stiffness reduction on the control surface. The present study shows that the severe decrease of flutter speed and the flutter mode transition can be induced by the reduction of rotational stiffness. In particular, it is shown that the aerodynamic effects of control surface oscillation play an important role in this flutter speed reduction. (C) 2004 Elsevier SAS. All rights reserved.This work was sponsored by the Korea Ministry of
Science and Technology. The authors are grateful for the
support as the National Laboratory Program
Endophthalmitis associated with glaucoma shunt intraluminal stent exposure
No full textEndophthalmitis post glaucoma drainage implant (GDI) surgery is rare, often associated with tube or plate exposure. We report a case of endophthalmitis following glaucoma shunt intraluminal stent exposure in a patient who underwent Baerveldt glaucoma implant surgery. Endophthalmitis following manipulation of intraluminal stents is a rare complication of GDIs but potentially vision threatening condition that needs to be carefully screened for and treated immediately. How to cite this article: Kwon HJ, Kerr NM, Ruddle JB, Ang GS. Endophthalmitis associated with Glaucoma Shunt Intraluminal Stent Exposure. J Curr Glaucoma Pract 2016;10(1):36-37
Nonlinear aeroelastic simulation of a full-span aircraft with oscillating control surfaces
No full textIn this paper, the transonic and low-supersonic aeroelastic behavior of the generic fighter model was investigated in the time domain. The simulation of flutter flight test using forced harmonic motion of control surfaces including inertial coupling effects was conducted at the various conditions. The detailed dynamic aeroelastic responses are computed using a coupled time-marching method based on the effective computational structural dynamic and computational fluid dynamics techniques. The nonlinear aerodynamic effects due to an existing shock wave on the lifting surfaces were considered using a transonic small disturbance equation. A modal model obtained by a free vibration analysis was used for the structural model. The relations between the computed flutter boundary and the simulation results of the responses using the harmonic motions of control surfaces at various conditions were investigated.This work was partially supported through funding from the National
Research Laboratory Program and the research project
from Korea Aerospace Industry ~KAI!. The writers would like to
acknowledge their support
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