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Seiji Kimura,Seiji Ohtori,Sumihisa Orita,Gen Inoue,Yawara Eguchi,Masashi Takaso,Nobuyasu Ochiai,Kazuki Kuniyoshi,Yasuchika Aoki,Tetsuhiro Ishikawa,Masayuki Miyagi,Hiroto Kamoda,Miyako Suzuki,Yoshihiro 연세대학교의과대학 2014 Yonsei medical journal Vol.55 No.2
Purpose: Bupivacaine is commonly used for the treatment of back pain and the diagnosis of its origin. Nonunion is sometimes observed after spinal fusion surgery;however, whether the nonunion causes pain is controversial. In the current study, we aimed to detect painful nonunion by injecting bupivacaine into the disc space of patients with nonunion after anterior lumbar interbody fusion (ALIF) surgery for discogenic low back pain. Materials and Methods: From 52 patients with low back pain, we selected 42 who showed disc degeneration at only one level (L4-L5 or L5-S1) on magnetic resonance imaging and were diagnosed by pain provocation on discography and pain relief by discoblock (the injection of bupivacaine). They underwent ALIF surgery. If the patients showed low back pain and nonunion 2 years after surgery, we injected bupivacaine into the nonuniondisc space. Patients showing pain relief after injection of bupivacaine underwentadditional posterior fixation using pedicle screws. These patients were followed up 2 years after the revision surgery. Results: Of the 42 patient subjects, 7 showed nonunion. Four of them did not show low back pain; whereas 3 showed moderate or severe low back pain. These 3 patients showed pain reductionafter injection of bupivacaine into their nonunion disc space and underwent additional posterior fixation. They showed bony union and pain relief 2 years afterthe revision surgery. Conclusion: Injection of bupivacaine into the nonunion disc space after ALIF surgery for discogenic low back pain is useful for diagnosis of the origin of pain.
Study on Minimum Time Maneuver Problem for High Maneuvering Missile
Seiji Yamaoka,Seiya Ueno 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
the authors have been studying an application of Multidisciplinary Design Optimization (MDO) to the future missiles. For the purpose, a new design procedure on guidance and control system is proposed in this paper. For the future missiles, high maneuvering and high responsiveness are required. Then, the authors have been studying on guidance and control system design of the missile that uses the useful side thruster method for the high maneuvering and high responsiveness in the future missile. The side thruster method has an independent gas generator. The maximum thrust does not depend on dynamic pressure and is enabled even in the low-speed region immediately after launching or the high altitude area. It is expected that this method is useful in high maneuvering and high responsiveness in the future missiles. It is assumed that the side thruster device can change the amplitude of thrust continuously in this paper. In our previous studies, we solved the minimum time problem with the open loop and calculated optimal solution. The optimum thrust is no bang-bang control, but intermediate value is also used. The numerical results verified the usefulness. In this paper, we propose the closed-loop control system which is calculated inputs in real time due to aim toward the guidance and control system of more realistic missiles, verified by simulation.