Abstract: There is provided a cooperative driving control method based on a vehicle security status. The cooperative driving method according to an embodiment includes: identifying a security status of a cooperative driving target vehicle; determining a cooperative driving strategy according to the identified security status; and controlling driving according to the determined cooperative driving strategy. Accordingly, cooperative driving may be performed or excluded based on a security status of a target vehicle, so that an accident may be prevented from being caused by cooperative driving with a problematic vehicle, and safety of a driver and an occupant may be guaranteed.

Abstract: Disclosed is a positive electrode material for a lithium secondary battery. The positive electrode material includes a positive electrode active material formed of Li—[Mn—Ti]-M-O-based material including a transition metal (M) to enable reversible intercalation and deintercalation of lithium and molybdenum oxide. The positive electrode active material is coated with the molybdenum oxide to form a coating layer on a surface thereof.

Abstract: The present disclosure relates to a carbazole-based anion exchange material, a preparation method therefor and use thereof, and more particularly, to an anion exchange material used in membranes for water electrolysis, redox flow batteries, fuel cells, carbon dioxide reduction, electrochemical ammonia production and decomposition, electrodialysis (ED), reverse electrodialysis (RED) or capacitive deionization (CDI), a separator comprising the same, a preparation method therefor and use thereof. According to the present disclosure, it is possible to prepare a separation membrane with improved mechanical and chemical stability and durability by remarkably improving the molecular weight together with solubility in solvent by providing the anion exchange material in which all bonds between monomers in the main chain are C—C bonds based on the carbazole-based material with high stability.

Abstract: Provided is a system for monitoring radiation based on a monitoring post, the system implemented to perform aerial radiation measurement for the altitude in the vertical direction based on the location in which monitoring posts are installed, thereby efficiently predicting the movement path and the contaminated area of radioactive materials, and efficiently distinguishing radioactive leakage from the ground surface and radioactive materials that float and move from the outside.

Abstract: Gamma-ray sensing probes operating under the Cerenkov effect measure the burnup of spent nuclear fuel assemblies. The probes include an optical fiber that reacts to gamma rays coming from the spent nuclear fuel assembly and emit light via the Cerenkov effect. A scatterer surrounds the optical fiber to increase the light emitting efficiency of the optical fiber by the Compton electron scattering. A collimator composed of shielding material surrounds the scatterer. The collimator has a slit groove which is open in one direction for directing the gamma rays from the spent fuel assembly to the scatterer.

Abstract: The present invention relates to a fiber-optic sensor system for measuring the relative dose of a therapeutic proton beam by measuring Cerenkov radiation and a method of measuring using the same, and more particularly to a fiber-optic sensor system for precisely and economically measuring a proton beam by measuring the Cerenkov radiation generated from a fiber-optic sensor and a method of measuring using the same. The present invention comprises a proton beam source, a fiber-optic sensor for measuring the Bragg peak of the proton beam and SOBP, an optical detector for measuring the Cerenkov radiation, and a pair of optical fibers connecting the fiber-optic sensor and the optical detector, wherein the fiber-optic sensor being irradiated with a proton beam, the Cerenkov radiation generated in the optical fibers themselves is delivered through the optical detector to an amplifier system, and the resulting signal is transferred to a computer.

Abstract: Provided are a gamma-ray sensing probe using the Cerenkov effect, and a system for identifying the burnup of a spent nuclear fuel assembly using the gamma-ray sensing probes, wherein the system is established using the gamma-ray sensing probe including: an optical fiber reacting to gamma rays coming from the spent nuclear fuel assembly by the Cerenkov effect and emitting light by itself; a scatterer surrounding the optical fiber to increase light emitting efficiency of the optical fiber by the Cerenkov effect; and a collimator configured to surround the scatterer and composed of a shielding material, the collimator having a slit groove which is open in one direction, whereby the burnup of the spent nuclear fuel assembly can be accurately determined.

Abstract: The present disclosure relates to a method for skin improvement using low-dose radiation, and the low-dose radiation can exhibit excellent effects of improving skin wrinkles, improving skin barriers, improving skin thickness, improving skin elasticity, and improving skin moisture through the mechanisms of promoting the growth of normal human dermal fibroblasts, increasing the collagen synthesis within the normal human dermal fibroblast, or reducing the metalloproteinase synthesis within the normal human dermal fibroblasts, thus being effectively used for skin improvement. Additionally, the low-dose radiation of the present disclosure can exhibit excellent hair growth-promoting effect through the mechanisms of promoting the growth of human dermal papilla cells or activating hair follicle cells, thus being useful for the improvement of promoting hair growth.

Abstract: The present invention relates to a fiber-optic sensor system for measuring the relative dose of a therapeutic proton beam by measuring Cerenkov radiation and a method of measuring using the same, and more particularly to a fiber-optic sensor system for precisely and economically measuring a proton beam by measuring the Cerenkov radiation generated from a fiber-optic sensor and a method of measuring using the same. The present invention comprises a proton beam source, a fiber-optic sensor for measuring the Bragg peak of the proton beam and SOBP, an optical detector for measuring the Cerenkov radiation, and a pair of optical fibers connecting the fiber-optic sensor and the optical detector, wherein the fiber-optic sensor being irradiated with a proton beam, the Cerenkov radiation generated in the optical fibers themselves is delivered through the optical detector to an amplifier system, and the resulting signal is transferred to a computer.

Abstract: Disclosed are a wing device for a flight vehicle and a flight vehicle having the same, the wing device including a fixing shaft disposed in a lengthwise direction of a main body of the flight vehicle, a wing rotatably mounted to the fixing shaft so as to be deployed from a state of being laid on an outer circumferential surface of the main body to an erected state, and slidable along the fixing shaft, a fixing groove formed to face the wing in a sliding direction of the wing, and a spring unit configured to apply a first elastic force in an outer circumferential direction of the main body for deployment of the wing, and apply a second elastic force in a lengthwise direction of the main body for inserting the wing into the fixing groove, whereby the wing can be fixed after deployment so as to enhance stability of the flight vehicle.

Abstract: Disclosed are a wing assembly including a wing movably accommodated in a launch tube, and a buffer unit detachably mounted to the wing to come in contact with the launch tube and configured to be separated from the wing after the wing comes out of an inner space of the launch tube, and an apparatus for launching a flying object having the same.

Abstract: Disclosed are a wing deployment apparatus and an apparatus for launching a flying object having the same, the wing deployment apparatus including wings configured to be in a folded state and a deployed state, a driving unit connected to the wings, and configured to drive the wings to be switched from the folded state to the deployed state or vice versa, and a damper cooperative with the operation of the driving unit, and configured to damp a driving force of the driving unit from the start of the wings being moved to the completion of the movement of the wings.

Abstract: The present invention discloses a physical/biochemical sensor using a multisized piezoelectric microcantilever resonator array which enables to quantitatively and simultaneously analyze a mass loading effect and a surface stress change effect and a manufacturing method thereof. In the physical/biochemical sensor using the multisized piezoelectric microcantilever resonator array, a plurality of piezoelectric micro-cantilever resonators having different sizes is arrayed so as to quantitatively and discriminately analyze a surface stress change as well as a sensor surface mass change induced by an adsorbed sensing-target material occurring in a sensing process. Thus, the mass loading effect and the surface stress change effect can be quantitatively and simultaneously analyzed.

Abstract: Disclosed are a wing device for a flight vehicle and a flight vehicle having the same, the wing device including a fixing shaft disposed in a lengthwise direction of a main body of the flight vehicle, a wing rotatably mounted to the fixing shaft so as to be deployed from a state of being laid on an outer circumferential surface of the main body to an erected state, and slidable along the fixing shaft, a fixing groove formed to face the wing in a sliding direction of the wing, and a spring unit configured to apply a first elastic force in an outer circumferential direction of the main body for deployment of the wing, and apply a second elastic force in a lengthwise direction of the main body for inserting the wing into the fixing groove, whereby the wing can be fixed after deployment so as to enhance stability of the flight vehicle.

Abstract: Disclosed are a wing deployment apparatus and an apparatus for launching a flying object having the same, the wing deployment apparatus including wings configured to be in a folded state and a deployed state, a driving unit connected to the wings, and configured to drive the wings to be switched from the folded state to the deployed state or vice versa, and a damper cooperative with the operation of the driving unit, and configured to damp a driving force of the driving unit from the start of the wings being moved to the completion of the movement of the wings.

Abstract: Disclosed are a wing assembly including a wing movably accommodated in a launch tube, and a buffer unit detachably mounted to the wing to come in contact with the launch tube and configured to be separated from the wing after the wing comes out of an inner space of the launch tube, and an apparatus for launching a flying object having the same.

Abstract: The present invention discloses a physical/biochemical sensor using a multisized piezoelectric microcantilever resonator array which enables to quantitatively and simultaneously analyze a mass loading effect and a surface stress change effect and a manufacturing method thereof. In the physical/biochemical sensor using the multisized piezoelectric microcantilever resonator array, a plurality of piezoelectric micro-cantilever resonators having different sizes is arrayed so as to quantitatively and discriminately analyze a surface stress change as well as a sensor surface mass change induced by an adsorbed sensing-target material occurring in a sensing process. Thus, the mass loading effect and the surface stress change effect can be quantitatively and simultaneously analyzed.

Abstract: A missile launch and guidance apparatus of a rail-shoe launching type is disclosed. In a missile adapted to be launched while moving along a rail of a launch tube, a missile launch and guidance apparatus comprises: a bushing inserted into a missile body; a shoe, one end of which is inserted into the bushing, and the other end of which is in contact with the rail; and a spring inserted between the bushing and the shoe so as to provide a separation force to the shoe against the bushing. By separating the shoe from the missile in a lateral direction of the missile launching direction by an elastic force of the spring after launching the missile, the missile launch and guidance apparatus can keep constant the gap between the missile and the launch tube rail irrespective of the behavior of the missile taking place in a launching process, and the drag and weight of the missile launched from the launch tube is reduced to thereby exhibit the maximum flight performance.

Abstract: A missile launch and guidance apparatus of a rail-shoe launching type is disclosed. In a missile adapted to be launched while moving along a rail of a launch tube, a missile launch and guidance apparatus comprises: a bushing inserted into a missile body; a shoe, one end of which is inserted into the bushing, and the other end of which is in contact with the rail; and a spring inserted between the bushing and the shoe so as to provide a separation force to the shoe against the bushing. By separating the shoe from the missile in a lateral direction of the missile launching direction by an elastic force of the spring after launching the missile, the missile launch and guidance apparatus can keep constant the gap between the missile and the launch tube rail irrespective of the behavior of the missile taking place in a launching process, and the drag and weight of the missile launched from the launch tube is reduced to thereby exhibit the maximum flight performance.