Abstract: A composition for a FDM 3D printer is disclosed. The composition contains bioglass and a biocompatible polymer resin. In addition, a FDM 3D printer molded article having a laminated strut structure, in which the composition for the FDM 3D printer is injected into four layers, is disclosed.

Abstract: The present invention relates to a paste-type composition for a fused deposition modeling (FDM) 3D printer comprising: a ceramic powder including CaO and SiO2; and a binder solution, wherein the composition may be injected into the FDM 3D printer in the form of a paste to rapidly manufacture a molded article without a melting process and may precisely implement a variety of geometries to be utilized as a biological replacement for medical use.

Abstract: Disclosed is a scaffold for living donor transplantation, which includes sintered bioglass and a biocompatible polymer and has improved properties using a 3D printer through a fused deposition modeling process.

Abstract: Disclosed is a scaffold for living donor transplantation, which includes sintered bioglass and a biocompatible polymer and has improved properties using a 3D printer through a fused deposition modeling process.

Abstract: A composition for a FDM 3D printer is disclosed. The composition contains bioglass and a biocompatible polymer resin. In addition, a FDM 3D printer molded article having a laminated strut structure, in which the composition for the FDM 3D printer is injected into four layers, is disclosed.

Abstract: Provided is a three-dimensional rigid ball driving system including: a support frame having a polyhedral shape; a rigid ball positioned at the center of an inner portion of the support frame; a plurality of ball bearings installed at corners of inner sides of the support frame, respectively, and contacting a surface of the rigid ball; and a plurality of electromagnets disposed around the ball bearings and generating magnetic fields to rotate the rigid ball; and a controller controlling the electromagnets to control a rotation direction and a rotation speed of the rigid ball.

Abstract: Provided is a three-dimensional rigid ball driving system including: a support frame having a polyhedral shape; a rigid ball positioned at the center of an inner portion of the support frame; a plurality of ball bearings installed at corners of inner sides of the support frame, respectively, and contacting a surface of the rigid ball; and a plurality of electromagnets disposed around the ball bearings and generating magnetic fields to rotate the rigid ball; and a controller controlling the electromagnets to control a rotation direction and a rotation speed of the rigid ball.

Abstract: The present invention relates to a method of measuring the rotating speed of a sphere for controlling the posture of a satellite. The method includes: an accelerometer installing operation in which a pair of accelerometers is installed at each accelerometer coordinate axis, the accelerometers being located in the sphere; an accelerometer coordinate axis alignment operation in which the accelerometer coordinate axes are aligned to allow the accelerometer coordinate axes to be in line with system coordinate axes, respectively; an acceleration measuring operation in which a current is applied to an electromagnet to rotate the sphere and sequentially measure the acceleration; an acceleration calculating operation in which only the acceleration generated by the rotation of the sphere is calculated; and a rotating speed calculating operation in which the rotating speed of the sphere with respect to each coordinate axis is calculated using the acceleration.

Abstract: The present invention relates to a display driving circuit and a display driving system, and more particularly, to a display driving circuit having a half-VDD power supply circuit built therein and a display driving system including the same, in which the display driving circuit is further provided with a half voltage VDD terminal in addition to the highest voltage VDD terminal and the lowest voltage VSS terminal, and the half voltage, which is between the highest voltage and the lowest voltage, is generated and supplied by the half voltage power supply from the inside of the display driving circuit, rather than being supplied from an external power supply.

Abstract: Provided are an attitude control system and method of a spacecraft of an artificial satellite that may enhance a maneuverability and a controllability by simultaneously applying a reaction wheel and a thruster among drive units used to maneuver an attitude of the spacecraft of the artificial satellite. The attitude control system may include: a thruster-based attitude controller which control firing time of thrusters mounted on the spacecraft; and a reaction wheel-based attitude controller controlling driving of a reaction wheel mounted on the spacecraft. The spacecraft may include a plurality of reaction wheels. When a defect occurs in the spacecraft due to a partial malfunction of the reaction wheels, an attitude maneuverability of the spacecraft may be corrected by simultaneously applying the thruster-based attitude controller and the reaction wheel-based attitude controller.

Abstract: Provided are an attitude control system and method of a spacecraft of an artificial satellite that may enhance a maneuverability and a controllability by simultaneously applying a reaction wheel and a thruster among drive units used to maneuver an attitude of the spacecraft of the artificial satellite. The attitude control system may include: a thruster-based attitude controller which control firing time of thrusters mounted on the spacecraft; and a reaction wheel-based attitude controller controlling driving of a reaction wheel mounted on the spacecraft. The spacecraft may include a plurality of reaction wheels. When a defect occurs in the spacecraft due to a partial malfunction of the reaction wheels, an attitude maneuverability of the spacecraft may be corrected by simultaneously applying the thruster-based attitude controller and the reaction wheel-based attitude controller.

Abstract: A reaction wheel momentum management method using a null space vector is provided. In accordance with this method, when any one of at least four reaction wheels used for triaxial control is made unavailable or degraded, a degraded wheel is used as long as possible for improving the mobility of the behavior of a satellite. The method provides momentum management for an N-number of reaction wheels W1, W2, . . .