Abstract: A system for extracting a ground route of an aircraft includes an airport surface detector acquiring ground movement information of an aircraft detected in an airport, a mapper acquiring node information of the airport from a database and mapping the ground movement information with the node information, a route detector detecting taxi route information of the aircraft by collecting adjacent node information of a mapped coordinate and erasing redundant node information among collected adjacent node information, a node identifier identifying start node information or end node information of a taxi route by using stand node information of the aircraft, and a final route extractor extracting a final taxi route including an extracted shortest route by dividing the taxi route into a plurality of sub-routes and applying a shortest route algorithm to the divided sub-routes.

Abstract: A flyback converter is provided, which includes a transformer comprising a primary winding and a secondary winding, the transformer for transforming a power inputted from an input power supply and outputting the transformed power, a switching part having one end connected to the primary winding and the other end connected to the input power supply, and an auxiliary circuit including an auxiliary capacitor, and an auxiliary winding coupled to the primary winding. In addition, a clamping diode and a two-series connected switch structure is utilized for the switch stage to relieve the voltage stress of the switch. Accordingly, it is possible to reduce the voltage stress of the switch and also reduce the ripple of the input current which are the causes of EMI.

Abstract: Provided is a method of verifying satellite software using a simulator, the method including receiving memory data of the simulator from the simulator in a first communication mode, the simulator being loaded with the satellite software to be verified; generating a first telemetry frame from the memory data based on a telemetry frame generation rule; and analyzing the first telemetry frame.

Abstract: A communication system for an unmanned aerial vehicle according to one embodiment of the present invention comprises: an onboard communication apparatus mounted on an unmanned aerial vehicle, for communicating by means of a previously configured first band and a previously configured second frequency band; and a ground communication apparatus for communicating with the onboard communication apparatus by means of the previously configured first band and previously configured second frequency band.

Abstract: A communication system for an unmanned aerial vehicle according to one embodiment of the present invention comprises: an onboard communication apparatus, mounted on an unmanned aerial vehicle, for communicating by means of a previously configured frequency band; and a ground communication apparatus for communicating with the onboard communication apparatus by means of the previously configured frequency band.

Abstract: A testing apparatus for Scramjet engine is capable of preventing breakage of liners in a high-pressure and high-temperature environment in which pressure is 10 Mpa or above and temperature is 1800 K or above. To this end, the testing apparatus for Scramjet engine includes a pipe that endures high-pressure environment, a first liner in a tubular shape, being provided within the pipe, and a second liner in a tubular shape, being provided within the pipe, in which an outer circumference of the second liner is overlapped with an inner circumference of a rear end of the first liner.

Abstract: Provided is a method of comparing satellite attitude control performances, the method including generating, by a controller, a satellite task execution command, receiving, by an input and output (I/O) unit, a result of a simulation performed on a satellite attitude control by a satellite attitude control simulator based on the satellite task execution command, and transmitting, by the I/O unit, the satellite task execution command to a satellite based on the result of the simulation.

Abstract: An apparatus for preventing an axial-flow compressor from stalling by employing a casing treatment includes an outer casing having an inner wall with a slot formed to face a rotor blade, an inner casing moveable so as to open the slot in an unstable operating region and close the slot of the outer casing in a stable operating region, and a drive means for moving the inner casing along the axial direction of the outer casing. Thus, the apparatus can be applied not only to a casing treatment structure where the slope of a slot does not vary with the rotational position of the rotor, but also to a casing with a variously shaped slot such as a radial slot or an axial skewed slot.

Abstract: A technical object of the present disclosure is to provide an anemometer for a wind turbine which is capable of precisely measuring a wind velocity and a wind direction. To this end, an anemometer for a wind turbine of the present disclosure is an anemometer for a wind turbine which is used for a wind turbine including a plurality of rotating blades and a hub which is equipped at a rotation center of the plurality of rotating blades and has a nosecone and is equipped in the nosecone.

Abstract: Provided is a deployment test apparatus including a fixing frame configured to fix a first portion of a target object in which the first portion is hingedly coupled to a second portion, a rotation axis module including a rotary shaft and disposed on one side of the fixing frame, a rotary arm radially extending from the rotary shaft in an upper portion of the fixing frame, and a support module connected to the rotary arm to clamp the second portion of the target object to be floated, wherein when deploying the target object, the deployment test apparatus is configured to reduce an external force applied to the target object.

Abstract: Provided are a three-dimensional (3D) ultrasonic anemometer, a 3D wind velocity measuring method, and a wind turbine. The 3D ultrasonic anemometer includes: an ultrasonic sensor including three pairs of ultrasonic transceivers arranged in different directions, wherein the ultrasonic sensor is installed at a rotation body rotating around a rotation axis and rotates around the rotation axis together with the rotation body; a signal processor outputting a 3D sensed wind velocity sensed by the ultrasonic sensor; and a coordinate converter converting the 3D sensed wind velocity into a 3D fixed wind velocity on a fixed coordinate system by using a rotation angle ? of the rotation body.

Abstract: A flight vehicle attitude control system design device includes: a gain calculator calculating a proportional gain and a derivative gain from a system natural frequency and a system damping coefficient; a margin calculator calculating a gain margin and a phase margin from the proportional gain and the derivative gain; a grid generator generating a gain-phase margin grid from a relationship between the proportional gain and the derivative gain and a relationship between the gain margin and the phase margin; and a display unit outputting the gain-phase margin grid on a control gain design region having a gain margin as one of a horizontal coordinate axis and a vertical coordinate axis and a phase margin as the other one of the horizontal coordinate axis and the vertical coordinate axis.

Abstract: A DC-DC converter includes a first transformer connected between a first node and a ground, the first node being located between an input terminal and an output terminal, and the first transformer comprising a first inductor and a second inductor magnetically coupled to each other, a first switch serially connected to the first inductor, between the first node and the ground, a second switch serially connected to the second inductor, between the first node and the ground, a third switch connected between a second node and the output terminal, the second node being located between the second inductor and the second switch, and a fourth switch connected between a third node and the output terminal, the third node being located between the first inductor and the first switch, and the third and fourth switch being controlled in a same manner as the first and second switch, respectively.

Abstract: Provided is a high-pressure gas supplying apparatus that may minimize impact to be exerted on a valve seat in a regulator and may reuse condensate water or gas produced from leaking gas that is gradually discharged to the outside. That is, it is possible to collect and reuse moisture (condensate water) or gas produced by the Joule-Thomson effect from leaking gas that is gradually discharged to the outside by the leaking gas discharge unit.

Abstract: Provided is a flight vehicle operating method including: mooring a flight vehicle to a mooring unit by a cable; reducing a weight of the flight vehicle, increasing the flotage of the flight vehicle, or increasing the flotage of the flight vehicle while reducing the weight of the flight vehicle, by using a first flotation adjuster; floating the flight vehicle at a suitable altitude in the air; increasing the weight of the flight vehicle, reducing the flotage of the flight vehicle, or reducing the flotage of the flight vehicle while increasing the weight of the flight vehicle, by using a second flotation adjuster or a propelling unit of the flight vehicle; and releasing the connection between the flight vehicle and the mooring unit and withdrawing the cable.

Abstract: Provided is a method of verifying satellite software using a simulator, the method including receiving memory data of the simulator from the simulator in a first communication mode, the simulator being loaded with the satellite software to be verified; generating a first telemetry frame from the memory data based on a telemetry frame generation rule; and analyzing the first telemetry frame.

Abstract: Disclosed is a system for determining a protection level. The system includes a receiver configured to receive an error augmentation for a satellite orbit and clock error, an error augmentation for an ionospheric error, an error augmentation for noise and multi-path between a receiver and a satellite, and an error augmentation for a tropospheric error, a first calculator configured to calculate a first adjustment coefficient to be applied to the error augmentation for the satellite orbit and clock error and the error augmentation for the ionospheric error, and a second calculator configured to calculate a protection level by applying the first adjustment coefficient.

Abstract: Provided is a sphere magnetic levitation system having magnetic-aligning devices that magnetically align the position of a sphere levitated by electromagnets according to whether the sphere is levitated, and a method of operating the sphere magnetic levitation system. The sphere magnetic levitation system includes: a sphere; a plurality of electromagnets symmetrically positioned about the sphere and spaced apart from the sphere at equal distances; and a plurality of magnetic-aligning devices provided around the sphere, and coming into contact with the sphere or separated from the sphere by a predetermined distance according to the modes of the system. The system is operated in one mode from among: an idle mode, in which the magnetic-aligning devices are in direct contact with and support the sphere; and an operation mode, in which the magnetic-aligning devices are separated from the sphere and the sphere is levitated and rotated.

Abstract: Provided is a vibration reduction shaft including a cylindrical outer shaft having an inner hollow portion, in which the outer shaft includes: a first member (110) and a second member (120) which are disposed to be spaced apart from each other in a longitudinal direction of the shaft; and a vibration reduction region (150) which is disposed between the first member and the second member, and multiple connecting members (151), which connect the first member and the second member in an axial direction, are disposed to be spaced apart from one another within the vibration reduction region.

Abstract: Provided is a vibration reduction device for a bearing, including: a bearing tube (50) which is spaced apart from an outer race of a bearing at a predetermined interval and surrounds the outer race; and a link (100) which is disposed between the outer race and the bearing tube, in which the link includes an outer race connecting portion (120) which is in contact with the outer race, and a tube connecting portion (130) which is in contact with the bearing tube, such that vibration reduction performance is implemented by the bearing, tube and the link installed at an outer side of the bearing, and as a result, the vibration reduction device may be applied to various fields in which it is necessary to minimize vibration.