Abstract: A landing receiving apparatus for aircraft landing, and a control method thereof are provided, in which the landing receiving apparatus includes a flight management system (FMS) which is inputted with, by a user, destination airport, destination runway, and a receiver mode, a data storage portion which stores approach path data for landing of the aircraft; a receiver portion which calculates aircraft position information by using Global Navigation Satellite System (GLASS) signals and Satellite-Based Augmentation System (SBAS) signals transmitted from an antenna portion, when a receiver mode inputted by a user is a GNSS/SBAS combination mode, and a landing guidance information generating portion which generates landing guidance information by using approach path data corresponding to a destination airport and a destination runway inputted by the user, and the aircraft position information, and transmits the generated landing guidance information to the FMS.

Abstract: Provided is a cryopump enabling the maintaining of a preset temperature during a preset time, even when turned off. The cryopump may comprise: a displacer which adjusts outside temperature by compressing or expanding a refrigerant existing therein; a thermal conduction part which transfers heat outside the cryopump to the refrigerant; and a thermal conduction buffer part which, if the displacer is turned off, absorbs the heat outside that is transferred to the refrigerant, and uses same as energy for changing a phase.

Abstract: The present invention relates to a method for coupling a flight plan and a flight path using ADS-B information, and more specifically to a method for coupling a flight plan and a flight path, wherein a flight data processing unit of an air traffic control system or an arrival management system separately and directly receives ADS-B information such that the received ADS-B information can be used for coupling a flight plan and a flight path of an aircraft.

Abstract: Provided is a method for maintaining a preset air pressure of a low-pressure chamber.

Abstract: A pintle-swirl hybrid injection device according to embodiments of the present disclosure is an injection device which is installed inside a housing that defines a combustion chamber to inject propellant toward the combustion chamber, and it includes a body in tubular shape, being installed in the housing, forming a passage through which the propellant is introduced, and being partially exposed to the combustion chamber, and an injection tip coupled with an end of the body exposed to the combustion chamber to inject the propellant introduced through the passage in a radial direction of the body, and at the same time, to inject the propellant to a direction of a central axis of the body.

Abstract: A docking simulator according to an exemplary embodiment of the present disclosure is a docking simulator capable of mimicking docking between two flight vehicles in a zero gravity environment, the docking simulator including: a passive module which is disposed at a preset position; and an active module which performs docking with the passive module by approaching the passive module while performing a translational motion. According to the present disclosure, the docking simulator capable of performing, on the ground, a logic verification test for rendezvous docking between the two flight vehicles in the space in the zero gravity environment is implemented, and as a result, it is possible to perform more various logic verification tests for rendezvous docking by mimicking the rendezvous docking by using actual objects.

Abstract: Provided is an antenna pattern synthesizing apparatus that synthesizes an antenna pattern by applying quantum-behaved particle swarm optimization (QPSO) algorithm of a satellite synthetic aperture radar (SAR), the antenna pattern synthesizing apparatus including a designer configured to design a mask template based on a performance of an SAR system including an antenna array in which a plurality of antennas are arranged in a multidimensional structure, and a generator configured to calculate a signal amplitude and a signal phase for the antenna array to generate a first antenna pattern using QPSO, and generate the first antenna pattern in the designed mask template based on the calculated signal amplitude and the calculated

Abstract: A tilt-prop aircraft is configured to operate in a vertical take-off and landing (VTOL) mode or a forward flight mode by adjusting a tilt angle of a rotor connected to a wing. The tilt-prop aircraft includes: a blade included in the rotor and configured to rotate to produce lift and thrust; and a tilt center shaft configured to connect the rotor and the wing to each other and adjust the tilt angle of the rotor with respect to a flight plane of the tilt-prop aircraft, wherein when the tilt angle of the rotor is adjusted, a pitch angle of the blade is varied by a power transmission unit mechanically interlocked with the tilt center shaft.

Abstract: Provided is a shock reducing tape spring hinge including fixing members fixed to at least two objects, respectively, a thin shell type tape spring having both end portions that are fastened to the fixing members, respectively, and a shell-shaped damping plate aligned with the tape spring, the damping plate having both end portions that are fastened to the fixing members, respectively. The damping plate and the tape spring may be configured to connect the at least two objects being spaced through the fixing members, and the damping plate may be configured to reduce a deployment shock occurring when the tape spring is deployed.

Abstract: A Global Positioning System (GPS) receiver, a control method of the GPS receiver, and a GPS system are provided, which are capable of reducing an initial position check time using an SBAS signal transmitted from a SBAS satellite. The control method of a GPS receiver includes receiving an SBAS signal from a SBAS satellite and calculating a satellite clock and a satellite position of the GPS receiver using the received SBAS signal. The SBAS signal may contain a difference value between the ephemeris data and the almanac data of the GPS satellite. The difference value between the ephemeris data and the almanac data may include a satellite clock difference value and a satellite position difference value for the GPS satellite. Accordingly, it is possible to acquire the current position and time information more quickly and accurately, by shortening the initial position check time using the difference value between the ephemeris data and the almanac data included in the SBAS signal.

Abstract: An apparatus and method for containing and charging an unmanned VTOL aircraft are disclosed. The apparatus for containing and charging an unmanned VTOL aircraft includes a post, an extended member, a cover, a fastening unit, and a charging unit. The post is placed on a ground. The extended member is connected to the post. The cover is provided on the extended member, and is configured to be opened or closed in order to contain and protect the unmanned VTOL aircraft. The fastening unit is provided in the cover, and is configured to fasten the unmanned VTOL aircraft. The charging unit is provided in the fastening unit, and is configured to charge the unmanned VTOL aircraft.

Abstract: A system and a method for determining a satellite image loss and a computer-readable recording medium therefor are provided. The satellite image loss determination system includes a data receiving unit configured to receive packet data including satellite image data, time information, and a flag value, and angle data of a scan mirror that generates the satellite image data; a data comparing unit configured to compare the angle data received by the data receiving unit with angle data of the scan mirror previously determined in correspondence with the packet data; and an image loss determining unit configured to determine whether a loss has occurred in a satellite image generated from the satellite image data in consideration of a result of comparison of the data comparing unit.

Abstract: A drop testing apparatus is provided. The drop testing apparatus includes a plate connected to an external crane, a magnet holder provided at one end of the plate and fixed to the plate by an electromagnetic force, a counterweight provided at another end of the plate and facing the magnet holder, a dummy structure connected to the magnet holder through a connecting member and having a test specimen installed at one side thereof, a load cell unit provided between the dummy structure and the test specimen to measure impulse of the test specimen, and a controller configured to control the electromagnetic force to be created in the magnet holder and to receive the impulse measured by the load cell unit. When the electromagnetic force is cancelled, the connecting member disengages from the magnet holder, and the dummy structure and the test specimen fall onto the ground.

Abstract: A non-motorized flying unit for observation according to an exemplary embodiment of the present disclosure includes: a body part which is mounted on a launcher, launched in a direction toward a preset target when the launcher operates, and falls, by its own weight, toward the ground from a position of a top dead point (TDP); a propeller unit which is coupled to the body part, and automatically generates rotational force by means of drag force applied to the body part when the body part falls so as to decrease a falling velocity of the body part; and an image capturing unit which is installed on the body part, and obtains image information in respect to the ground when the body part falls.

Abstract: A technical object of the present invention is to provide an unmanned aerial vehicle capable of performing a position movement while maintaining posture stabilization. To this end, the unmanned aerial vehicle of the present invention includes: a main body unit; a plurality of propeller motors of which the rotational speed is adjusted by the main body unit; supports which extend from the main body unit in order to support the plurality of propeller motors; propellers which are axially coupled to the plurality of propeller motors and output thrust; and tilting units which tilt rotating shafts of the propellers with respect to the main body unit.

Abstract: An integrated landing receiver for landing of an aircraft and a controlling method thereof are provided, in which the integrated landing receiver includes a receiver including a plurality of signal information processors that generate landing guidance information respectively corresponding to a plurality of landing support facilities, a collector collecting the landing guidance information respectively generated at the plurality of signal information processors, and an integrator generating integrated landing guidance information by using the landing guidance information collected at the collector and outputting the result. Accordingly, when a plurality of landing support facilities are installed together at an airport, the landing guidance information provided from these landing support facilities are mixed and provided so that shortcomings that each landing supporting facility may have can be advantageously compensated, thus enabling safe and effective provision of the landing guidance information.

Abstract: An apparatus and method for containing and charging an unmanned VTOL aircraft are disclosed. The apparatus for containing and charging an unmanned VTOL aircraft includes a post, an extended member, a cover, a fastening unit, and a charging unit. The post is placed on a ground. The extended member is connected to the post. The cover is provided on the extended member, and is configured to be opened or closed in order to contain and protect the unmanned VTOL aircraft. The fastening unit is provided in the cover, and is configured to fasten the unmanned VTOL aircraft. The charging unit is provided in the fastening unit, and is configured to charge the unmanned VTOL aircraft.

Abstract: As a component of an aerial vehicle, a power management system having an active power control device is provided. The system includes a solar cell converting solar energy into electric energy; a fuel cell provided in the aerial vehicle and converting fuel energy into electric energy by electrochemical reaction; a battery compensating for a lack of electric power supplied from the solar cell and the fuel cell to the aerial vehicle and storing surplus electric power; and an active power control device connecting with all the solar cell, the fuel cell and the battery and combining and distributing electric power generated in the solar cell, the fuel cell and the battery to loads. The system efficiently distributes the power from the respective power sources through the controllable output of the fuel cell in accordance with power required by the aerial vehicle and the solar cell's performance depending on weather.

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 method of controlling a satellite and a computer-readable recording medium are provided. The method is for controlling a satellite moving along an orbit having an inclination angle from the equatorial plane to capture due-north images. The method includes: determining a position of the satellite; calculating a roll angle and a pitch angle of the satellite for pointing a line-of-sight vector of the satellite to a first ground surface being a photographing point; determining a compensation angle by considering effects of the inclination angle and rotation of the Earth so as to capture images in the due north direction of the photographing point; calculating a yaw angle based on the compensation angle; and rotating the satellite according to the calculated roll angle, pitch angle, and yaw angle.