Abstract:
PURPOSE: A device for holding and handling the body panel of a satellite is provided to improve the efficiency and stability of an assembling process since the body panel of the satellite can be easily and stably mounted on a mounting surface. CONSTITUTION: A device for holding and handling the body panel of a satellite comprises a strong back, a lifting tool(20) and a trolley(30). The strong back is coupled to the body panel of the satellite. The lifting tool lifts and moves the strong back using a plurality of lifting strings(22). The trolley enables the strong back moved through the lifting tool to be mounted. The trolley rotates the mounted strong back.
Abstract:
PURPOSE: A deflection compensation system for a satellite is provided to prevent the deflection of a satellite by supporting the satellite on a bogie for rotating the satellite. CONSTITUTION: A deflection compensation system for a satellite comprises a main body(310) which has a through hole(311) and is installed on a bogie for rotating a satellite, a screw(312) which is inserted and slid in the through hole, a worm wheel which is formed inside the main body and engaged with the screw, a worm which is formed inside the main body and engaged with the worm wheel, a handle(315) which is connected to the worm to rotate the worm, and a bracket(320) which is installed on the top of the screw and coupled with a satellite.
Abstract:
PURPOSE: A weightlessness offering apparatus for a deployment test of a solar panel is provided to implement a perfect weightless state by allowing a support cable supporting the weight of a solar panel to slide along two axes. CONSTITUTION: A weightlessness offering apparatus for a deployment test of a solar panel comprises a pair of rails(100) which are arranged in parallel, first slide members(200) which are installed in the rails and slid along the rails, a guide rail(300) which connects the first slide members, a second slide member(400), and a support cable(500) which is connected to the second slide member and a solar panel and supports the weight of the solar panel.
Abstract:
An apparatus for supporting a synthetic aperture radar of a satellite is provided to obtain a space for mounting other equipment and satisfy dynamic characteristics and quasi-static conditions. An apparatus for supporting a synthetic aperture radar of a satellite includes support frames(110), upper and lower platforms(120,130), side panels(140), a support bracket(150), and a hinge bracket(160). The support frames are disposed at corners of a hexagonal post. The upper and lower platforms are connected to upper and lower ends of the support frame to form upper and lower surfaces of the support apparatus. The side panels constitutes side surfaces of the hexagonal support apparatus. The support bracket is coupled to a center part of the support frame to fasten the synthetic aperture radar. The hinge bracket is coupled to the support frame to fasten the synthetic aperture radar.
Abstract:
An optical loading device of an observation satellite is provided to effectively absorb thermal load generated in various directions. An optical loading device of an observation satellite includes a coupling unit(500). The coupling unit includes a first coupling part(510), a second coupling part(530), and a blade(550). The first coupling part is coupled to a platform. The second coupling part is coupled to a main body of the observation satellite. The blade connects the first coupling part and the second coupling part. Fastening grooves(510a) are formed in horizontal directions of the first coupling part. Fastening grooves(530a) are formed in vertical directions of the second coupling part. The coupling unit is connected to a main body of the platform.
Abstract:
Provided is a signal processing device. The signal processing device includes an extraction unit for extracting a pilot signal from a received signal; a first prefilter for filtering the pilot signal by assuming the pilot signal as a signal related to an interference-limited environment; a second prefilter for filtering the pilot signal by assuming the pilot signal as a signal related to a noise-limited environment; and a determination unit for determining whether the first prefilter is applied to the received signal or whether the second prefilter is applied to the received signal by comparing output quality indexes of the first prefilter and the second prefilter.
Abstract:
본 발명은 신호 처리 장치 및 방법에 관한 것으로, 이 장치는 센서로 인가되는 물리량을 누적 또는 적분하여 M-비트 디지털 값으로 출력하는 센서로부터 디지털 값을 입력받아 연이은 두 데이터 획득 시간에서의 물리량의 차이가 미리 정해진 범위 내에 있으면 디지털 카운터 증분의 절댓값이 2 M-1 보다 큰 경우 디지털 값의 증분을 센서가 측정한 물리량으로 계산한다.
Abstract:
본 발명은 인공위성의 조립작업용 몸체패널을 용이하게 안전하게 전개하고 고정하기 위한 인공위성 몸체 패널의 전개 및 고정장치에 관한 것으로, 상기 장치는, 상기 몸체패널에 장착되는 스트롱 백; 고정편을 통해서 상기 몸체패널의 일측에 구비된 회전축에 장착되는 프레임; 상기 스트롱 백과 상기 프레임을 연결시켜주되 상기 스트롱 백의 높이 및 위치 간격이 보정될 수 있도록 하는 인터페이스 브라켓; 인공위성의 핸들링 포인트와 상기 프레임의 고정편에 결합되어서 상기 스트롱 백의 회전운동을 발생시키는 회전장치; 상기 고정부에 착설되어서 상기 몸체패널의 전개 이후에 회전 위치를 고정시켜주는 록킹 부재; 및 상기 몸체패널이 전개되었을 때 하향 처짐현상을 방지해주는 처짐방지 지지대를 포함하며, 인공위성 조립과정에서 빈번히 요구되는 몸체패널의 전개 및 장착을 보다 편리하고 안전하게 수행할 수 있게 하는 효과를 제공한다. 인공위성, 몸체패널, 스트롱 백, 핸들링 포인트, 인터페이스 브라켓
Abstract:
PURPOSE: A mechanical ground support device is provided to transport, rotate and move an artificial satellite, to offer convenience and efficiency by performing various works using one structure, and to be structurally stable and simple against the load conditions added differently to an artificial satellite. CONSTITUTION: A mechanical ground support device comprises a movement support unit(110) attached to one side of an artificial satellite(10) and supporting the artificial satellite when moving the artificial satellite using a rope, a transportation support unit(120) supporting the movement support unit and functioning as a base when transporting the artificial satellite fixed to the movement support unit, and a rotation support unit(130) supported to the transportation support unit and attached to the other side of the artificial satellite to rotate the artificial satellite.