公开(公告)号：US20190276147A1

公开(公告)日：2019-09-12

申请号：US16348672

申请日：2017-12-05

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Seon Ho LEE

IPC: B64C39/02 ,  B60L53/12 ,  B60L53/31 ,  B60L53/38

Abstract: A drone takeoff and landing system according to an embodiment comprises: a drone including a through-hole; and a landing pad including an extension member which can pass through the through-hole, wherein, when the extension member of the landing pad passes through the through-hole of the drone, an eddy current may occur between the through-hole and the extension member to cause magnetic braking of the drone.

公开(公告)号：US20240067364A1

公开(公告)日：2024-02-29

申请号：US18450037

申请日：2023-08-15

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Seon Ho LEE

IPC: B64G1/24 ,  G05D1/00 ,  G05D1/08 ,  H04N23/60 ,  H04N23/695

CPC classification number: B64G1/244 ,  G05D1/0094 ,  G05D1/08 ,  H04N23/64 ,  H04N23/695

Abstract: Provided are a method and apparatus for ground target precision orientation for satellite image acquisition, in which the method includes: receiving a desired satellite position (P) for imaging from a ground station, and receiving a ground plan imaging time (T) or an algorithm execution time (TA) from the ground station, in which the ground plan imaging time (T) is calculated according to the desired satellite position (P) for imaging at a ground-based orbit propagator, and the algorithm execution time (TA) is set to be earlier than the ground plan imaging time (T) by a predetermined amount of time; and determining, based on a position error (E) calculated by using a difference between the desired satellite position (P) for imaging and the predicted satellite position (Q) output from the satellite-based orbit propagator, a closest satellite position (QC) and a closest satellite time (TC) corresponding to when the satellite is closest to the desired satellite position (P) for imaging, and determining a corrected maneuvering attitude ({right arrow over (e)},θ) for orienting the line-of-sight vector of an image capturing payload of the satellite to a ground target at the closest satellite position (QC).

公开(公告)号：US20160298962A1

公开(公告)日：2016-10-13

申请号：US14777682

申请日：2013-10-25

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Seon Ho LEE

IPC: G01C19/30 ,  B64G1/28 ,  F16F15/30

CPC classification number: G01C19/30 ,  B60G2401/28 ,  B62D37/06 ,  B64C17/06 ,  B64G1/28 ,  B64G1/286 ,  F16F15/30 ,  G01C19/06 ,  G01C19/08 ,  G01C19/16

Abstract: The objective of the present invention is to provide a control moment gyroscope which can be provided in a limited space since the volume thereof can be reduced without change in performance by optimizing the shapes and mounting positions of each component. To this end, the control moment gyroscope of the present invention is a control moment gyroscope for generating torque in the orthogonal directions to both of two shafts which are perpendicularly disposed to each other by rotating the two shafts, and the control moment gyroscope comprises: a gimbal motor formed in a hollow cylinder shape and supplying momentum; spin motor provided inside the gimbal motor and supplying momentum in a perpendicular direction to the momentum of the gimbal motor; and a flywheel provided in the inside of the gimbal motor and supplied with the rotational force of the gimbal motor and the rotational force of the spin motor.

Abstract translation: 本发明的目的是提供一种控制力矩陀螺仪，其可以设置在有限的空间中，因为通过优化每个部件的形状和安装位置可以在不改变性能的情况下减小其体积。 为此，本发明的控制力矩陀螺仪是用于通过旋转两个轴而相互垂直设置的两个轴的正交方向产生扭矩的控制力矩陀螺仪，并且控制力矩陀螺仪包括： 万向电机形成中空圆柱形并提供动量; 旋转电动机设置在万向电机内部，并与垂直于万向电机的动量的方向供给动量; 以及飞轮，其设置在万向马达的内部并被提供有万向马达的旋转力和旋转马达的旋转力。

公开(公告)号：US20180244363A1

公开(公告)日：2018-08-30

申请号：US15752848

申请日：2016-08-26

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Seon Ho LEE

IPC: B64C1/06 ,  B64C39/02 ,  B64C27/08 ,  B64C27/00

CPC classification number: B64C1/063 ,  B64C1/30 ,  B64C27/006 ,  B64C27/08 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

Abstract: A drone having a deployment device, which is configured such that the same can fly both in a folded mode and in a deployed mode. A platform 300 is arranged in the middle of the drone body 400, a deployment device 200 is arranged on the radial outer side of the platform 300, a fixed support table 230 extends outwardly from the radial outer surface of the platform 300, a rotating support table 210 is coupled to an outer free end of the fixed support table 230, and the rotating support table 210 is rotatably coupled to/supported on the outer free end of the fixed support table 230. Multiple propellers 100 are mounted on the radial outer ends of the rotating support table 210, respectively, a landing structure 600 is coupled to the body 400, and a holder 500 is mounted on the landing structure 600.

公开(公告)号：US20180178896A1

公开(公告)日：2018-06-28

申请号：US15579708

申请日：2015-12-09

Applicant: Korea Aerospace Research Institute

Inventor： Seon Ho LEE

IPC: B64C1/30 ,  B64C27/08 ,  B64C39/02

Abstract: The present invention discloses an unfolding propeller unit type unmanned aerial vehicle including a body unit, a plurality of propeller units in which propellers are installed, a locking unit configured to lock the propeller units so that a state in which the propeller units are overlapping on the body unit is maintained, and propeller unit unfolders, each configured to connect each of the propeller units to the body unit, and unfold the propeller unit from the body unit so the propeller units are positioned around the body unit when locking of the locking unit is released.