公开(公告)号：US20210025786A1

公开(公告)日：2021-01-28

申请号：US17042296

申请日：2019-03-28

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Tae Joo KIM

IPC: G01M99/00

Abstract: The present invention provides blade structure testing equipment comprising: a mounting jig to which one end of a blade specimen is mounted; a grip member to which the other end of the blade specimen is coupled; and a wire (W) having one end attached to the grip member to apply a tensile force to the blade specimen in a direction at a certain angle with respect to the ground. Also, the present invention provides a method for testing a blade specimen, the method comprising: a first step of coupling one end of the blade specimen to a mounting jig and the other end of the blade specimen to a grip member; a second step of determining the values of a centrifugal force, a flap moment, and a lag moment that are to be applied to the blade specimen; a third step of determining the magnitude and direction of a tensile force to be applied to the blade specimen, on the basis of the values determined in the second step; and a fourth step of attaching one end of a wire to the grip member and applying a tensile force to the blade specimen by means of the wire at the magnitude and in the direction of the tensile force determined in the third step.

公开(公告)号：US20210009264A1

公开(公告)日：2021-01-14

申请号：US17040896

申请日：2019-04-12

Applicant: Korea Aerospace Research Institute

Inventor： Sung Ho Chang ,  Yu Shin Kim ,  Seong Wook Choi ,  Young Shin Kang ,  Am Cho

IPC: B64C29/00 ,  B64C5/02 ,  B64C5/06 ,  B64C5/10 ,  B64C3/38 ,  B64C13/02 ,  B64D31/02 ,  B64C27/20

Abstract: The flying object according to one embodiment comprises: a main body; a main wing formed on a side surface of the main body; a duct-shaped first propulsion part which is provided outside the main wing and can be tilted; a second propulsion part arranged behind the main body; horizontal tail wings formed on both side surfaces of the second propulsion part; and a control part for controlling the movement of the first propulsion part, second propulsion part, and horizontal tail wings, wherein the control part controls the second propulsion part and the horizontal tail wings according to the tilt angle of the first propulsion part.

公开(公告)号：US20200340243A1

公开(公告)日：2020-10-29

申请号：US16622546

申请日：2017-09-28

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： ILL KYUNG PARK ,  Sung Joon KIM ,  Tae Uk KIM

IPC: E04B1/98 ,  E04H9/02 ,  F16F13/00 ,  F16F15/02

Abstract: The present invention provides a device configured to effectively absorb repeated shock energy such as a vibration shock by using a composite tube, and the present invention has advantageous effects in that the shock energy caused by a tensile or compressive shock load may be effectively absorbed by the composite tube, and the shock energy absorption device may be applied to a building and used as a vibration control device capable of preparing for repeated earthquakes.

公开(公告)号：US10767635B2

公开(公告)日：2020-09-08

申请号：US16315731

申请日：2017-06-01

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Byeong Hee Chang

IPC: F03D17/00 ,  F03D1/00 ,  F03D7/02 ,  G01P5/24 ,  G01P5/02

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.

公开(公告)号：US20200206728A1

公开(公告)日：2020-07-02

申请号：US16814080

申请日：2020-03-10

Applicant: Korea Aerospace Research Institute

Inventor： Hyok Jin CHO ,  Hee Jun SEO ,  Sung Wook PARK ,  Guee Won MOON

IPC: B01L1/02 ,  F04B37/04 ,  B01J20/02 ,  B01J20/04 ,  B01J20/20 ,  G01L13/00

Abstract: Provided is a method of designing a low-pressure chamber that provides a preset air pressure corresponding to a predetermined altitude. The method may include the steps of: calculating a predetermined error range of the preset air pressure, and calculating an amount and types of materials of a getter to be inserted into the low-pressure chamber based on the error range and a total volume of the low-pressure chamber.

公开(公告)号：US10696394B2

公开(公告)日：2020-06-30

申请号：US15740733

申请日：2016-07-28

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Sung Ho Chang

IPC: B64C37/02 ,  B64C27/10 ,  B64C27/52 ,  B64C39/02

Abstract: A first embodiment relates to a shape-reconfigurable drone and, more specifically, to a shape-reconfigurable drone comprising unit module drones having a rectangular-parallelepiped body capable of applying a thrust in every direction, thereby being capable of flying horizontally without rotating the drone and of forming a drone assembly formed by the coupling of the unit module drones, and thus can fly solo or can fly in various shapes.

公开(公告)号：US10661919B2

公开(公告)日：2020-05-26

申请号：US15822901

申请日：2017-11-27

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Jae Wook Kwon ,  Yong Sik Chun ,  Il Young Kim ,  Dong Young Rew ,  Gi Hyuk Choi

IPC: G09B19/16 ,  B64G1/64 ,  B64G7/00 ,  B64G4/00

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.

公开(公告)号：US20190199283A1

公开(公告)日：2019-06-27

申请号：US16191635

申请日：2018-11-15

Applicant: Korea Aerospace Research Institute

Inventor： Shi Hwan OH ,  Hong Youl MOON

IPC: H02S50/10 ,  F24S40/90 ,  G01L5/24 ,  G01M13/02

CPC classification number: H02S50/10 ,  B64G1/222 ,  F24S40/90 ,  F24S2201/00 ,  G01L5/24 ,  G01M13/027

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.

公开(公告)号：US20190173385A1

公开(公告)日：2019-06-06

申请号：US16191568

申请日：2018-11-15

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Jeong Eon Park ,  Nayoung Lee ,  Jae-dong Choi ,  Jin Baek Jang ,  Sang-ryool Lee

IPC: H02M3/158 ,  H02M1/14

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.

公开(公告)号：US20190153981A1

公开(公告)日：2019-05-23

申请号：US16184209

申请日：2018-11-08

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Jongwon CHAE

IPC: F02K9/97

Abstract: The present invention relates to a thruster having a combustion chamber and a nozzle portion using a honeycomb structure, and more particularly, to a thruster having a combustion chamber and a nozzle portion using a honeycomb structure in which a wall reinforcement including honeycomb structures and heat-resistant paints provided in the honeycomb structures are bonded to a wall constituting a combustion chamber portion and a nozzle portion to increase durability and strength against a mechanical load such as vibrations, impact, or the like, due to combustion of a high-temperature and high-speed propellant and a heat-fluid load such as heat transfer and a temperature load, and a thickness of the wall of the existing combustion chamber and nozzle portion may thus be decreased, such that a weight of the thruster may further be decreased and durability of the wall may be increased.