公开(公告)号：US20240369718A1

公开(公告)日：2024-11-07

申请号：US18689014

申请日：2022-10-12

Applicant: Korea Aerospace Research Institute

Inventor： Sung Hyuck IM ,  Kee Joo LEE ,  Jae Sung PARK

IPC: G01S19/25 ,  G01S19/22

Abstract: Disclosed are a positioning system and a positioning method using a low earth orbit satellite. The positioning system using a low earth orbit satellite according to the present invention comprises a generation unit for generating, when a communication period with a ground control station is reached, a first telemetry signal including a time value according to a reference time used by a low earth orbit satellite; a confirmation unit for confirming, on the basis of a navigation signal received from a navigation satellite, the GNSS time used as a reference by the navigation satellite; an adjustment unit for adjusting the time value in the first telemetry signal so as to be synchronized with the GNSS time; and a transmission unit for broadcast transmitting a second telemetry signal, after the adjustment, so that a positioning receiver on the ground can determine the position by using the second telemetry signal.

公开(公告)号：US20230003178A1

公开(公告)日：2023-01-05

申请号：US17539846

申请日：2021-12-01

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Keum Oh LEE ,  Byoung Jik LIM ,  Jun Sung LEE ,  Kee Joo LEE ,  Jae Sung PARK

IPC: F02K9/64 ,  F02K9/44 ,  F02K9/97

Abstract: A combustor of a liquid rocket engine includes a nozzle unit including a regenerative cooling channel, in which the nozzle unit includes a fuel manifold outer shell, a combustor inner shell, and a combustor outer shell having a downward channel inlet, and the combustor includes a fuel inlet connected to a nozzle neck of the nozzle unit, a fuel manifold formed between the fuel manifold outer shell and the combustor outer shell, and in which fuel introduced from the fuel inlet flows, a downward channel connected in communication with the fuel manifold through the downward channel inlet, and extending in a downward direction from an upper portion of the combustor, a diverting manifold provided at a distal end of the nozzle unit and connected in communication with the downward channel, and an upward channel connected in communication with the diverting manifold and extending in an upward direction of the combustor.

公开(公告)号：US20250130091A1

公开(公告)日：2025-04-24

申请号：US18490627

申请日：2023-10-19

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Sung Hyuck IM ,  Kee Joo LEE ,  Jae Sung PARK

IPC: G01F23/284 ,  G01F23/80

Abstract: A method and apparatus for measuring a level for calculating a flow of a propellant tank are provided. The method of measuring a level for calculating a flow of a propellant tank includes, in response to an instruction to measure a level in a propellant tank storing a liquid fuel, generating propagated power for level measurement at a specified generation intensity inside the propellant tank through a transmission antenna, receiving the propagated power for level measurement passing through the liquid fuel through a reception antenna, calculating a degree of attenuation between the generation intensity and a reception intensity of the propagated power for level measurement, and measuring a height level of the liquid fuel by considering the degree of attenuation.

公开(公告)号：US20220332441A1

公开(公告)日：2022-10-20

申请号：US17555848

申请日：2021-12-20

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Sung Hyuck IM ,  Jun Seong LEE ,  Kee Joo LEE ,  Jae Sung PARK

IPC: B64G1/28 ,  B64G1/00 ,  B64G1/10 ,  B64G1/24

Abstract: An orbit transition apparatus that transitions an orbit of a payload in outer space includes a rotating body, an adapter disposed on a center part of the rotating body for docking a payload, a launch module disposed outside of the rotating body for launching the payload, and a thruster for rotating the rotating body. The launch module may launch the payload to a target orbit.

公开(公告)号：US20220145832A1

公开(公告)日：2022-05-12

申请号：US17516465

申请日：2021-11-01

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Keum Oh LEE ,  Byoung Jik LIM ,  Kee Joo LEE

IPC: F02K9/52 ,  F02K9/95 ,  F02K9/60

Abstract: An injection device for injecting an oxidizer for a liquid rocket includes a housing, a plate disposed inside the housing and having an injection hole to eject an oxidizer, a duct disposed above the plate to guide the oxidizer, and a manifold with one end connected to the injection hole of the plate and the other end connected to the duct, wherein the oxidizer may be distributed to the injection hole at an equal flow rate.