Patents Assigned to Korea Aerospace Research Institute
  • Patent number: 12237759
    Abstract: Disclosed are a high-efficiency integrated power circuit with a reduced number of semiconductor elements and a control method thereof. A high-efficiency integrated power circuit of an integrated converter includes an input port, which is a first port, to which power for driving the integrated converter is input, a non-isolated port, which is a second port, for outputting, to outside the high-efficiency integrated power circuit, an allowable amount of power generated when power input through the input port passes through an inductor, and an isolated port, which is a third port, for conducing remaining power excepting power output through the non-isolated port and for maintaining the conducted remaining power inside the high-efficiency integrated power circuit.
    Type: Grant
    Filed: July 21, 2022
    Date of Patent: February 25, 2025
    Assignee: Korea Aerospace Research Institute
    Inventors: Jeong Eon Park, Jung Kyu Han
  • Patent number: 12234005
    Abstract: Provided is a system for controlling an RPM of a propeller and a rotor of a flight vehicle having multiple power units including: a collective pitch angle command generating unit generating a collective pitch angle command upon receiving a thrust control command from a pilot or an automatic controller; a disturbance factor compensating unit for generating an RPM compensation electronic speed control (ESC) command for compensating for an RPM error, and an electronic speed adjustment command generating unit generating a final ESC command upon receiving a collective command input or derived in the process of generating the collective pitch angle command by the collective pitch angle command generating unit and the RPM compensation ESC command generated by the disturbance factor compensating unit. RPMs of motors of a flight vehicle having a plurality of propellers and rotors may be maintained to be the same.
    Type: Grant
    Filed: November 26, 2020
    Date of Patent: February 25, 2025
    Assignee: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventors: Youngshin Kang, Am Cho, Bumjin Park, Seongwook Choi, Sam Ok Koo, Chang Sun Yoo, Yushin Kim
  • Patent number: 12227320
    Abstract: A storage station for unmanned vertical take-off and landing (VTOL) aircrafts includes a storage case (110) for accommodating an unmanned VTOL aircraft therein, a first coupling member (120) having one end pivotably coupled to an inner upper surface of the storage case and the other end protruding out of the storage case by a pivoting operation, and a second coupling member (130) provided at the other end of the first coupling member, in which one end of a main body of the unmanned VTOL aircraft is coupled to the second coupling member, and the second coupling member is rotatable about a rotation axis in a longitudinal direction of the first coupling member, whereby it is possible to provide an advantageous effect of simultaneously storing and charging multiple drones on sides, and it is particularly possible to provide an advantageous effect of charging and storing a large number of drones used in swarm flight technology, which has recently become increasingly useful.
    Type: Grant
    Filed: June 2, 2023
    Date of Patent: February 18, 2025
    Assignee: Korea Aerospace Research Institute
    Inventors: Sang Cherl Lee, Myeong Shin Lee, Jung Hyun Lee, Hee Seob Kim
  • Patent number: 12188849
    Abstract: Provided is a control surface load simulation apparatus including a reaction force providing structure. The control surface load simulation apparatus includes a first support surface, a second support surface apart from the first support surface in a height direction, a control surface located between the first support surface and the second support surface, an actuator connected to the second support surface and configured to apply a certain load to the control surface, and a reaction force providing structure connected to the first support surface and the control surface to be movable relative to the first support surface and the control surface, the reaction force providing structure being configured to apply a reaction force corresponding to the load to the control surface.
    Type: Grant
    Filed: July 8, 2022
    Date of Patent: January 7, 2025
    Assignee: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventor: Jung Jin Lee
  • Patent number: 12179944
    Abstract: The present invention relates to an apparatus and a method for simulating a satellite mission operating state.
    Type: Grant
    Filed: April 4, 2019
    Date of Patent: December 31, 2024
    Assignee: Korea Aerospace Research Institute
    Inventors: Ok Chul Jung, Jae Dong Seong, Dea Won Chung
  • Patent number: 12183983
    Abstract: A method of optimizing driving of an antenna for communication of an artificial satellite, by controlling a rotation angle of the antenna, according to an embodiment of the disclosure, includes: receiving a basic profile indicating a change in a rotation angle of the antenna such that a center line of the antenna points to a ground station in response to movement of the artificial satellite; determining a processing section with reference to points at which a rotation velocity of the antenna, for the basic profile, is zero; and generating an optimization profile that determines the change in the rotation angle of the antenna by configuring the rotation velocity of the antenna, for the processing section, with a preset optimized rotation velocity.
    Type: Grant
    Filed: May 6, 2022
    Date of Patent: December 31, 2024
    Assignee: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventor: Dae Kwan Kim
  • Patent number: 12163541
    Abstract: Provided is a heat exchanger heat transfer enhancement device, and in particular, to a heat exchanger heat transfer enhancement device by allowing a fluid flowing into a heat exchanger to form a uniform flow field. A flow distribution device is disposed at an inlet of a pipe through which a fluid is introduced, and the flow distribution device includes a plurality of holes formed on a circumferential surface and an end portion to distribute the fluid to the center and the periphery. Also, a flange is formed at one end and coupled between the pipe and a diffusion portion. The distributed fluid passes through a heat exchanger, and here, one or more screens are disposed to make a flow field of the fluid more uniform.
    Type: Grant
    Filed: September 29, 2023
    Date of Patent: December 10, 2024
    Assignee: Korea Aerospace Research Institute
    Inventor: Chun Taek Kim
  • Patent number: 12099114
    Abstract: A method according to the present invention comprises the steps of: dividing SAR raw data into one or more sub-aperture data by a predetermined number in an azimuth direction; performing a spectral length extension FFT on the sub-aperture data in the azimuth direction; multiplying the sub-aperture data by a chirp scaling function; performing a range FFT on the sub-aperture data; performing range compression, SRC, and a bulk RCMC on the sub-aperture data; performing an inverse chirp-z transform on the sub-aperture data in a range direction; multiplying the divided sub-aperture data by a predetermined first function; performing an IFFT on the sub-aperture data in the azimuth direction; recombining the sub-aperture data; multiplying the recombined data by a second function and deramping same; performing an azimuth FFT on the recombined data; performing an azimuth IFFT on the recombined data; multiplying the recombined data by a third function and deramping same; performing the azimuth FFT on the recombined data;
    Type: Grant
    Filed: November 14, 2019
    Date of Patent: September 24, 2024
    Assignee: Korea Aerospace Research Institute
    Inventor: Dong Hyun Kim
  • Patent number: 12071261
    Abstract: A drone docking/landing system includes: a docking portion having a shape of any one of a polygonal pyramid, a truncated polygonal pyramid, a cone, and a truncated cone and being capable of docking a drone; and a landing portion mounted at a lower portion of the drone, having a lower portion that is open, into which the docking portion is inserted, and having an empty inner space, wherein the landing portion has a shape of any one of a polygonal pyramid, a truncated polygonal pyramid, a cone, and a truncated cone, wherein the shape corresponds to the shape of the docking portion so that the docking portion is inserted into the landing portion.
    Type: Grant
    Filed: November 21, 2022
    Date of Patent: August 27, 2024
    Assignee: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventor: Sung Yug Kim
  • Publication number: 20240228050
    Abstract: An electric aircraft according to an embodiment of the present invention comprises: a fuselage equipped with a power means, a front spar and a rear spar extending from the fuselage to an end of a wing, and a plurality of ribs extending from the rear spar to the front spar and coupled to the front spar and the rear spar, in which a plurality of solid state batteries are mounted in a plurality of individual spaces partitioned by the front spar, the rear spar, and the plurality of ribs, respectively, and the front spar and the rear spar are used as members for serial connection of the plurality of solid state batteries, and the plurality of ribs are used as members for parallel connection of the plurality of solid state batteries.
    Type: Application
    Filed: August 18, 2022
    Publication date: July 11, 2024
    Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventor: Hyo Jung AHN
  • Patent number: 12025077
    Abstract: The disclosure relates to a combustor including a heat exchange structure and a rocket including the combustor. The combustor according to an embodiment of the disclosure includes: an inner wall; an outer jacket arranged to cover an outer surface of the inner wall; a plurality of first heat exchange channels arranged between the inner wall and the outer jacket and through which a fuel introduced from a fuel tank flows; and a second heat exchange channel arranged between the inner wall and the outer jacket and through which a pressurized gas introduced from a pressurized gas tank flows.
    Type: Grant
    Filed: November 4, 2021
    Date of Patent: July 2, 2024
    Assignee: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventors: Keum-Oh Lee, Byoungjik Lim, Soon-Young Park
  • Publication number: 20240178420
    Abstract: Provided is a pressure control device for a liquid hydrogen tank for a hydrogen fuel cell vehicle that includes a fuel cell, a battery, and a drive motor, wherein the liquid hydrogen tank includes a vacuum chamber, an inner chamber inside the vacuum chamber and storing liquid hydrogen therein, and a multi-layered insulation surrounding the inner chamber. The pressure control device includes a liquid hydrogen pump inside a liquid hydrogen section, an expansion valve located downstream of the liquid hydrogen pump, a heat exchanger located downstream of the expansion valve, a first flow path through which liquid hydrogen supplied from the liquid hydrogen pump passes through the heat exchanger and is sprayed into a gaseous hydrogen section, and a second flow path through which the liquid hydrogen supplied from the liquid hydrogen pump sequentially passes through the expansion valve and the heat exchanger and flows.
    Type: Application
    Filed: October 31, 2023
    Publication date: May 30, 2024
    Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventors: Seungwhan BAEK, Young Suk JUNG, Kwang Kun PARK, I Sang YU, Kie Joo CHO
  • Patent number: 11988174
    Abstract: Provided are an igniter-integrated thrust chamber for a rocket engine using a cryogenic fuel and liquid oxygen and a rocket including the thrust chamber. The thrust chamber includes a combustion chamber and a mixing head assembly, which is disposed at one side of the combustion chamber and is integrated with the combustion chamber.
    Type: Grant
    Filed: October 14, 2021
    Date of Patent: May 21, 2024
    Assignee: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventor: Byoung Jik Lim
  • Publication number: 20240140623
    Abstract: A launch pad system includes a fuel vent port provided in a launch vehicle, a launch pad fuel tank provided outside the launch vehicle to store fuel, a fuel recovery line connecting the fuel vent port and the launch pad fuel tank such that the fuel is transferred therethrough, and a fuel transfer unit provided on the fuel recovery line to transfer the fuel, wherein the fuel may be recovered from the launch vehicle to the launch pad fuel tank.
    Type: Application
    Filed: July 11, 2023
    Publication date: May 2, 2024
    Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventors: Kwang Kun PARK, I Sang YU, Seung Whan BAEK, Young Suk JUNG, Kie Joo CHO
  • Publication number: 20240140630
    Abstract: A storage station for unmanned vertical take-off and landing (VTOL) aircrafts includes a storage case (110) for accommodating an unmanned VTOL aircraft therein, a first coupling member (120) having one end pivotably coupled to an inner upper surface of the storage case and the other end protruding out of the storage case by a pivoting operation, and a second coupling member (130) provided at the other end of the first coupling member, in which one end of a main body of the unmanned VTOL aircraft is coupled to the second coupling member, and the second coupling member is rotatable about a rotation axis in a longitudinal direction of the first coupling member, whereby it is possible to provide an advantageous effect of simultaneously storing and charging multiple drones on sides, and it is particularly possible to provide an advantageous effect of charging and storing a large number of drones used in swarm flight technology, which has recently become increasingly useful.
    Type: Application
    Filed: June 2, 2023
    Publication date: May 2, 2024
    Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventors: Sang Cherl LEE, Myeong Shin LEE, Jung Hyun LEE, Hee Seob KIM
  • Publication number: 20240132223
    Abstract: An electric aircraft according to an embodiment of the present invention comprises: a fuselage equipped with a power means, a front spar and a rear spar extending from the fuselage to an end of a wing, and a plurality of ribs extending from the rear spar to the front spar and coupled to the front spar and the rear spar, in which a plurality of solid state batteries are mounted in a plurality of individual spaces partitioned by the front spar, the rear spar, and the plurality of ribs, respectively, and the front spar and the rear spar are used as members for serial connection of the plurality of solid state batteries, and the plurality of ribs are used as members for parallel connection of the plurality of solid state batteries.
    Type: Application
    Filed: August 17, 2022
    Publication date: April 25, 2024
    Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventor: Hyo Jung AHN
  • Publication number: 20240124136
    Abstract: A rotor hub system includes a rotor rotation axis, a flap hinge connected to the rotor rotation axis and enabling flapping motion of a rotor blade, a lead-lag hinge connected to the flap hinge and enabling lead-lag motion of the rotor blade, a first hub to which one end of the rotor blade is fixed, a rotating pitch control actuator connected to the first hub and rotating the first hub to enable pitching motion of the rotor blade, and a second hub equipped with the rotating pitch control actuator and hinged to the lead-lag hinge.
    Type: Application
    Filed: October 13, 2023
    Publication date: April 18, 2024
    Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventor: Tae Joo KIM
  • Publication number: 20240092484
    Abstract: A tilt prop aircraft is provided, including a first longeron and a second longeron capable of tilting relatively to each other, a tilt actuator disposed on the second longeron, a first power transmission member rotated by the tilt actuator, a second power transmission member fixed to the first longeron and coupled to the first power transmission member to transmit a rotational movement of the first power transmission member by turning 90 degrees in different planes, a crank fixed to the second longeron and extending through a slot in the first longeron and protruding inwardly from the first longeron, and a connecting rod connected to the crank so as to be relatively rotatable to the crank, and connected to the pitch control rod.
    Type: Application
    Filed: August 15, 2023
    Publication date: March 21, 2024
    Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventors: Jun Ho CHO, Myeong Kyu LEE, Seong Wook CHOI
  • Patent number: 11927974
    Abstract: The flow rate control device includes a main plate corresponding to an inner diameter and including a through hole which is formed at the center thereof and through which a fluid flows, a sub-plate corresponding to a size of the through hole, disposed in front of the main plate, and applied with a pressure of the flowing fluid, and an expansion and contraction flow path formed to connect the through hole and a circumference of the sub-plate to each other and expanded and contracted by the pressure applied to the sub-plate. The expansion and contraction flow path includes a plurality of holes which are formed in a side surface thereof and through which the flow flows, and has a cross-sectional area changed by the pressure to control a flow rate.
    Type: Grant
    Filed: November 17, 2021
    Date of Patent: March 12, 2024
    Assignee: Korea Aerospace Research Institute
    Inventors: Kwang Kun Park, Jun Seong Lee, Kee Joo Lee
  • Patent number: 11918781
    Abstract: An infusion flow regulator includes: a main body having an inlet through which fluid is introduced and an outlet through which the fluid is discharged; and a rotary dial rotatably coupled to the main body, with a sealing member interposed therebetween, so as to regulate a flow rate of the fluid, in which the rotary dial includes a regulating flow path having a shape of a recessed groove in cross section with a first width and a first height, and the regulating flow path includes a first region in which the first width is constant and the first height is decreased, and a second region in which both the first width and the first height are decreased. By the aforementioned configuration, the infusion flow regulator for the fluid can accurately regulate the flow rate even in a region where the flow rate of the fluid is very small.
    Type: Grant
    Filed: May 27, 2019
    Date of Patent: March 5, 2024
    Assignee: Korea Aerospace Research Institute
    Inventors: Poo Min Park, Hyung Mo Kim, Tae Choon Park, Young Seok Kang, Jae Sung Huh, Doo Yong Lee