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11.发明公开公开(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).
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公开(公告)号：US20240067154A1
公开(公告)日：2024-02-29
申请号：US18315756
申请日：2023-05-11
Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
Inventor： Chun Taek KIM
CPC classification number: B60W10/08 , B60W10/06 , B60W10/26 , B60W2710/0666
Abstract: Provided are a hybrid engine system capable of protecting an engine from overspeeding when the load of a generator rapidly decreases, and a method of controlling the hybrid engine system.
The hybrid engine system includes: an engine; a generator driven by the engine to output electrical energy; a battery configured to store electrical energy produced by the generator or supply electrical energy together with the generator; and a controller configured to control the engine, wherein the controller includes a torque meter for measuring torque of an output shaft of the engine and a current meter for measuring output current of the generator, and is further configured to change a control mode of the engine when a reduction rate of at least one of the torque and the current is greater than a set value while the engine is operating in a fly mode.-
13.发明公开公开(公告)号：US20240014953A1
公开(公告)日：2024-01-11
申请号：US18255555
申请日：2021-10-01
Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
Inventor： Seokkwon KIM , Sung Wan KIM , Keunsu MA
Abstract: The present invention relates to a method for estimating a bit error probability using an error rate ratio of a frame synchronization word, to lower computational complexity such that the method can be implemented in a relatively simple and economical way at a high computational speed. The method includes the steps of: a) defining error rate ratios of frame synchronization words; b) setting a weighted least squares cost function with weights greater than or equal to 0 for the bit error probability using the error rate ratios of the frame synchronization words set in the step a); c) obtaining an estimated bit error probability value that minimizes the cost function set in the step b); and d) sequentially obtaining the weights so that a mean squared error of the estimated bit error probability value obtained in the step c) becomes small.
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14.发明公开公开(公告)号：US20230412259A1
公开(公告)日：2023-12-21
申请号：US18332977
申请日：2023-06-12
Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
Inventor： Seok-Teak YUN
CPC classification number: H04B7/18543 , H02J7/0048
Abstract: The present disclosure relates to an apparatus and method for estimating a state of charge of a satellite battery in a satellite system. According to the present disclosure, a method of operating an apparatus for estimating a state of charge includes obtaining satellite information indicating the status of the satellite according to a mission plan of the satellite, generating prediction information about a battery state of the satellite in a non-contact duration of the satellite from the satellite information based on a pre-learned artificial neural network, obtaining measurement information about a battery state of the satellite in a contact duration of the satellite; and estimating the state of charge of the battery based on the prediction information and the measurement information.
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公开(公告)号：US20230395343A1
公开(公告)日：2023-12-07
申请号：US18249953
申请日：2021-10-12
Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
Inventor： Hyokjin CHO , Sangkwon JEONG
CPC classification number: H01H37/36 , F28D15/043 , F28D15/0266
Abstract: The present disclosure relates to a heat switch device using a cryogenic loop heat pipe and a method therefor, and more specifically, to a heat switch device using a cryogenic loop heat pipe and a method therefor, wherein the cryogenic loop heat pipe is configured to be operable at a cryogenic temperature, the heat switch device can perform the operation of a heat switch for heat transfer and heat blocking, by using the structure of the cryogenic loop heat pipe, without a separate heat switch, thereby reducing the weight and complexity of a system, compared to a conventional configuration, the heat switch can be operated at a user's desired time, and the heat switch device can be used even in a cryogenic environment, and performs heat exchange by using a gas-liquid phase change, thereby effectively providing high heat transfer and heat blocking effects.
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Patent Agency Ranking
公开(公告)号：US11809203B2
公开(公告)日：2023-11-07
申请号：US16872825
申请日：2020-05-12
Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
Inventor： Youngshin Kang , Am Cho , Seongwook Choi , Yushin Kim , Sung Ho Chang
CPC classification number: G05D1/102 , B64C27/52 , B64C27/82 , G05D1/0858 , B64C2027/8254
Abstract: Provided is a vertical take-off/landing aircraft controlling a tilt angle of a main rotor, based on a vertical posture control signal during low-speed flight, wherein, when an aircraft steering signal including a vertical posture control signal for changing the pitch posture angle of the vertical take-off/landing aircraft by a first pitch posture angle is obtained, a flight controller determines a tilt angle of the main rotor with reference to the first pitch posture angle and generates a tilt angle control signal for the main rotor based on the determined tilt angle.
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公开(公告)号：US20220368245A1
公开(公告)日：2022-11-17
申请号：US17713048
申请日：2022-04-04
Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
Inventor： Jeong Eon PARK , Byoung Hee LEE
Abstract: A power system circuit apparatus is provided, which includes a first transformer having a Y-Y connection structure and configured to receive and transform three-phase AC power and output the transformed result, a first controlled rectifier configured to rectify an output voltage of the first transformer and output the rectified result; a second transformer having a Y-delta connection structure and configured to receive and transform the three-phase AC power and output the transformed result; a second controlled rectifier configured to rectify an output voltage of the second transformer and output the rectified result; and an output unit configured to add the output of the first controlled rectifier and the output of the second controlled rectifier and output a resultant sum. Accordingly, there is an effect of reducing the output current ripple and thus reducing the loss compared to the related method.
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公开(公告)号：US20220263239A1
公开(公告)日：2022-08-18
申请号：US17738338
申请日：2022-05-06
Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
Inventor： Dae Kwan KIM
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.
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公开(公告)号：US20220120242A1
公开(公告)日：2022-04-21
申请号：US17501370
申请日：2021-10-14
Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
Inventor： Byoung Jik LIM
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.
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公开(公告)号：US11230361B2
公开(公告)日：2022-01-25
申请号：US16308607
申请日：2016-11-15
Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
Inventor： Dong Min Kim
Abstract: Provided is a flight vehicle operating method including: mooring a flight vehicle to a mooring unit by a cable; reducing a weight of the flight vehicle, increasing the flotage of the flight vehicle, or increasing the flotage of the flight vehicle while reducing the weight of the flight vehicle, by using a first flotation adjuster; floating the flight vehicle at a suitable altitude in the air; increasing the weight of the flight vehicle, reducing the flotage of the flight vehicle, or reducing the flotage of the flight vehicle while increasing the weight of the flight vehicle, by using a second flotation adjuster or a propelling unit of the flight vehicle; and releasing the connection between the flight vehicle and the mooring unit and withdrawing the cable.
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