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公开(公告)号：US11897635B2
公开(公告)日：2024-02-13
申请号：US17458537
申请日：2021-08-26
Applicant: Space Engineering University
Inventor： Min Hu , Jiuyang Li , Xuyu Wang , Yongjing Ruan , Feifei Li , Xianjun Pan , Tianyu Sun , Ge Zhang
CPC classification number: B64G1/242 , B64G1/1085 , G05B17/02 , B64G1/247
Abstract: Provided are a method for maintaining Walker constellation formation and a terminal device. The method comprises: determining a first offset amount of each satellite within a simulation time period according to parameters of a Walker constellation; performing first offset on each satellite according to the first offset amount to obtain a Walker constellation after the first offset; determining a second offset amount of each satellite within the simulation time period according to parameters of the Walker constellation after the first offset; and superimposing the first offset amount and the second offset amount, and performing second offset on each satellite so as to maintain the formation of the Walker constellation.
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2.发明申请公开(公告)号：US20210389129A1
公开(公告)日：2021-12-16
申请号：US17346190
申请日：2021-06-11
Applicant: Space Engineering University
Inventor： Min Hu , Xuyu Wang , Qiang Li , Jiuyang Li , Feifei Li , Yulong Zhao , Rui Zhang , Tun Wu
Abstract: Provided is a method and system of evaluating a constellation spare strategy based on a stochastic time Petri net, which is applied in the technical field of constellation operation management. The method comprises: constructing a single satellite STPN model and an orbital plane STPN model, and establishing a navigation constellation STPN model that includes multiple spare strategies according to the single satellite STPN model and the orbital plane STPN model; establishing an availability model according to the number of malfunctioning satellites and the constellation value (CV) in the navigation constellation STPN model, and establishing a cost model according to operating costs of the navigation constellation STPN model; and evaluating the navigation constellation STPN model using the availability model and the cost model, and determining a target spare strategy from the multiple spare strategies according to an evaluation result.
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公开(公告)号：US10274424B2
公开(公告)日：2019-04-30
申请号：US15959179
申请日：2018-04-21
Applicant: Space Engineering University
Inventor： Wei Rao , Guangyu Wang , Yanji Hong , Junling Song
IPC: G01N21/00 , G01N21/39 , G01J3/42 , G01N21/3504
Abstract: The present invention provides a Voigt line shape fitting method, including step 1: Calculate a Gauss line shape function and a Lorentz line shape function, and calculate a Voigt line shape function. Step 2: For determined line shape parameters to be fitted, calculate partial derivatives of the Voigt line shape function with respect to the parameters, convert a partial derivative of the Voigt line shape function with respect to a parameter into a partial derivative of the Gauss line shape function or the Lorentz line shape function with respect to the parameter. Step 3: Substitute the Voigt line shape function and the partial derivative of the Voigt line shape function with respect to the parameter to be fitted, into a least squares algorithm step, perform least squares fitting calculation, and determine whether to terminate the least squares fitting calculation or return to step 1 to perform next iterative calculation.
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公开(公告)号：US11787567B2
公开(公告)日：2023-10-17
申请号：US17363363
申请日：2021-06-30
Applicant: Space Engineering University
Inventor： Min Hu , Jiuyang Li , Qiang Li , Xuyu Wang , Chaoming Yun , Xueyang Zhang , Tianyu Sun , Qinglei Song
Abstract: The disclosure describes a low-orbit satellite deorbit control method and system based on a particle swarm algorithm. The method includes: constructing an objective function according to a position parameter and a perturbation acceleration of each of particles in a particle swarm as well as a preset Lagrangian multiplier and a penalty factor; determining an objective fitness of each particle and a population fitness of the particle swarm based on the objective function, updating the position parameter and the velocity of each particle, and obtaining a population optimal fitness at a maximum number of iterations; updating the Lagrangian multiplier and the penalty factor according to the population optimal fitness, comparing the objective deviation value with a preset convergence condition, and determining an objective population fitness and an objective position parameter according to a comparison result to obtain an objective deorbit mode.
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公开(公告)号：US20220063843A1
公开(公告)日：2022-03-03
申请号：US17458537
申请日：2021-08-26
Applicant: Space Engineering University
Inventor： Min Hu , Jiuyang Li , Xuyu Wang , Yongjing Ruan , Feifei Li , Xianjun Pan , Tianyu Sun , Ge Zhang
Abstract: Provided are a method for maintaining Walker constellation formation and a terminal device. The method comprises: determining a first offset amount of each satellite within a simulation time period according to parameters of a Walker constellation; performing first offset on each satellite according to the first offset amount to obtain a Walker constellation after the first offset; determining a second offset amount of each satellite within the simulation time period according to parameters of the Walker constellation after the first offset; and superimposing the first offset amount and the second offset amount, and performing second offset on each satellite so as to maintain the formation of the Walker constellation.
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Patent Agency Ranking
6.发明申请公开(公告)号：US20180238798A1
公开(公告)日：2018-08-23
申请号：US15959179
申请日：2018-04-21
Applicant: Space Engineering University
Inventor： Wei RAO , Guangyu WANG , Yanji HONG , Junling SONG
IPC: G01N21/39 , G01J3/42 , G01N21/3504
CPC classification number: G01N21/39 , G01J3/42 , G01J2003/423 , G01N21/3504 , G01N2021/399 , G01N2201/0612 , G01N2201/129
Abstract: The present invention provides a Voigt line shape fitting method, including step 1: Calculate a Gauss line shape function and a Lorentz line shape function, and calculate a Voigt line shape function. Step 2: For determined line shape parameters to be fitted, calculate partial derivatives of the Voigt line shape function with respect to the parameters, convert a partial derivative of the Voigt line shape function with respect to a parameter into a partial derivative of the Gauss line shape function or the Lorentz line shape function with respect to the parameter. Step 3: Substitute the Voigt line shape function and the partial derivative of the Voigt line shape function with respect to the parameter to be fitted, into a least squares algorithm step, perform least squares fitting calculation, and determine whether to terminate the least squares fitting calculation or return to step 1 to perform next iterative calculation.
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公开(公告)号：US20240033778A1
公开(公告)日：2024-02-01
申请号：US17964326
申请日：2022-10-12
Applicant: Space Engineering University
Inventor： Jifei YE , Baoyu XING , Yanji HONG , Sibo WANG , Nanlei LI
CPC classification number: B05D3/144 , B05D3/101 , B05D2201/02
Abstract: Provided is a preparation method for a double-layer working medium target tape with a plasma-enhanced interfacial bonding force for a micro laser thruster. Aiming at the problem that in an existing micro laser thruster, when a working medium is ablated by a laser beam, due to a weak interlayer interfacial bonding force between a transparent film substrate and the coating working medium, sputtering or bulging occurs, which remarkably reduces propulsive performance, a method for treating a surface of a transparent film substrate with a low-temperature plasma is used to increase surface energy of a film and an adhesive force of a working medium layer on a surface of the film, thereby enhancing the interlayer interfacial bonding force. According to the method in the present disclosure, the transparent film substrate is treated with the low-temperature plasma.
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8.发明授权公开(公告)号：US10260959B2
公开(公告)日：2019-04-16
申请号：US15959225
申请日：2018-04-21
Applicant: Space Engineering University
Inventor： Yanji Hong , Junling Song , Guangyu Wang , Wei Rao
Abstract: The present invention discloses a multi-lightpath and multi-angle measurement apparatus, including an electrically controlled rotary table, electronically controlled translation tables, a laser transmitting/receiving end face, laser couplers, a multipath data acquisition card, a laser controller, a translation controller, an etalon, a laser, detectors, and a computer. The measurement apparatus uses an all-fiber coupling structure, and two ends of the laser transmitting/receiving end face are respectively fixed on two electronically controlled translation tables. Therefore, a maximum area measured by the apparatus is 350 mm×350 mm, and an adjustable minimum translation distance is 1 mm. Bottoms of the translation tables are fixed on the electrically controlled rotary table. Featuring an ingenious design and a compact structure, the whole apparatus is easy to disassemble and easy to operate. The apparatus has high universality, and can implement two-dimensional measurement in a high-temperature combustion flow field.
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公开(公告)号：US20240418157A1
公开(公告)日：2024-12-19
申请号：US18460611
申请日：2023-09-04
Applicant: Space Engineering University
Inventor： Siyin ZHOU , Wansheng NIE , Yunfan YANG , Zitong WANG , Xinhui LIN , Danyang LI , Peng WANG
Abstract: The present disclosure relates to the technical field of space electric propulsion of spacecrafts, and discloses a thrust-quantitatively-controllable and self-neutralizable Kaufman ion thruster and a use method thereof. The Kaufman ion thruster includes a discharge chamber, a central cathode, a gas supply assembly, a steel magnetic assembly, an insulating barrier and a grid system, wherein the central cathode is coaxially inserted in the center of a front panel; the gas supply assembly includes an electronegative working substance gas source, a conventional working substance gas source, N electronegative working medium gas supply pipes and N working medium gas supply pipes; the insulating barrier includes a central connecting rod and 2N fins. Self-neutralization can be achieved without the need of neutralizers. In addition, the center-oriented thrust modes can be used for spacecraft orbit control; and the eccentric thrust mode can be used for spacecraft attitude adjustment.
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公开(公告)号：US11925956B2
公开(公告)日：2024-03-12
申请号：US17964326
申请日：2022-10-12
Applicant: Space Engineering University
Inventor： Jifei Ye , Baoyu Xing , Yanji Hong , Sibo Wang , Nanlei Li
CPC classification number: B05D3/144 , B05D3/101 , B05D2201/02
Abstract: Provided is a preparation method for a double-layer working medium target tape with a plasma-enhanced interfacial bonding force for a micro laser thruster. Aiming at the problem that in an existing micro laser thruster, when a working medium is ablated by a laser beam, due to a weak interlayer interfacial bonding force between a transparent film substrate and the coating working medium, sputtering or bulging occurs, which remarkably reduces propulsive performance, a method for treating a surface of a transparent film substrate with a low-temperature plasma is used to increase surface energy of a film and an adhesive force of a working medium layer on a surface of the film, thereby enhancing the interlayer interfacial bonding force. According to the method in the present disclosure, the transparent film substrate is treated with the low-temperature plasma.
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