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1. 发明公开

US20240383619A1 METHOD FOR ACQUIRING IMAGES OF A TERRESTRIAL ZONE USING A SPACECRAFT COMPRISING A LASER TRANSMISSION MODULE 审中-公开
公开(公告)号：US20240383619A1
公开(公告)日：2024-11-21
申请号：US18690082
申请日：2022-09-05
申请人： AIRBUS DEFENCE AND SPACE SAS
发明人： Mehdi GHEZAL , Emmanuel GIRAUD
IPC分类号： B64G1/10 , B64G1/24 , H04B10/118
CPC分类号： B64G1/1028 , B64G1/245 , H04B10/118
摘要： A method for acquiring images by a spacecraft is disclosed having an observation instrument and a laser transmission module, the method including a phase of acquiring an image of the surface of the Earth and a phase of transmitting images using the laser transmission module, and during each acquisition phase and each transmission phase, the attitude control includes: a pointing modification step during which the attitude of the spacecraft is modified so as to orient the satellite towards a predetermined setpoint, a pointing immobilization step during which the attitude of the spacecraft is controlled for a time interval referred to as an immobilization period so as to keep the spacecraft oriented towards the setpoint.

2. 发明授权

US12024314B2 End-to-end on-orbit servicing 有权
公开(公告)号：US12024314B2
公开(公告)日：2024-07-02
申请号：US17769848
申请日：2020-10-19
申请人： Thales Alenia Space Italia S.p.A. Con Unico Socio
发明人： Giorgio Fasano , Enrico Gaia , Stefano Ferroni , Mario Pessana
IPC分类号： B64G1/10 , B64G1/24 , B64G1/26 , B64G1/64
CPC分类号： B64G1/1078 , B64G1/244 , B64G1/26 , B64G1/646 , B64G1/245
摘要： An on-orbit servicing spacecraft includes an engagement system to engage a space vehicle or object to be serviced or tugged, so as to form a space system, and an electronic reaction control system to cause the spacecraft to rotate about roll, yaw, and pitch axes to control attitude and displacement along given trajectories to cause the spacecraft to carry out given maneuvers. The electronic reaction control system includes (i) a sensory system to directly sense physical quantities or allow physical quantities to be indirectly computed based on sensed physical quantities, including one or more of position, attitude, angular rates, available fuel, geometrical features, and on-board systems state, (ii) attitude control thrusters mounted so as to allow their positions and orientations to be adjustable, and (iii) an attitude control computer in communication with the sensory system and the attitude control thrusters and programmed to receive data from the sensory system and to control, based on the received data, positions, orientations, and operating states of the attitude control thrusters so as to control attitude and position of the spacecraft. The attitude control computer is programmed to cause the spacecraft to carry out a given mission including an engagement step, in which the engagement system and the attitude control thrusters are controlled by the attitude control computer to engage a space vehicle or object to be serviced or tugged, and one or more operating steps, in each of which the attitude control thrusters are controlled by the attitude control computer to meet one or more requirements established for the operating step.

3. 发明公开

US20240383620A1 DETERMINATION OF POSITIONING OF SATELLITES ASSOCIATED WITH EDGE-COMPUTING 审中-公开
公开(公告)号：US20240383620A1
公开(公告)日：2024-11-21
申请号：US18320429
申请日：2023-05-19
申请人： International Business Machines Corporation
发明人： Sudheesh S. Kairali , Sarbajit K. Rakshit
IPC分类号： B64G1/24 , G06F9/50
CPC分类号： B64G1/242 , G06F9/5027 , B64G1/002 , B64G1/245
摘要： An approach for managing location of satellites associated with edge computing is disclosed. The approach includes, identifying a group of satellites using edge computing; determining a computation requirement associated with the edge computing; determining existing computational resources associated the group of satellites; determining whether the computation requirement exceeds the existing computation resources; in responsive to having determined that the computational requirement does exceed the existing computation resources, identifying addition resources required; determining one or more orbital positions for the additional resources; and placing the additional resources into the one or more orbital positions in order to participate in the edge computing.

4. 发明授权

US12017803B2 System and method for debris capture 有权
公开(公告)号：US12017803B2
公开(公告)日：2024-06-25
申请号：US17875543
申请日：2022-07-28
申请人： Jackson Michael Lyons , Kurt Anderson
发明人： Jackson Michael Lyons , Kurt Anderson
IPC分类号： B64G1/10 , B64G1/24 , B64G1/36 , B64G1/66 , G06F16/904 , G06F18/2111 , H02S10/40
CPC分类号： B64G1/1078 , B64G1/242 , B64G1/36 , B64G1/66 , G06F16/904 , G06F18/2111 , H02S10/40 , B64G1/245 , B64G1/247
摘要： A method for capturing and deorbiting space debris includes: deploying a space debris capturing device in planetary orbit; receiving an initial target set including a first database of space debris targets that are within range of the space debris capturing device; performing a first algorithm to convert the initial target set to an accessible target set including a second database of space debris targets that are within range of the space debris capturing device; performing a second algorithm to convert the accessible target set to a final target set including a third database of space debris targets to be captured by the space debris capturing device capturing the first space debris target via a capture mechanism of the space debris capturing device; jettisoning the capture mechanism and the first captured space debris target into a decaying orbit; one of the remaining space debris targets of the third database; and positioning the space debris capturing device and the final captured space debris target into a decaying orbit.

5. 发明公开

US20240190588A1 METHOD, SYSTEM AND APPARATUS FOR SPACECRAFT ATTITUDE CONTROL ERROR REDUCTION IN TRAJECTORY INTERPOLATION 审中-公开
公开(公告)号：US20240190588A1
公开(公告)日：2024-06-13
申请号：US18537554
申请日：2023-12-12
申请人： THE UNITED STATES OF AMERICA, AS REPRESENTED BY THE SECRETARY OF THE NAVY
发明人： Roberto Cristi , Joshua Levitas , Mark Karpenko
IPC分类号： B64G1/24
CPC分类号： B64G1/245 , B64G1/2422
摘要： A method, apparatus and system for controlling an attitude of a spacecraft, the spacecraft including an attitude control system operatively associated with a ground-based spacecraft control system. According to an exemplary embodiment, the spacecraft attitude control system uses a B-spline interpolator for commanding the spacecraft and a Kalman filtering process is used to estimate B-spline interpolator coefficients. The methods and systems disclosed herein can be implemented in, for example, executable machine code and/or integrated circuit hardware.

6. 发明授权

US11958633B2 Artificial satellite and control method thereof 有权
公开(公告)号：US11958633B2
公开(公告)日：2024-04-16
申请号：US17616466
申请日：2020-05-29
申请人： SONY GROUP CORPORATION
发明人： Satoshi Ezawa , Itaru Shimizu , Naomi Kurahara , Kazuo Ishigame , Tetsu Ogawa
IPC分类号： B64G1/10 , B64G1/24 , B64G1/66 , H04B7/185
CPC分类号： B64G1/1021 , B64G1/24 , B64G1/66 , H04B7/18521 , B64G1/1028 , B64G1/1035 , B64G1/245
摘要： The present technology relates to an artificial satellite and a control method thereof that enable to ensure quality of a captured image while suppressing battery consumption. An artificial satellite includes: an imaging device configured to perform imaging of a predetermined region on the ground; and a management unit configured to change accuracy of attitude control in accordance with a remaining battery amount at an instructed imaging time, and configured to change an imaging condition in accordance with accuracy of the attitude control. The present technology can be applied to, for example, an artificial satellite or the like that performs satellite remote sensing by formation flight.

7. 发明授权

US11958635B2 Linear programming problem solving system, solution candidate calculation device, optimal solution calculation device, thruster control device for spacecraft, flying object control device, and linear programming problem solving method 有权
公开(公告)号：US11958635B2
公开(公告)日：2024-04-16
申请号：US17042956
申请日：2018-05-23
申请人： Mitsubishi Electric Corporation
发明人： Yuta Asano , Takehiro Nishiyama
IPC分类号： B64G1/24 , G06F17/12 , G06F17/16
CPC分类号： B64G1/245 , G06F17/12 , G06F17/16
摘要： A dual solution candidate searcher receives an input of information about a constraint coefficient matrix and a cost vector, determines a dual problem of a linear programming problem being a primal problem and all active sets representing combinations of active formulas in constraints of the dual problem, finds, for each of the active sets, a feasible dual solution candidate meeting constraints, and stores the dual solution candidate into a storage in a manner associated with a corresponding one of the active sets. An optimal solution calculation device receives an input of a constraint vector as, selects an optimal one of the active sets as an optimal active set based on an inner product of the constraint vector and the dual solution candidate stored in the storage, and finds and outputs a basic feasible solution corresponding to the selected active set as an optimal solution.

8. 发明授权

US11919663B2 Estimation of attitude and angular velocity of a satellite based on the use of only optical sensors 有权
公开(公告)号：US11919663B2
公开(公告)日：2024-03-05
申请号：US17423003
申请日：2020-01-15
申请人： ARCA DYNAMICS SOCIETA' A RESPONSABILITA' LIMITATA SEMPLIFICATA
发明人： Emanuele Cidonio , Fabio Curti , Daniele Luchena , Marco Moriani , Dario Spiller
IPC分类号： B64G1/24 , B64G1/36 , G01C21/02
CPC分类号： B64G1/244 , B64G1/361 , G01C21/025 , B64G1/245
摘要： The invention concerns a method for estimating the angular velocity (and, preferably, also the attitude) of a space platform (for example, a satellite, a space vehicle, or a space station) using only the information provided by one or more optical sensors, such as one or more star trackers, one or more colour and/or black and white cameras or video cameras, one of more infrared sensors, etc.

9. 发明授权

US11873123B2 Aerospace vehicle navigation and control system comprising terrestrial illumination matching module for determining aerospace vehicle position and attitude 有权
公开(公告)号：US11873123B2
公开(公告)日：2024-01-16
申请号：US17123810
申请日：2020-12-16
申请人： Government of the United States, as represented by the Secretary of the Air Force
发明人： Liberty M. Shockley , Robert A. Bettinger
IPC分类号： B64G3/00 , B64G1/24 , G01C21/24 , G06T7/73 , G06T7/277
CPC分类号： B64G3/00 , B64G1/242 , B64G1/244 , G01C21/24 , G06T7/277 , G06T7/74 , B64G1/245 , G06T2207/30181 , G06T2207/30244
摘要： The present invention relates to an aerospace vehicle navigation and control system comprising a terrestrial illumination matching module for determining spacecraft position and attitude. The method permits aerospace vehicle position and attitude determinations using terrestrial lights using an Earth-pointing camera without the need of a dedicated sensor to track stars, the sun, or the horizon. Thus, a module for making such determinations can easily and inexpensively be made onboard an aerospace vehicle if an Earth-pointing sensor, such as a camera, is present.

10. 发明授权

US11845573B2 Configuration construction and attitude control method for pyramid deorbit sail 有权
公开(公告)号：US11845573B2
公开(公告)日：2023-12-19
申请号：US17961125
申请日：2022-10-06
申请人： BEIJING INSTITUTE OF TECHNOLOGY
发明人： Jingrui Zhang , Ruonan Zhang , Keying Yang , Lincheng Li
IPC分类号： B64G1/40 , B64G1/24
CPC分类号： B64G1/407 , B64G1/245
摘要： Provided is a configuration construction and attitude control method for a pyramid deorbit sail. By taking into consideration environmental perturbation like atmospheric resistance perturbation and non-spherical earth perturbation, a dynamics model featuring three-dimensional orbit-and-attitude coupling based on position vectors and quaternion descriptions, the deorbit sail is taken as a rigid body, a spacecraft body is taken as a mass point, airflow obstruction is considered in the windward area, thereby improving the precision of the dynamics model; based on this model, the law of influence of the configuration parameters in the deorbit sail, such as a cone angle and a strut length, on the attitude stability and deorbiting efficiency of the spacecraft in different cases is analyzed, the configuration parameters of the pyramid deorbit sail system are analyzed and optimized according to the derived law, so as to obtain a pyramid deorbit sail achieving high attitude stability and high deorbiting efficiency.

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