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Статті в журналах з теми "Satellite docking"

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Автор: Grafiati

Опубліковано: 6 вересня 2023

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1

Bai, Bingtao, Lurui Xia, and Sen Li. "Design and dynamics simulation of axial radial double locking satellite docking mechanism." Journal of Physics: Conference Series 2569, no. 1 (August 1, 2023): 012020. http://dx.doi.org/10.1088/1742-6596/2569/1/012020.

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Анотація:

Abstract Aiming at the docking requirements of small satellites in orbit service, an axial, radial double-locking satellite docking mechanism was designed to realize the docking and separation of small satellites. Capture docking using the butt bar and the groove. The mechanism possesses multiple advantages, such as simple structure and fast response. A dynamic model considering contact, collision, buffering, and friction was established, and ADAMS software simulated the docking process. Apart from that, the dynamics and motion data of the mechanism were obtained. As revealed by the results, under the initial conditions of the general light and small docking mechanism, the mechanism can achieve the set task and complete the docking with a small collision force. What’s more, the buffer device can absorb 85.5% of the energy of the satellite, and the mechanism has a certain attitude correction ability. Altogether, this exploration can provide a reference for designing satellite docking mechanisms and formulating a docking strategy in the future.

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2

Jianbin, Huang, Li Zhi, Huang Longfei, Meng Bo, Han Xu, and Pang Yujia. "Docking mechanism design and dynamic analysis for the GEO tumbling satellite." Assembly Automation 39, no. 3 (August 5, 2019): 432–44. http://dx.doi.org/10.1108/aa-12-2017-191.

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Purpose According to the requirements of servicing and deorbiting the failure satellites, especially the tumbling ones on geosynchronous orbit, this paper aims to design a docking mechanism to capture these tumbling satellites in orbit, to analyze the dynamics of the docking system and to develop a new collision force-limited control method in various docking speeds. Design/methodology/approach The mechanism includes a cone-rod mechanism which captures the apogee engine with a full consideration of despinning and damping characteristics and a locking and releasing mechanism which rigidly connects the international standard interface ring (Marman rings, such as 937B, 1194 and 1194A mechanical interface). The docking mechanism was designed under-actuated, aimed to greatly reduce the difficulty of control and ensure the continuity, synchronization and force uniformity under the process of repeatedly capturing, despinning, locking and releasing the tumbling satellite. The dynamic model of docking mechanism was established, and the impact force was analyzed in the docking process. Furthermore, a collision detection and compliance control method is proposed by using the active force-limited Cartesian impedance control and passive damping mechanism design. Findings A variety of conditions were set for the docking kinematics and dynamics simulation. The simulation and low-speed docking experiment results showed that the force translation in the docking phase was stable, the mechanism design scheme was reasonable and feasible and the proposed force-limited Cartesian impedance control could detect the collision and keep the external force within the desired value. Originality/value The paper presents a universal docking mechanism and force-limited Cartesian impedance control approach to capture the tumbling non-cooperative satellite. The docking mechanism was designed under-actuated to greatly reduce the difficulty of control and ensure the continuity, synchronization and force uniformity. The dynamic model of docking mechanism was established. The impact force was controlled within desired value by using a combination of active force-limited control approach and passive damping mechanism.

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3

Seweryn, Karol, and Jurek Z. Sasiadek. "Satellite angular motion classification for active on-orbit debris removal using robots." Aircraft Engineering and Aerospace Technology 91, no. 2 (February 4, 2019): 317–32. http://dx.doi.org/10.1108/aeat-01-2018-0049.

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PurposeThis paper aims to present a novel method for identification and classification of rotational motion for uncontrolled satellites. These processes are shown in context of close proximity orbital operations. In particular, it includes a manipulator arm mounted on chaser satellite and used to capture target satellites. In such situations, a precise extrapolation of the target’s docking port position is needed to determine the manipulator arm motion. The outcome of this analysis might be used in future debris removal or servicing space missions.Design/methodology/approachNonlinear, and in some special cases, chaotic nature of satellite rotational motion was considered. Four parameters were defined: range of motion toward docking port, dominant frequencies, fractal dimension of the motion and its time dependencies.FindingsThe qualitative analysis was performed for presented cases of spacecraft rotational motion and for each case the respective parameters were calculated. The analysis shows that it is possible to detect the type of rotational motion.Originality/valueA novel procedure allowing to estimate the type of satellite rotational motion based on fractal approach was proposed.

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4

Yu, Feng, Yi Zhao, and Yanhua Zhang. "Pose Determination for Malfunctioned Satellites Based on Depth Information." International Journal of Aerospace Engineering 2019 (June 11, 2019): 1–15. http://dx.doi.org/10.1155/2019/6895628.

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Autonomous on-orbit servicing is the future space activity which can be utilized to extend the satellite life. Relative pose estimation for a malfunctioned satellite is one of the key technologies to achieve robotic on-orbit servicing. In this paper, a relative pose determination method by using point cloud is presented for the final phase of the rendezvous and docking of malfunctioned satellites. The method consists of three parts: (1) planes are extracted from point cloud by utilizing the random sample consensus algorithm. (2) The eigenvector matrix and the diagonal eigenvalue matrix are calculated by decomposing the point cloud distribution matrix of the extracted plane. The eigenvalues are utilized to recognize rectangular planes, and the eigenvector matrix is the attitude rotation matrix from the sensor to the plane. The solution of multisolution problem is also presented. (3) An extended Kalman filter is designed to estimate the translational states, the rotational states, the location of mass center, and the moment-of-inertia ratios. Because the method only utilizes the local features without observing the whole satellite, it is suitable for the final phase of rendezvous and docking. The algorithm is validated by a series of mathematical simulations.

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5

TAKEBAYASHI, Shinichi, and Satoshi TAKEZAWA. "Synchronous Position Control Method for Satellite Docking System." Proceedings of the JSME annual meeting 2000.2 (2000): 553–54. http://dx.doi.org/10.1299/jsmemecjo.2000.2.0_553.

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6

Liang, Jianxun, and Ou Ma. "Angular velocity tracking for satellite rendezvous and docking." Acta Astronautica 69, no. 11-12 (December 2011): 1019–28. http://dx.doi.org/10.1016/j.actaastro.2011.07.009.

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7

Zhang, Yuan, Ying Ying Wang, Yan Song, and Li Li Zhou. "Kinematics Analysis and Simulation of Small Satellite Docking Mechanism End Executor." Applied Mechanics and Materials 487 (January 2014): 460–64. http://dx.doi.org/10.4028/www.scientific.net/amm.487.460.

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Анотація:

In order to save space mission cost, prolonging the working life of the spacecraft and improving the flexibility and capable of performing various tasks should get more attention on orbit servicing technology. For the docking process of a new type of two independent service in-orbit spacecraft, this paper finished the kinematics analysis, for the whole docking capture process, two groups of different initial conditions and control function of the simulation analysis were finished by the ADAMS software. The results prove that the docking mechanism performance is very good, and reliable connection can be realized in the general initial conditions.

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8

YongZhi, Wen, Zhang ZeJian, and Wu Jie. "High-Precision Navigation Approach of High-Orbit Spacecraft Based on Retransmission Communication Satellites." Journal of Navigation 65, no. 2 (March 12, 2012): 351–62. http://dx.doi.org/10.1017/s0373463311000671.

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Many countries have presented new requirements for in-orbit space services. Space autonomous rendezvous and docking technology could speed up the development of in-orbit spacecraft and reduce the threat of increasing amounts of space debris. The purpose of this paper is to provide real-time high-precision navigation data for high-orbit spacecraft, thus reducing the cost of ground monitoring for high-orbit spacecraft autonomous rendezvous operations, and to provide technical support for high-orbit spacecraft in-orbit services. This paper proposes a new high-orbit spacecraft autonomous navigation approach, based on a communication satellite transmitting ground navigation signals. It proposes an overall navigation system design, sets up the system information integration model and analyses the precision of the navigation system by simulation research. Through simulation of this navigation method, the positional precision of a spacecraft at an altitude of 40 000 km, can be within 2·6 m with a velocity precision of 0·0011 m/s. The transponding satellite navigation method greatly reduces the development costs by using communication satellites in high-orbit spacecraft navigation instead of launching special navigation satellites. Moreover, the signals of transponding satellite navigation are generated on the ground, which is very convenient and cost-effective for system maintenance. In addition, placing atomic clocks on the ground may also help improve the clock accuracy achieved. In this study, the satellite-based navigation method is for the first time applied in high-orbit spacecraft navigation. The study's data could improve the present lack of effective high-orbit spacecraft navigation methods and provide strong technical support for autonomous rendezvous and docking of high orbital spacecraft, as well as other application fields.

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9

Ui, Kyoichi, Saburo Matunaga, Shin Satori, and Tomohiro Ishikawa. "Microgravity experiments of nano-satellite docking mechanism for final rendezvous approach and docking phase." Microgravity - Science and Technology 17, no. 3 (September 2005): 56–63. http://dx.doi.org/10.1007/bf02872088.

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10

Somov, Ye I., S. A. Butyrin, S. Ye Somov, and T. Ye Somova. "DYNAMICS OF MOORING AND DOCKING OF A SPACE ROBOT-MANIPULATOR WITH A GEOSTATIOONARY SATELLITE." Izvestiya of Samara Scientific Center of the Russian Academy of Sciences 24, no. 4 (2022): 155–60. http://dx.doi.org/10.37313/1990-5378-2022-24-4-155-160.

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The control problems of a space robot-manipulator in the process of mooring and docking with a geostationary satellite are considered when docking mechanism of the “rod-cone” class. A dynamic analysis is carried out with changing mooring conditions and the results of computer simulation are presented.

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11

TAKEBAYASHI, Shin-ichi, and Satoshi TAKEZAWA. "212 Synchronous Position Control Method for Satellite Docking Control." Proceedings of Conference of Hokkaido Branch 2000.40 (2000): 74–75. http://dx.doi.org/10.1299/jsmehokkaido.2000.40.74.

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12

Oda, Mitsushige. "Summary of NASDA's ETS-VII robot satellite mission." Journal of Robotics and Mechatronics 12, no. 4 (August 20, 2000): 417–24. http://dx.doi.org/10.20965/jrm.2000.p0417.

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The National Space Development Agency of Japan launched ETS-VII (Engineering Test Satellite No.7) on November 28, 1997, to conduct rendezvous docking and space robot technology experiments. ETS-VII is the world's first satellite that used a robot arm on a satellite. The robot arm was 2m long and was teleoperated from a ground control station. Mission of ETS-VII lasted for two years and yielded much experience and many results. This paper summarizes experiences and results of the ETS-VII robot satellite.

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13

Akhloumadi, Mahdi, and Danil Ivanov. "Influence of Satellite Motion Control System Parameters on Performance of Space Debris Capturing." Aerospace 7, no. 11 (November 6, 2020): 160. http://dx.doi.org/10.3390/aerospace7110160.

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Relative motion control problem for capturing the tumbling space debris object is considered. Onboard thrusters and reaction wheels are used as actuators. The nonlinear coupled relative translational and rotational equations of motion are derived. The SDRE-based control algorithm is applied to the problem. It is taken into account that the thrust vector has misalignment with satellite center of mass, and reaction wheels saturation affects the ability of the satellite to perform the docking maneuver to space debris. The acceptable range of a set of control system parameters for successful rendezvous and docking is studied using numerical simulations taking into account thruster discreteness, actuators constrains, and attitude motion of the tumbling space debris.

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14

YASUDA, Kuniharu. "Rendezvous and Docking Simulation for the Engineering Test Satellite VII." Journal of the Japan Society for Aeronautical and Space Sciences 42, no. 491 (1994): 739–45. http://dx.doi.org/10.2322/jjsass1969.42.739.

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15

Qiao, Kun, and Shinichi NAKASUKA. "B1 Trajectory Planning for Safe Docking with a Tumbling Satellite." Proceedings of the Space Engineering Conference 2011.20 (2012): _B1–1_—_B1–4_. http://dx.doi.org/10.1299/jsmesec.2011.20._b1-1_.

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16

Zhang, Wei, Pingguo Xiao, and Junlin Li. "Satellite Pose Estimation via Only a Single Spatial Circle." Information 13, no. 2 (February 17, 2022): 95. http://dx.doi.org/10.3390/info13020095.

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To estimate the pose of satellites in space, the docking ring component has strong rigid body characteristics and can provide a fixed circular feature, which is an important object. However, due to the need for additional constraints to estimate a single spatial circle pose on the docking ring, practical applications are greatly limited. In response to the above problems, this paper proposes a pose solution method based on a single spatial circle. First, the spatial circle is discretized into a set of 3D asymmetric specific sparse points, eliminating the strict central symmetry of the circle. Then, a two-stage pose estimation network, Hvnet, based on Hough voting is proposed to locate the 2D sparse points on the image. Finally, the position and orientation of the spatial circle are obtained by the Perspective-n-Point (PnP) algorithm. The effectiveness of the proposed method was verified through experiments, and the method was found to achieve good solution accuracy under a complex lighting environment.

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17

Oda, Mitsushige. "In-Orbit Experiment of Space Robot Technologies on ETS-7." Journal of Robotics and Mechatronics 6, no. 5 (October 20, 1994): 370–74. http://dx.doi.org/10.20965/jrm.1994.p0370.

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NASDA is now developing Engineering Test Satellite <I>#</I>7 (ETS-7) to perform Rendezvous Docking and Space robot technology experiments in the actual space environment. ETS-7’s space robot experiments include 1) performance evaluation of a robot arm and related equipment in the actual space environment, 2) cooperative control experiment between the satellite attitude and the robot arm, 3) teleoperation experiment of the satellite mounted robot system from a ground control station, and 4) demonstration of in-orbit satellite servicing using a robot arm. The satellite will be launched in 1997 by NASDA’s H-11 rocket into a low earth orbit.

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18

Zhang, Yuan, Jian Wang, Yan Song, and Li Li Sun. "Dynamic Simulation Analysis for Docking Mechanism of On-Orbit-Servicing Satellite." Applied Mechanics and Materials 487 (January 2014): 313–18. http://dx.doi.org/10.4028/www.scientific.net/amm.487.313.

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The new type of three jaw docking mechanism is designed for use in orbiting spacecraft, the mathematical model is given and its working characteristics are analyzed. By establishing the mathematical model of the interaction of the parts under the different coordinate system, it is obtained that the corresponding kinematic characteristics; contact collision dynamics model is established by using the Hertz model theory, dynamic equation is established by Newton-Euler method, and simulation analysis are carried out by using the dynamics simulation software ADAMS, through the simulation analysis of three groups with different initial conditions, the results show that it achieve reliable grasp with good performance, it provides the lock claw curve in contact collision force and movement characteristics curve. These curves provide reference to improve the performance of docking mechanism.

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19

Kawano, Isao, Masaaki Mokuno, Toru Kasai, and Takashi Suzuki. "Result of Autonomous Rendezvous Docking Experiment of Engineering Test Satellite-VII." Journal of Spacecraft and Rockets 38, no. 1 (January 2001): 105–11. http://dx.doi.org/10.2514/2.3661.

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20

Jeong, Miri, Dong-Hyun Cho, and Hae-Dong Kim. "A Development of Docking Phase Analysis Tool for Nanosatellite." Journal of Astronomy and Space Sciences 37, no. 3 (September 2020): 187–97. http://dx.doi.org/10.5140/jass.2020.37.3.187.

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In order to avoid the high cost and high risk of demonstration mission of rendezvous-docking technology, missions using nanosatellites have recently been increasing. However, there are few successful mission cases due to many limitations of nanosatellites like small size, power limitation, and limited performances of sensor, thruster, and controller. To improve the probability of rendezvous-docking mission success using nanosatellite, a rendezvous-docking phase analysis tool for nanosatellites is developed. The tool serves to analyze the relative position and attitude control of the chaser satellite at the docking phase. In this tool, the Model Predictive Controller (MPC) is implemented as a controller, and Extended Kalman Filter (EKF) is adopted as a filter for noise filtering. To verify the performance and effectiveness of the developed tool for nanosatellites, simulation study was conducted. Consequently, we confirmed that this tool can be used for the analysis of relative position and attitude control for nanosatellites in the rendezvous-docking phase.

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21

Wen, Changxuan, and Pini Gurfil. "Guidance, navigation and control for autonomous R-bar proximity operations for geostationary satellites." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 3 (November 13, 2016): 452–73. http://dx.doi.org/10.1177/0954410016638877.

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R-bar refers to the local vertical axis pointing radially upward in a satellite-fixed reference frame. Approaching a satellite along the R-bar, especially for rendezvous and docking to geostationary satellites, is advantageous in terms of safety considerations and flight time compared to other options. In this paper, a specialized study on autonomous R-bar proximity operations with respect to a geostationary target from a separation of several kilometers to a few hundreds of meters, commonly referred to as the closing phase, is carried out and a comprehensive solution for both attitude and orbit control in this scenario is proposed. An integrative design of the guidance, navigation, and control for R-bar proximity operations is presented. Impulsive R-bar hopping maneuvers are developed for the trajectory guidance. This method is shown to be passively safe and time efficient. The onboard sensors provide measurements of the line-of-sight, range to the target, attitude and angular velocity in the inertial frame. Due to the sensitivity of the sensor’s pointing in the far-range phase, a sliding mode attitude control law is introduced to align the optical axis with the line-of-sight to the target. Sensor measurements are fused and processed by an extended Kalman filter. Simulation results indicate that the proposed integrative guidance, navigation, and control algorithms are robust to uncertainties and noise, and can be used as a comprehensive solution for R-bar rendezvous and docking mission design during the closing phase.

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22

Kawano, Isao, Masaaki Mokuno, Hiroshi Koyama, and Taichi Nakamura. "Space robot. Guidance and Control for the Automatic Rendezvous Docking Technology. Engineering Test Satellite VII Rendezvous Docking System." Journal of the Robotics Society of Japan 14, no. 7 (1996): 935–39. http://dx.doi.org/10.7210/jrsj.14.935.

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23

YAMADA, Yuki, and Takaya INAMORI. "Propellantless Close-Range Guidance for Small Satellite Docking Using Simple Electromagnetic Devices." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19, no. 4 (2021): 500–506. http://dx.doi.org/10.2322/tastj.19.500.

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24

An, Xue Yan, Wei Lu, and Zhang Ren. "Compound Control of Attitude Synchronization for Autonomous Docking to a Tumbling Satellite." Applied Mechanics and Materials 394 (September 2013): 470–76. http://dx.doi.org/10.4028/www.scientific.net/amm.394.470.

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In order to solve the attitude synchronization control problem for an on-orbit servicing spacecraft autonomous docking to a tumbling satellite in the presence of unknown bounded disturbances and system uncertainties, a compound control law is presented in this paper. The compound control law is composed of a nonlinear feedback control law and a compensate control law. The nonlinear feedback control law is mainly used to track the system command and the compensate control law is mainly used to deal with the external disturbances and system uncertainties to enhance the robustness of the control system. Simulation results verified the effectiveness of the designed compound control law, and the robustness to the unknown bounded disturbances, system uncertainties is also demonstrated.

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25

Xiao, Zhengyi, jinghui Lv, Guowang Wu, and Jiantao Yao. "Configuration Optimization and Force Analysis of Parallel Attached Platform for Satellite Docking." IOP Conference Series: Materials Science and Engineering 382 (July 2018): 052041. http://dx.doi.org/10.1088/1757-899x/382/5/052041.

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26

Mokuno, Masaaki. "Rendezvous Docking Technology of Engineering Test Satellite VII (EST-VII/Orihime・Hikoboshi)." Journal of the Society of Mechanical Engineers 103, no. 982 (2000): 598–99. http://dx.doi.org/10.1299/jsmemag.103.982_598.

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27

Zhang, Yuan-wen, Le-ping Yang, Yan-wei Zhu, Huan Huang, and Wei-wei Cai. "Nonlinear 6-DOF control of spacecraft docking with inter-satellite electromagnetic force." Acta Astronautica 77 (August 2012): 97–108. http://dx.doi.org/10.1016/j.actaastro.2012.03.020.

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28

Michael, Johannes, Kurt Chudej, and Jürgen Pannek. "Modelling and Optimal Control of a Docking Maneuver with an Uncontrolled Satellite." IFAC Proceedings Volumes 45, no. 2 (2012): 1135–40. http://dx.doi.org/10.3182/20120215-3-at-3016.00201.

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29

Yang, George, and Ou Ma. "Validation of satellite docking simulations using an air-bearing-based experimental testbed." International Journal of Space Science and Engineering 1, no. 3 (2013): 253. http://dx.doi.org/10.1504/ijspacese.2013.058845.

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30

Estable, Stéphane, Ingo Ahrns, Ralf Regele, Marko Jankovic, Wiebke Brinkmann, Jeremi Gancet, A. M. Barrio, et al. "Outcomes of the PERIOD project on In-Space Manufacturing, Assembly and Refuelling Technologies." Journal of Physics: Conference Series 2526, no. 1 (June 1, 2023): 012121. http://dx.doi.org/10.1088/1742-6596/2526/1/012121.

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Анотація:

Abstract Traditionally, satellites and other space-specific assemblies (e.g., antennas, spacecraft, etc.) are built on Earth and then sent into orbit. New approaches are pursuing direct on-orbit manufacturing and assembly using robotics, autonomy, and modularity. The advantages are many, ranging from virtually unlimited overall volume and design of large satellite antennas to numerous options for building larger space infrastructures such as large reflectors and modular space stations. In addition, in-space manufacturing and assembly (ISMA) technologies can enable the upgrade and repair of existing spacecraft and satellites already in orbit, promoting the sustainable use of space through plug-and-play modularity. The PERIOD project is pursuing a concept in which an orbital demonstrator is being developed for satellite manufacturing and assembly, as well as docking and refuelling experiments. This paper describes the background of the development, the PERASPERA building block technologies ESROCOS (European Space Robotics Control and Operating System), ERGO (European Robotic Goal-Oriented Autonomous Controller) and InFuse (Data Fusion) used, the test setup of the demonstrator and first results. The successful implementation and validation of ISMA technologies will lead to the generation of independent European capacities allowing Europe to build future orbital infrastructure and to be competitive on the ISMA markets

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31

Yu, Feng, Zhen He, Bing Qiao, and Xiaoting Yu. "Stereo-Vision-Based Relative Pose Estimation for the Rendezvous and Docking of Noncooperative Satellites." Mathematical Problems in Engineering 2014 (2014): 1–12. http://dx.doi.org/10.1155/2014/461283.

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Анотація:

Autonomous on-orbit servicing is expected to play an important role in future space activities. Acquiring the relative pose information and inertial parameters of target is one of the key technologies for autonomous capturing. In this paper, an estimation method of relative pose based on stereo vision is presented for the final phase of the rendezvous and docking of noncooperative satellites. The proposed estimation method utilizes the sparse stereo vision algorithm instead of the dense stereo algorithm. The method consists of three parts: (1) body frame reestablishment, which establishes the body-fixed frame for the target satellite using the natural features on the surface and measures the relative attitude based on TRIAD and QUEST; (2) translational parameter estimation, which designs a standard Kalman filter to estimate the translational states and the location of mass center; (3) rotational parameter estimation, which designs an extended Kalman filter and an unscented Kalman filter, respectively, to estimate the rotational states and all the moment-of-inertia ratios. Compared to the dense stereo algorithm, the proposed method can avoid degeneracy when the target has a high degree of axial symmetry and reduce the number of sensors. The validity of the proposed method is verified by numerical simulations.

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32

Choi, Won-Sub, Dong-Hyun Cho, Ha-Ryong Song, Jong-Hak Kim, Su-Jeong Ko, and Hae-Dong Kim. "A 5-DOF Ground Testbed for Developing Rendezvous/Docking Algorithm of a Nano-satellite." Journal of the Korean Society for Aeronautical & Space Sciences 43, no. 12 (December 1, 2015): 1124–31. http://dx.doi.org/10.5139/jksas.2015.43.12.1124.

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33

Zebenay, M., T. Boge, R. Krenn, and D. Choukroun. "Analytical and experimental stability investigation of a hardware-in-the-loop satellite docking simulator." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 229, no. 4 (June 20, 2014): 666–81. http://dx.doi.org/10.1177/0954410014539290.

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34

Dhanalakshmi, R., N. P. G. Bhavani, S. Srinivasulu Raju, Pundru Chandra Shaker Reddy, Dinesh Marvaluru, Devesh Pratap Singh, and Areda Batu. "Onboard Pointing Error Detection and Estimation of Observation Satellite Data Using Extended Kalman Filter." Computational Intelligence and Neuroscience 2022 (October 7, 2022): 1–8. http://dx.doi.org/10.1155/2022/4340897.

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The satellite communication is embellished constantly by providing information, ensuring security, and enables the communication among huge at a particular time efficiently. The satellite navigation helps in determining the people’s location. Global development, natural disasters, change in climatic conditions, agriculture crop growth, etc., are monitored using satellite observation. Hence, the satellite includes detailed information data, and it must be protected confidentially. The field of the satellite is enhanced at an astonishing pace. Satellite data play an important role in this modern world; hence, the onboard-satellite data must secure through the proper selection of error detection and estimation schema. Lightweight deep learning algorithm based on Extended Kalman Filter (KFK) is proposed to detect and estimate onboard pointing error such as an error in attitude and orbit. The Extended Kalman Filter (EKF) is widely used in the satellite system. EKF is utilized in this proposed model to detect the onboard pointing error such as attitude and orbit determination. An autonomous estimation of orbit position is possible through space-borne gravity. The information obtained through the observation of satellite data is compared with the accurate gravity model in detecting the error. The utilization of EKF reduces the dependence of the ground tracking system in satellite determination. The orbital altitude and orbital position are the most important challenges faced in the satellite determination system. The satellite model using the Extended Kalman Filter is an optimum method in estimating the orbital parameters. The errors in the linearization process are detected, and this can be overcome through the proper selection of linear expansion point with the EKF algorithmic model with the Jacobian matrix calculation. The results show that the EKF implementation helps in attaining better accuracy than other methodologies. Its contribution is enormous to many space missions, autonomous rendezvous and docking for manned and unmanned missions (e.g., ISS operations and beyond, in-orbit servicing, and in-orbit refueling), routine satellite OD operations, orbital debris removal systems, Space Situational Awareness (SSA) operations, and others.

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35

Hartley, Craig. "Simulating Satellite Retrieval Missions Using the Manned Maneuvering Unit." Journal of the IEST 28, no. 2 (March 1, 1985): 29–33. http://dx.doi.org/10.17764/jiet.1.28.2.p184236431225358.

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The Manned Maneuvering Unit (MMU) built by the Martin Marietta Company is a self-contained, propulsive backpack that provides space-suited astronauts with six degree-of-freedom precision maneuvering capability to at least 150 meters (500 feet) from the Shuttle Orbiter. Astronauts are trained to fly the MMU in the Space Operations Simulator (SOS) Laboratory located at Martin Marietta Denver Aerospace facilities in Denver, Colorado. MMU simulations in the SOS use two major devices. The first is a six-degree-of-freedom Moving Base Carriage (MBC) that allows the trainee to fly the MMU in a large room and to maneuver around and dock with full-scale targets. The second device is a large-screen television display that provides the trainee with accurate views of tumbling targets from any point in a surrounding sphere up to 300 meters (1000 feet) in diameter. Astronauts used the SOS to train for the mission to retrieve and repair the Solar Maximum satellite in April 1984 and the mission to recover two H-376 communications satellites in November 1984. Subjective comparisons by astronauts of on-orbit MMU performance to simulated MMU performance in the SOS indicate that the simulations are very realistic. Data from the Solar Maximum mission resulted in two software upgrades that increased SOS fidelity for the H-376 recovery mission: a model of contact dynamics between the MMU and a target spacecraft, and a model of forces imparted to the target by MMU thruster plumes impinging on the target during docking. Success of both satellite retrieval missions demonstrates the value of MMU space operations simulations.

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36

Ledkov, A. S., and R. S. Pikalov. "Nonlinear Control of Tether Retrieval in an Elliptical Orbit." Nelineinaya Dinamika 19, no. 1 (2023): 0. http://dx.doi.org/10.20537/nd230401.

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Tether retrieval is an important stage in many projects using space tether systems. It is known that uniform retrieval is an unstable process that leads to the winding of the tether on a satellite at the final stage of retraction. This is a serious obstacle to the practical application of space tethers in the tasks of climbing payloads to a satellite and docking the spacecraft with a tethered satellite after its capture. The paper investigates the plane motion of a space tether system with a massless tether of variable length in an elliptical orbit. A new control law that ensures the retrieval of the tether without increasing the amplitude of oscillations at the final stage is proposed. The asymptotic stability of the space tether system’s controlled motion in an elliptical orbit is proved. A numerical analysis of tether retrieval is carried out. The influence of the eccentricity of the orbit on the retrieval process is investigated. The results of the work can be useful in preparing missions of the active space debris removal and in performing operations involving tether retrieval.

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37

Ma, Ou, Angel Flores-Abad, and Toralf Boge. "Use of industrial robots for hardware-in-the-loop simulation of satellite rendezvous and docking." Acta Astronautica 81, no. 1 (December 2012): 335–47. http://dx.doi.org/10.1016/j.actaastro.2012.08.003.

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38

Kunugi, M., H. Koyama, T. Okanuma, T. Nakamura, M. Mokuno, I. Kawano, H. Horiguchi, and K. Kibe. "Guidance, Navigation and Control System in Engineering Test Satellite VII Rendez-Vous and Docking Experiment." IFAC Proceedings Volumes 27, no. 13 (September 1994): 303–8. http://dx.doi.org/10.1016/s1474-6670(17)45817-4.

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39

ZHAO, Jiankang, and Jinhai DAI. "A Control Technique for Rendezvous and Docking Based on Helix-approach Orbit of Inspector Satellite." Chinese Journal of Space Science 26, no. 4 (2006): 298. http://dx.doi.org/10.11728/cjss2006.04.298.

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40

Zhang, Jianming, Junxiang Lian, Zhaoxiang Yi, Shuwang Yang, and Ying Shan. "High-Accuracy Guide Star Catalogue Generation with a Machine Learning Classification Algorithm." Sensors 21, no. 8 (April 9, 2021): 2647. http://dx.doi.org/10.3390/s21082647.

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In order to detect gravitational waves and characterise their sources, three laser links were constructed with three identical satellites, such that interferometric measurements for scientific experiments can be carried out. The attitude of the spacecraft in the initial phase of laser link docking is provided by a star sensor (SSR) onboard the satellite. If the attitude measurement capacity of the SSR is improved, the efficiency of establishing laser linking can be elevated. An important technology for satellite attitude determination using SSRs is star identification. At present, a guide star catalogue (GSC) is the only basis for realising this. Hence, a method for improving the GSC, in terms of storage, completeness, and uniformity, is studied in this paper. First, the relationship between star numbers in the field of view (FOV) of a staring SSR, together with the noise equivalent angle (NEA) of the SSR—which determines the accuracy of the SSR—is discussed. Then, according to the relationship between the number of stars (NOS) in the FOV, the brightness of the stars, and the size of the FOV, two constraints are used to select stars in the SAO GSC. Finally, the performance of the GSCs generated by Decision Trees (DC), K-Nearest Neighbours (KNN), Support Vector Machine (SVM), the Magnitude Filter Method (MFM), Gradient Boosting (GB), a Neural Network (NN), Random Forest (RF), and Stochastic Gradient Descent (SGD) is assessed. The results show that the GSC generated by the KNN method is better than those of other methods, in terms of storage, uniformity, and completeness. The KNN-generated GSC is suitable for high-accuracy spacecraft applications, such as gravitational detection satellites.

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41

S.Ye. Somov, T.Ye. Somova, S.A. Butyrin, and Ye.I. Somov. "COMPARISON OFTORQUE PROPERTIESFOR THE FLYWHEELS AND GYRODYNES CLUSTERS WHILE A SPACE ROBOT DOCKING WITH A GEOSTATIONARY SATELLITE." Izvestiya of Samara Scientific Center of the Russian Academy of Sciences 24, no. 1 (2022): 105–13. http://dx.doi.org/10.37313/1990-5378-2022-24-1-105-113.

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The possibilities of creating the control torques by clusters of flywheels and gyrodines when braking the rotation of a space robot mated with a geostationary satellite after the completion of their dockingare compared. The control system algorithms with unloading of electromechanical drives angular momentums using an electro-reaction propulsion unit are developed. The results of computer simulation of nonlinear dynamic processes are presented, confirming the effectiveness of the created algorithms.

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42

Kurtulmus, Bahtiyar, Wenbo Wang, Thomas Ruppert, Annett Neuner, Berati Cerikan, Linda Viol, Rafael Dueñas-Sánchez, Oliver J. Gruss, and Gislene Pereira. "WDR8 is a centriolar satellite and centriole-associated protein that promotes ciliary vesicle docking during ciliogenesis." Journal of Cell Science 129, no. 3 (December 16, 2015): 621–36. http://dx.doi.org/10.1242/jcs.179713.

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43

Ui, Kyoichi, Ryuichi Hodoshima, Saburo Matunaga, and Masafumi IAI. "F-1531 Study on Docking Mechanism with Release and Retract Function for Small Mothership-Daughtership Satellite." Proceedings of the JSME annual meeting IV.01.1 (2001): 375–76. http://dx.doi.org/10.1299/jsmemecjo.iv.01.1.0_375.

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44

Huang, Panfeng, Lu Chen, Bin Zhang, Zhongjie Meng, and Zhengxiong Liu. "Autonomous Rendezvous and Docking with Nonfull Field of View for Tethered Space Robot." International Journal of Aerospace Engineering 2017 (2017): 1–11. http://dx.doi.org/10.1155/2017/3162349.

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In the ultra-close approaching phase of tethered space robot, a highly stable self-attitude control is essential. However, due to the field of view limitation of cameras, typical point features are difficult to extract, where commonly adopted position-based visual servoing cannot be valid anymore. To provide robot’s relative position and attitude with the target, we propose a monocular visual servoing control method using only the edge lines of satellite brackets. Firstly, real time detection of edge lines is achieved based on image gradient and region growing. Then, we build an edge line based model to estimate the relative position and attitude between the robot and the target. Finally, we design a visual servoing controller combined with PD controller. Experimental results demonstrate that our algorithm can extract edge lines stably and adjust the robot’s attitude to satisfy the grasping requirements.

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45

Yang, Xi, Mengqing Cao, Cong Li, Hua Zhao, and Dong Yang. "Learning Implicit Neural Representation for Satellite Object Mesh Reconstruction." Remote Sensing 15, no. 17 (August 24, 2023): 4163. http://dx.doi.org/10.3390/rs15174163.

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Constructing a surface representation from the sparse point cloud of a satellite is an important task for satellite on-orbit services such as satellite docking and maintenance. In related studies on surface reconstruction from point clouds, implicit neural representations have gained popularity in learning-based 3D object reconstruction. When aiming for a satellite with a more complicated geometry and larger intra-class variance, existing implicit approaches cannot perform well. To solve the above contradictions and make effective use of implicit neural representations, we built a NASA3D dataset containing point clouds, watertight meshes, occupancy values, and corresponding points by using the 3D models on NASA’s official website. On the basis of NASA3D, we propose a novel network called GONet for a more detailed reconstruction of satellite grids. By designing an explicit-related implicit neural representation of the Grid Occupancy Field (GOF) and introducing it into GONet, we compensate for the lack of explicit supervision in existing point cloud surface reconstruction approaches. The GOF, together with the occupancy field (OF), serves as the supervised information for neural network learning. Learning the GOF strengthens GONet’s attention to the critical points of the surface extraction algorithm Marching Cubes; thus, it helps improve the reconstructed surface’s accuracy. In addition, GONet uses the same encoder and decoder as ConvONet but designs a novel Adaptive Feature Aggregation (AFA) module to achieve an adaptive fusion of planar and volume features. The insertion of AFA allows for the obtained implicit features to incorporate more geometric and volumetric information. Both visualization and quantitative experimental results demonstrate that our GONet could handle 3D satellite reconstruction work and outperform existing state-of-the-art methods by a significant margin. With a watertight mesh, our GONet achieves 5.507 CD-L1, 0.8821 F-score, and 68.86% IoU, which is equal to gains of 1.377, 0.0466, and 3.59% over the previous methods using NASA3D, respectively.

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46

Ui, Kyoichi, Tomoyuki Urabe, Saburo Matunaga, Tomohiro Ishikawa, and Shin Satori. "Three Dimensional Microgravity Experiments of Approaching/Grasping Phase of Docking Mechanism for Nano-Satellite with Air Thruster." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 53, no. 620 (2005): 419–25. http://dx.doi.org/10.2322/jjsass.53.419.

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47

TAKEZAWA, Satoshi, Shin SATORI, and Tomohiro ISHIKAWA. "Method of Image Estimation at the Attitude in Docking for Micro Satellite Usingied Radial Basis Function Networks." Transactions of the Japan Society of Mechanical Engineers Series C 70, no. 698 (2004): 2854–61. http://dx.doi.org/10.1299/kikaic.70.2854.

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48

Kozin, Filipp, Mahdi Akhloumadi, and Danil Ivanov. "Laboratory Study of Microsatellite Control Algorithms Performance for Active Space Debris Removal Using UAV Mock-Ups on a Planar Air-Bearing Test Bed." Drones 7, no. 1 (December 22, 2022): 7. http://dx.doi.org/10.3390/drones7010007.

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In this paper, a planar air-bearing test bed with unmanned aerial vehicles (UAV) was used to test a microsatellite motion control system. The UAV mock-ups were controlled by four ventilator actuators that imitated the satellite thrusters and provided the required acceleration vector in the horizontal plane, and torque along the vertical direction. The mock-ups moved almost without friction along the planar air-bearing test bed due to the air cushion between the test bed surface and the flat mock-up base. The motion of the mock-ups motion imitated the motion of satellites in the orbital plane. The problem of space debris can be solved using special microsatellite missions able to dock to space debris objects and change their orbit. In this paper, two control algorithms based on the virtual potentials approach and the State Dependent Ricatti Equation (SDRE) controller, were proposed for docking to a non-cooperative space debris object. The algorithms were tested in a laboratory facility, and the results are presented and analyzed, including their main features demonstrated during the laboratory study. It was shown that the SDRE-based control was faster, although the virtual potential-based control required less characteristic velocity.

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49

Zuehlke, David, Madhur Tiwari, Khalid Jebari, and Krishna Bhavithavya Kidambi. "Rendezvous and Proximity Operations in Cislunar Space Using Linearized Dynamics for Estimation." Aerospace 10, no. 8 (July 28, 2023): 674. http://dx.doi.org/10.3390/aerospace10080674.

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As interest in Moon exploration grows, and efforts to establish an orbiting outpost intensify, accurate modeling of spacecraft dynamics in cislunar space is becoming increasingly important. Contrary to satellites in Low Earth Orbit (LEO), where it takes around 5 ms to communicate back and forth with a ground station, it can take up to 2.4 s to communicate with satellites near the Moon. This delay in communication can make the difference between a successful docking and a catastrophic collision for a remotely controlled satellite. Moreover, due to the unstable nature of trajectories in cislunar space, it is necessary to design spacecraft that can autonomously make frequent maneuvers to stay on track with a reference orbit. The communication delay and unstable trajectories are exactly why autonomous navigation is critical for proximity operations and rendezvous and docking missions in cislunar space. Because spacecraft computational hardware is limited, reducing the computational complexity of navigational algorithms is both desirable and often necessary. By the introduction of a linear system approach to the deputy spacecraft motion, this research avoids the computational burden of integrating the deputy relative equations of motion. In this research, the relative CR3BP equations of motion are derived and linearized using a matrix exponential approximation. This research continues the development of the matrix exponential linearized relative circular restricted three-body problem (CR3BP) equations by applying the dynamics model to estimation and control applications. A simulation is performed to compare state estimation results obtained from using the linearized equations of motion utilizing a Kalman filter and for state estimation utilizing an unscented Kalman filter with the full nonlinear equations of motion. The linearized exponential model is shown to be sufficient for state estimation in the presence of noisy measurements for an example scenario. Additionally, a linear quadratic regulator (LQR) controller was added to optimally control a deputy spacecraft to rendezvous with a chief spacecraft in cislunar space. The contribution of this work is twofold: to provide a proof of concept that the matrix exponential solution for the linearized relative CR3BP equations can be used as the dynamics model for state estimation, as well as to simulate an optimal rendezvous maneuver in the presence of measurement noise.

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50

Guo, Xin, Shiyao Zhu, Guanri Liu, Bin Yu, Qiaofei Zhang, and Yongjun Lei. "Nonlinear Static Analysis and Structural Optimization of Rigid Clamp Band Connection Device between Launch Vehicle and Satellite." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 38, no. 5 (October 2020): 1122–28. http://dx.doi.org/10.1051/jnwpu/20203851122.

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The Rigid Clamp Band Connection Device (RCBCD) is a novel satellite-rocket connection method adapted to the heavy lift trend of the launch vehicle. The static analysis model for the Rigid Clamp Band (RCB) and the Docking Ring (DR) under preloading state is established, and the structural strength and connection stiffness characteristics under the axial loading are analyzed, and the axisymmetric equivalent and parametric modeling techniques are combined to optimize the section shape parameter, which improves the overall connection performance. The results show that the structural stress concentrated on the "line-to-face" contact position between RCB and DR. Increasing the axial dimension of RCB, reducing the V-type angle and deepening the occlusion depth of RCB and DR can effectively improve the connection rigidity of RCB. By optimizing the section shape, the connection performance of RCBCD can be improved by above 70% under the structural strength and mass constraints.

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