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Journal articles on the topic 'Satellite docking'

Author: Grafiati

Published: 6 September 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 (2023): 012020. http://dx.doi.org/10.1088/1742-6596/2569/1/012020.

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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, u

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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 (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 conne

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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 (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 s

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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 cal

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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 (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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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 connecti

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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 (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 navigatio

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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 (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 (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 (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 rende

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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 (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.

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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 (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 launch

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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 o

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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 (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 (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 sat

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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 (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 orb

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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

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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, et al. "Outcomes of the PERIOD project on In-Space Manufacturing, Assembly and Refuelling Technologies." Journal of Physics: Conference Series 2526, no. 1 (2023): 012121. http://dx.doi.org/10.1088/1742-6596/2526/1/012121.

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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 exi

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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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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

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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 (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 (2014): 666–81. http://dx.doi.org/10.1177/0954410014539290.

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34

Dhanalakshmi, R., N. P. G. Bhavani, S. Srinivasulu Raju, et al. "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

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35

Hartley, Craig. "Simulating Satellite Retrieval Missions Using the Manned Maneuvering Unit." Journal of the IEST 28, no. 2 (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 r

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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

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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 (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, et al. "Guidance, Navigation and Control System in Engineering Test Satellite VII Rendez-Vous and Docking Experiment." IFAC Proceedings Volumes 27, no. 13 (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 (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

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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, et al. "WDR8 is a centriolar satellite and centriole-associated protein that promotes ciliary vesicle docking during ciliogenesis." Journal of Cell Science 129, no. 3 (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 base

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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 (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 datas

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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 (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.

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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 (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

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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 (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 concent

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