Relevant bibliographies by topics / Satellite docking

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Satellite docking'

Author: Grafiati
Published: 6 September 2023

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Journal articles on the topic "Satellite docking"

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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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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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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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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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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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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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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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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 connection can be realized in the general initial conditions.
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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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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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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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Dissertations / Theses on the topic "Satellite docking"

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Mienie, Dewald. "Autonomous docking for a satellite pair using monocular vision." Thesis, Stellenbosch : University of Stellenbosch, 2009. http://hdl.handle.net/10019.1/2382.

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Thesis (MEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2009.
Autonomous rendezvouz and docking is seen as an enabling technology. It allows, among others, the construction of larger space platforms in-orbit and also provides a means for the in-orbit servicing of space vehicles. In this thesis a docking sequence is proposed and tested in both simulation and practice. This therefore also requires the design and construction of a test platform. A model hovercraft is used to emulate the chaser satellite in a 2-dimensional plane as it moves relatively frictionlessly. The hovercraft is also equipped with a single camera (monocular vision) that is used as the main sensor to estimate the target’s pose (relative position and orientation). An imitation of a target satellite was made and equipped with light markers that are used by the chaser’s camera sensor. The position of the target’s lights in the image is used to determine the target’s pose using a modified version ofMalan’s Extended Kalman Filter [20]. This information is then used during the docking sequence. This thesis successfully demonstrated the autonomous and reliable identification of the target’s lights in the image, and the autonomous docking of a satellite pair using monocular camera vision in both simulation and emulation.
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Miller, Duncan Lee. "Development of resource-constrained sensors and actuators for in-space satellite docking and servicing." Thesis, Massachusetts Institute of Technology, 2015. http://hdl.handle.net/1721.1/98697.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 171-177).
Most satellites on-orbit today are not intended to physically approach or interact with other spacecraft. However, the robotic servicing of orbiting assets will be an economically desirable (and often scientifically necessary) capability in future space enterprises. With the right set of tools and technologies, satellites will be able to autonomously refuel, repair, or replace each other. This has the potential to extend mission lifetimes, reduce orbital debris and make space more sustainable. Spacecraft may also assemble on-orbit into larger aggregate spaceflight systems, with applications to sparse aperture telescopes, solar power stations, fuel depots and space habitats. The purpose of this thesis is to address the highest risk elements associated with the docking and servicing of satellites: the sensors, actuators, and associated algorithms. First, a peripheral agnostic robotics platform is introduced, upon which a suite of technology payloads may be developed. Next, a flight qualified docking port for small satellites is presented, and the results detailing its operation in a relevant environment are discussed. In addition, we review a high precision relative sensor designed to enable boresight visual docking. The measurements from this optical camera are applied to a nonlinear estimator to provide the highly accurate sensing necessary for docking. Finally, a free-flying robotic arm is examined and modeled as an experimental payload for the SPHERES Facility on the International Space Station.
by Duncan Lee Miller.
S.M.
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Nolet, Simon 1975. "Development of a guidance, navigation and control architecture and validation process enabling autonomous docking to a tumbling satellite." Thesis, Massachusetts Institute of Technology, 2007. http://hdl.handle.net/1721.1/39697.

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Thesis (Sc. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2007.
Includes bibliographical references (p. 307-324).
The capability to routinely perform autonomous docking is a key enabling technology for future space exploration, as well as assembly and servicing missions for spacecraft and commercial satellites. Particularly, in more challenging situations where the target spacecraft or satellite is tumbling, algorithms and strategies must be implemented to ensure the safety of both docking entities in the event of anomalies. However, difficulties encountered in past docking missions conducted with expensive satellites on orbit have indicated a lack of maturity in the technologies required for such operations. Therefore, more experimentation must be performed to improve the current autonomous docking capabilities. The main objectives of the research presented in this thesis are to develop a guidance, navigation and control (GN&C) architecture that enables the safe and fuel-efficient docking with a free tumbling target in the presence of obstacles and anomalies, and to develop the software tools and verification processes necessary in order to successfully demonstrate the GN&C architecture in a relevant environment. The GN&C architecture was developed by integrating a spectrum of GN&C algorithms including estimation, control, path planning, and failure detection, isolation and recovery algorithms.
(cont.) The algorithms were implemented in GN&C software modules for real-time experimentation using the Synchronized Position Hold Engage and Reorient Experimental Satellite (SPHERES) facility that was created by the MIT Space Systems Laboratory. Operated inside the International Space Station (ISS), SPHERES allow the incremental maturation of formation flight and autonomous docking algorithms in a risk-tolerant, microgravity environment. Multiple autonomous docking operations have been performed in the ISS to validate the GN&C architecture. These experiments led to the first autonomous docking with a tumbling target ever achieved in microgravity. Furthermore, the author also demonstrated successful docking in spite of the presence of measurement errors that were detected and rejected by an online fault detection algorithm. The results of these experiments will be discussed in this thesis. Finally, based on experiments in a laboratory environment, the author establishes two processes for the verification of GN&C software prior to on-orbit testing on the SPHERES testbed.
by Simon Nolet.
Sc.D.
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Antonello, Andrea. "Design of a robotic arm for laboratory simulations of spacecraft proximity navigation and docking." Doctoral thesis, Università degli studi di Padova, 2017. http://hdl.handle.net/11577/3426208.

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The increasing number of human objects in space has laid the foundation of a novel class of orbital missions for servicing and maintenance. The main goal of this thesis is the development, building and testing of a robotic manipulator for the simulation of orbital maneuvers, with particular attention to Active Debris Removal (ADR) and On-Orbit Servicing (OOS). There are currently very few ways to reproduce microgravity in a non-orbital environment: among the main techniques, it is worth mentioning parabolic flights, pool simulations and robotic facilities. Parabolic flights allow to reproduce orbital conditions quite faithfully, but simulation conditions are very constraining. Pool simulations, on the other hand, have fewer constrictions in terms of cost, but the drag induced by the water negatively affects the simulated microgravity. Robotic facilities, finally, permit to reproduce indirectly (that is, with an appropriate control system) the physics of microgravity. State of the art on 3D robotic simulations is nowadays limited to industrial robots facilities, that bear conspicuous costs, both in terms of hardware and maintenance. This project proposes a viable alternative to these costly structures. Through dedicated algorithms, the system is able to compute in real time the consequences of these contacts in terms of trajectory modifications, which are then fed to the hardware in the loop (HIL) control system. Moreover, the governing software can be commanded to perform active maneuvers and relocations: as a consequence, the manipulator can be used as the testing bench not only for orbital servicing operations but also for attitude control systems, providing a faithful, real-time simulation of the zero-gravity behavior. Furthermore, with the aid of dynamic scaling laws, the potentialities of the facility can be exponentially increased: the simulation environment is not longer bounded to be as big as the robot workspace, but could be several orders of magnitude bigger, allowing for the reproduction of otherwise preposterous scenarios. The thesis describes the detailed mechanical design of the facility, corroborated by structural modeling, static and vibrational finite element verification. A strategy for the simulation of impedance-matched contacts is presented and an analytical control analysis defines the set of allowable inertial properties of the simulated entities. Focusing on the simulation scenarios, an innovative information theoretic approach for simultaneous localization and docking has been designed and applied for the first time to a 3D rendezvous scenario. Finally, in order to instrument the facility’s end effector with a consistent sensor suite, the design and manufacturing of an innovative Sun sensor is proposed.
Il crescente numero di oggetti umani nello spazio ha posto le basi per una nuova classe di missioni orbitali per l'assistenza e la manutenzione. L'obiettivo principale di questa tesi è lo sviluppo, la costruzione e la verifica sperimentale di un manipolatore robotico per la simulazione di manovre orbitali, con particolare attenzione alla rimozione di detriti (ADR) e la manutenzione in orbita (OOS). Allo stato dell'arte, sono poche le modalità utilizzate per la riproduzione della microgravità in un ambiente non-orbitale: fra le tecniche principali, vale la pena ricordare voli parabolici, simulazioni in piscina e simulatori robotici. I voli parabolici consentono di riprodurre le condizioni orbitali abbastanza fedelmente, ma le condizioni di simulazione sono pesantemente vincolanti. Le simulazioni in piscina, d'altra parte, hanno meno costrizioni in termini di costo, ma la resistenza indotta dall'acqua influisce negativamente sulla qualità della microgravità simulata. Gli impianti robotizzati, infine, permettono di riprodurre indirettamente (cioè attraverso un adeguato sistema di controllo) la fisica della microgravità. Lo stato dell'arte sulle simulazioni robotiche 3D è oggi limitato a robot industriali, caratterizzati da notevoli costi sia in termini di hardware che di manutenzione. Questo progetto propone un'alternativa a queste strutture: attraverso algoritmi dedicati, il sistema è in grado di calcolare in tempo reale le conseguenze dei contatti tramite le opportune modifiche alla traiettoria, che vengono poi fornite al sistema di controllo "hardware in the loop" (HIL). Inoltre, il software può essere comandato per eseguire manovre attive e di "relocation": di conseguenza, il manipolatore può essere utilizzato come test-bed non solo per operazioni di manutenzione orbitale, ma anche per sistemi di controllo di assetto, fornendo una fedele simulazione in tempo reale del rispettivo comportamento in assenza di gravità. La tesi descrive la progettazione meccanica dettagliata della struttura, corroborata dalla rispettiva modellazione strutturale, e dalla verifica agli elementi finiti delle prestazioni statiche e vibrazionali. Viene successivamente presentata una strategia per la simulazione di contatti tramite il matching tra le impedenze e un controllore dedicato definisce l'insieme delle proprietà inerziali simulabili tramite la struttura. Concentrandosi sugli scenari di simulazione, viene poi presentato un innovativo approccio SLAM (simultaneous localization and mapping) che utilizza metodi stocastici per il design di traiettorie di ispezione e riconoscimento markers applicato ad un task di rendez-vous 3D. Infine, con l'obiettivo di fornire una sensor-suite capace di stimare in real-time l'assetto dell'end-effector, viene descritto un innovativo sensore di Sole miniaturizzato. Ne vengono discusse la progettazione e la fabbricazione, corroborate dalle necessarie verifiche sperimentali.
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Mastromarco, Vincenzo. "Studio preliminare di un satellite per la cattura multipla di detriti spaziali attraverso meccanismo a rete." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2018. http://amslaurea.unibo.it/15667/.

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Studio preliminare di una forma di satellite che possa effettuare una missione multi target nella quale eliminare più detriti, tutti situati nelle orbite basse. Si è iniziato studiando il meccanismo a rete, una delle tante tipologie di meccanismi che permettono di andare a catturare detriti o satelliti non più in funzione in orbita. Si è poi iniziato il processo di ideazione, che ha previsto un processo di esclusione, arrivando a delle soluzioni finali accettabili. Un punto fondamentale nella ideazione della struttura del satellite è stato considerare la creazione di un satellite in grado di trasportare più detriti contemporaneamente durante l'intera missione, in modo da risparmiare carburante. Per calcolarne il consumo si sono ipotizzati due scenari differenti: nel primo il satellite scendeva ad una bassa quota, per rilasciare in atmosfera il detrito, ad ogni cattura; nel secondo il satellite scendeva solo quando tutti i detriti erano stati catturati, evitando di effettuare più manovre.
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Fejzić, Amer. "Development of control and autonomy algorithms for docking to complex tumbling satellites." Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/46369.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2008.
This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
MIT Institute Archives copy: with DVD; divisional library copy with no DVD.
Includes bibliographical references (p. 171-173).
The capability of automated rendezvous and docking is a key enabling technology for many government and commercial space programs. Future space systems will employ a high level of autonomy to acquire, repair, refuel, and reconfigure satellites. Several programs have demonstrated a subset of the necessary autonomous docking technology; however, none has demonstrated online path planning in-space necessary for safe automated docking. Particularly, when a docking mission is sent to service an uncooperative spacecraft that is freely tumbling. In order to safely maneuver about an uncontrolled satellite, an online trajectory planning algorithm with obstacle avoidance employed in a GN&C architecture is necessary. The main research contributions of this thesis is the development of an efficient sub-optimal path planning algorithm coupled with an optimal feedback control law to successfully execute safe maneuvers for docking to tumbling satellites. First, an autonomous GN&C architecture is presented that divides the docking mission into four phases, each uniquely using the algorithms within to perform their objectives. For reasons of safety and fuel efficiency, a new sub-optimal spline-based trajectory planning algorithm with obstacle avoidance of the uncooperative spacecraft is presented. This algorithm is shown to be computationally efficient and computes desirable trajectories to a complex moving docking port of the tumbling spacecraft. As a realistic space system includes external disturbances and noises in sensor measurement and control actuation, a closed-loop form of control is necessary to maneuver the spacecraft. Therefore, several optimal feedback control laws are developed to track a trajectory provided by the path planner. Performance requirements for the tracking controllers are defined for the case of two spacecraft docking. With these requirements, the selection of a controller is narrowed down to a phase-plane switching between LQR and servo-LQR control laws.
(cont.) The autonomous GN&C architecture with the spline-based path planning algorithm and phase-plane controller is validated with simulations and hardware experiments using the Synchronized Position Hold Engage and Reorient Satellites (SPHERES) testbed aboard the International Space Station (ISS). Utilizing the unique space environment provided by the ISS, the experiment is the first in-space demonstration of an online path planning algorithm. Both the flight and simulation tests successfully validated the capabilities of the autonomous control system to dock to a complex tumbling satellite. The contributions in this thesis advance and validate a GN&C architecture that builds on a legacy in autonomous docking of spacecraft.
by Amer Fejzić.
S.M.
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Porter, Robert D. "Development and control of the Naval Postgraduate School Planar Autonomous Docking Simulator (NPADS) /." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02sep%5FPorter.pdf.

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Thesis (M.S. in Astronautical Engineering)--Naval Postgraduate School, September 2002.
Thesis advisor(s): Michael G. Spencer, Brij N. Agrawal. Includes bibliographical references (p. 83). Also available online.
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Olivieri, Lorenzo. "Development and characterization of a standardized docking system for small spacecraft." Doctoral thesis, Università degli studi di Padova, 2015. http://hdl.handle.net/11577/3423898.

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Since the first mating manoeuvre in space, performed in 1966, many different docking mechanisms were developed, mainly for large manned spacecraft. The few systems recently conceived for small satellites have never been verified in space nor scaled to CubeSat size. In the near future, small spacecraft docking procedures could acquire great importance due to the need to share resources between clusters of low-weight and low-cost vehicles: in fact, small spacecraft market is rapidly growing, focusing on commercial low risk application, low budget scientific and educational missions. In this context, this document presents a novel docking mechanism to provide small spacecraft with the ability to join and separate in space, to realize multi-body platforms able to rearrange, be repaired or updated, thus overcoming the actual on board limitations of single small-scale satellites. As for now, the few proposed docking ports present (1) simple probe-drogue interfaces, unable to dock with same-gender ports, or (2) androgynous geometries, that can overcome that problem, but usually employing complex and non-axis-symmetric latches to perform the docking manoeuvre, that would demand robust and stringent navigation and control systems. The proposed solution overcomes the aforementioned drawbacks, using a semi-androgynous shape-shifting mechanism that actuating one interface changes the port into a “drogue" configuration, letting the other port penetrate it and closing around to create a solid joint. The mechanism design through the requirement definition and a trade-off between different concepts is presented, followed by the analysis of the dynamic behaviour of the selected solution, with particular attention to two aspects, i.e. the loads transmitted between the mating ports and the alignment tolerances requested to perform successful docking manoeuvres. Such analysis led to the definition of an instrumented prototype to verify the solution through simple validation tests, which demonstrated the mechanism operations and defined the alignment ranges, that lie in the range of +- 15 mm and up to 6 degrees. Last, a comparison with SPHERES UDP is presented, as part of the activities performed during a visit period at MIT Space Systems Laboratory.
Fin dalla prima manovra di ancoraggio avvenuta nel 1966, molti e differenti meccanismi di docking sono stati sviluppati, per lo più per satlliti dotati di equipaggio. I pochi sistemi recentemente concepiti per piccoli satelliti non sono mai stati testati in spazio né scalati alle dimensioni adeguate per essere installati su CubeSat. Nel prossimo futuro, vi potrebbe essere un crescente interesse nello sviluppo di adeguate procedure di docking per piccoli veicoli, per realizzare strutture interdipendenti di satelliti, capaci di distribuire e condividere le proprie risorse: infatti, il mercato relativo a tali veicoli è in continua e costante crescita, concentrandosi su applicazioni commerciali a basso rischio e missioni scientifiche o educazionali a basso costo. In questo contesto, questo documento presenta un innovativo meccanismo di docking, capace di dare ai piccoli satelliti la capacità di agganciarsi e separarsi nello spazio, consentendo la realizzazione di piattaforme multicomponente intercambiabili, autoriparabili e aggiornabili tramite l'aggiunta di nuovi moduli, così da superare gli attuali limiti tecnologici imposti dalle limitate risorse disponibili a bordo dei singoli satelliti. Le interfaccie di docking fino ad ora realizzate presentano (1) sistemi maschio-femmina assai semplici ma ovviamente incapaci di agganciarsi a porte dello stesso genere, o (2) geometrie androgine, che pur evitando tale problematica risultano utilizzarre meccanismi complessi e non assialsimmetrici, richiedendo quindi strategie di navigazione e controllo d'assetto molto complicate e robuste. La soluzione proposta vuole superare le limitiazioni precedentemente menzionate, utilizzando un meccanismo muta-forma semiandrogino, capace di cambiare la forma dell'interfaccia in "femmina" così da consentire la penetrazione da parte di una porta equivalente ma non attuata, catturandola e realizzando l'aggancio. La progettazione del meccanismo ha seguito un processo logico, dalla definizione di una serie di requisiti al confronto tra soluzioni concettuali concorrenti, per concludersi con l'analisi del suo comportamento dinamico, dedicando particolare attenzione a due aspetti critici, la trasmissione dei carichi e le tolleranze di allineamento richieste durante una manovra di docking. Tali analisi sono state seguite dalla realizzazione di un prototipo instrumentato, utilizzato per verificare in laboratorio la funzionalità del meccanismo e definire precisamente i valori di tali tolleranze, che giacciono in un intervallo di discostamenti compreso tra +-15 mm e 6 gradi. Infine, un paragone con l'interfaccia UDP di SPHERES viene brevemente presentato, all'interno di una più ampia descrizione delle attività condotte durante un periodo di visita presso lo Space Systems Laboratory del Massachusetts Institute of Technology.
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Bondoky, Karim [Verfasser], Klaus [Gutachter] Janschek, and Stefanos [Gutachter] Fasoulas. "A Contribution to Validation and Testing of Non-Compliant Docking Contact Dynamics of Small and Rigid Satellites Using Hardware-In-The-Loop Simulation / Karim Bondoky ; Gutachter: Klaus Janschek, Stefanos Fasoulas." Dresden : Technische Universität Dresden, 2020. http://d-nb.info/122783313X/34.

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"Small Satellite Electromagnetic Docking System Modeling and Control." Master's thesis, 2018. http://hdl.handle.net/2286/R.I.49051.

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abstract: There is a growing need for interplanetary travel technology development. There are hence plans to build deep space human habitats, communication relays, and fuel depots. These can be classified as large space structures. To build large structures, it is essential that these are modular in nature. With modularization of structures, it becomes essential that interconnection of modules is developed. Docking systems enable interconnection of modules. The state-of-the-art technology in docking systems is the Power Data Grapple Fixture (PDGF), used on the International Space Station by the Canadarm2 robotic arm to grapple, latch onto and provide power to the object it has grappled. The PDGF is operated by highly skilled astronauts on the ISS and are prone to human errors. Therefore, there is a need for autonomous docking. Another issue with the PDGF is that it costs around 1 to 2 million US dollars to build the 26-inch diameter docking mechanism. Hence, there is a growing need to build a lower cost and scalable, smaller docking systems. Building scalable smaller docking systems will hence enable testing them on small satellites. With the increasing need for small, low cost, autonomous docking systems, this thesis has been proposed. This thesis focuses on modeling and autonomous control of an electromagnetic probe and cone docking mechanism. The electromagnetic docking system is known to be a highly nonlinear system. Hence, this work discusses various control strategies for this docking system using a levitation strategy.
Dissertation/Thesis
Masters Thesis Electrical Engineering 2018
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Books on the topic "Satellite docking"

1

Fehse, Dr Wigbert. Automated Rendezvous and Docking of Spacecraft (Cambridge Aerospace Series). Cambridge University Press, 2008.

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Book chapters on the topic "Satellite docking"

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Wei, Wang, Chai Qiang, Gao Weiguang, Lu Jun, Shao Shihai, Bai Yu, Niu Jingyi, Feng Wenjing, and Li Shaoqian. "The Design and Implementation of Global Navigation Satellite System Remote Docking Test Platform." In Wireless and Satellite Systems, 247–58. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-69072-4_21.

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Jarzebowska, Elzbieta, and Michal Szwajewski. "A Docking Maneuver Scenario of a Servicing Satellite—Quaternion-Based Dynamics and Control Design." In Springer Proceedings in Mathematics & Statistics, 181–96. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-42402-6_16.

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Dunlap, Kyle, Kelly Cohen, and Kerianne Hobbs. "Comparing the Explainability and Performance of Reinforcement Learning and Genetic Fuzzy Systems for Safe Satellite Docking." In Explainable AI and Other Applications of Fuzzy Techniques, 116–29. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-82099-2_11.

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Silahtar, Onur, Fatih Kutlu, Özkan Atan, and Oscar Castillo. "Rendezvous and Docking Control of Satellites Using Chaos Synchronization Method with Intuitionistic Fuzzy Sliding Mode Control." In Fuzzy Logic and Neural Networks for Hybrid Intelligent System Design, 177–97. Cham: Springer International Publishing, 2023. http://dx.doi.org/10.1007/978-3-031-22042-5_10.

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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." In Automatic Control in Aerospace 1994 (Aerospace Control '94), 303–8. Elsevier, 1995. http://dx.doi.org/10.1016/b978-0-08-042238-1.50051-3.

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Conference papers on the topic "Satellite docking"

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Wiens, Gloria J., Anake Umsrithong, Shawn Miller, Aneesh Koka, and Travis Vitello. "Design of Autonomous Foldable Docking Mechanism for Small Space Vehicles." In ASME 2009 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2009. http://dx.doi.org/10.1115/detc2009-87678.

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Over the past decade, small satellites have gained the interest of the space industry as a new and cost effective approach for servicing space assets. To address the special constraints inherent to the component miniaturization required for these satellites, researchers in the Space, Automation and Manufacturing Mechanisms Laboratory (SAMM) are exploring foldable mechanisms and their effectiveness for providing autonomous rendezvous and docking capabilities for small space vehicles. This paper focuses particularly on the design of autonomous docking mechanisms for space vehicles within the small satellite class known as picosatellite (size and mass requirements: 1 kilogram mass within a 10×10×10 centimeter cube). The docking mechanisms deployment scenario is a dual satellite system comprised of two small satellites (a chaser and a target). The chaser has attitude and translational control capability, while the target is a passive satellite having only attitude stabilization capability. This paper will first present a review of the existing docking mechanism technology utilized in space. This is followed by details of a foldable mechanism approach for providing small satellites autonomous docking capabilities. This includes geometric and dynamic analysis conducted in ADAMS software simulations.
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Ritter, Greg, Anthony Hays, Greg Wassick, Greg Sypitkowski, Carl Nardell, Pete Tchory, and Jane Pavlich. "Autonomous satellite docking system." In AIAA Space 2001 Conference and Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-4527.

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Reiter, Joel, Mason Terry, Karl F. Böhringer, John W. Suh, and Gregory T. A. Kovacs. "Thermo-Bimorph Microcilia Arrays for Small Spacecraft Docking." In ASME 2000 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/imece2000-1071.

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Abstract Microelectromechanical system (MEMS) technology promises to improve performance of future spacecraft components while reducing mass, cost, and manufacture time. Arrays of microcilia actuators offer a lightweight alternative to conventional docking systems for miniature satellites. Instead of mechanical guiding structures, such a system uses a surface tiled with MEMS actuators to guide the satellite to its docking site. This paper describes an experimental setup for precision docking of a “picosatellite” with the help of MEMS cilia arrays. Microgravity is simulated with an aluminum puck on an airtable. A series of experiments is performed to characterize the cilia, with the goal to understand the influence of normal force, picosat mass, docking velocity, cilia frequency, interface material, and actuation strategy (“gait”) on the performance of the MEMS docking system. We demonstrate a 4 cm2 cilia array capable of docking a 45 gram picosat with a 2 mm2 contact area at micrometer precision. It is concluded that current MEMS cilia arrays are useful to position and align miniature satellites with up to several kg of mass.
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Erdem, Y., Aras M. Numan Uyar, Mahmut C. Soydan, M. Selahaddin Harmankaya, Furkan Alan, and Burak Akbulut. "Developing and modelling of satellite docking algorithm." In 2017 8th International Conference on Recent Advances in Space Technologies (RAST). IEEE, 2017. http://dx.doi.org/10.1109/rast.2017.8002987.

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Ma, Ou, Angel Flores-Abad, and Toralf Boge. "Using Industrial Robots for Hardware-in-the-Loop Simulation of Spacecraft Rendezvous and Docking." In ASME 2012 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/detc2012-70917.

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One of the most challenging and risky operations for spacecraft is to perform proximity Rendezvous and Docking (R&D) autonomously in space. To ensure a safe and reliable operation, such a mission must be carefully designed and thoroughly verified before a real space mission can be launched. This paper describes the control strategy for achieving high fidelity contact dynamics simulation of a new, robotics-based, hardware-in-the-loop (HIL) R&D simulation facility which uses two industrial robots to simulate the 6-DOF dynamic maneuvering of the two docking satellites. The facility is capable of physically simulating the final approaching within a 25-meter range and the entire docking or capturing process in a satellite on-orbit servicing mission. The paper discusses the difficulties of using industrial robots for HIL contact dynamics simulation and the proposed robot control strategy for dealing with these difficulties.
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Mokuno, Masaaki, Isao Kawano, Hiroshi Horiguchi, and Koichi Kibe. "Engineering Test Satellite VII Rendezvous Docking optical sensor system." In Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-3689.

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Prabhakar, Nirmit, Madhar Tiwari, Troy Henderson, and Richard J. Prazenica. "Application of Direct Adaptive Control to Autonomous Satellite Docking." In AIAA Scitech 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-1520.

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Hays, Anthony B., Peter Tchoryk, Jr., Jane C. Pavlich, Greg A. Ritter, and Gregory J. Wassick. "Advancements in design of an autonomous satellite docking system." In Defense and Security, edited by Peter Tchoryk, Jr. and Melissa Wright. SPIE, 2004. http://dx.doi.org/10.1117/12.537767.

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Hays, Anthony B., Peter Tchoryk, Jr., Jane C. Pavlich, and Gregory Wassick. "Dynamic simulation and validation of a satellite docking system." In AeroSense 2003, edited by Peter Tchoryk, Jr. and James Shoemaker. SPIE, 2003. http://dx.doi.org/10.1117/12.497150.

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Dunlap, Kyle, Mark Mote, Kai Delsing, and Kerianne L. Hobbs. "Run Time Assured Reinforcement Learning for Safe Satellite Docking." In AIAA SCITECH 2022 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2022. http://dx.doi.org/10.2514/6.2022-1853.

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