Bibliografías temáticas / Asteroid Landing

Literatura académica sobre el tema "Asteroid Landing"

Autor: Grafiati
Publicado: 6 de septiembre de 2023

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Artículos de revistas sobre el tema "Asteroid Landing"

1

Yan, Weifeng, Ruoyu Feng y Hexi Baoyin. "Stability of a Flexible Asteroid Lander with Landing Control". Aerospace 9, n.º 11 (16 de noviembre de 2022): 719. http://dx.doi.org/10.3390/aerospace9110719.

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Stable landing on asteroids is of considerable scientific and economic value but accompanied by huge difficulties. This paper proposes a novel flexible lander suitable for asteroids with microgravity and rugged surface. The gravity model with the artificial neural network and the surface model with the spherical harmonic method are introduced to establish the target asteroid’s dynamical environment. The flexible dynamics with the discrete shell model, the collision with the spring-damping model and viscous sliding friction, and the rigid coupling with the constraint violation stabilization method are elaborated for the lander. Combining the asteroid’s model with the lander’s dynamics, one successful landing scenario of the lander is presented. The lander’s landing stability of the final uncontrolled touching phase is studied through massive simulations. It is found that reasonable touching conditions can largely enhance the landing stability, and the lander can achieve a stable landing on the asteroid under a particular touching condition without control. The flexible lander’s comparison to the rigid lander is also discussed. It is concluded that the flexible lander does have higher adaptability and lower risk in asteroid landing. What is more, the attitude controller and position controller for the lander’s descent phase are also proposed and tested.
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2

Chen, Danhe, Chuangyi Li y Zhou Su. "Dynamics Research and Analysis of landing on the surface of Asteroid". Journal of Physics: Conference Series 2472, n.º 1 (1 de mayo de 2023): 012033. http://dx.doi.org/10.1088/1742-6596/2472/1/012033.

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Abstract Asteroid detection has been the main research field of deep space exploration, and even in the future years. Countries have carried out missions to flyby and landing on the surface of asteroids, the sampling can help human explore the origins of small bodies, as well as origin of the solar system. While the particular environmental factors such as small size and low gravity of asteroids make the landing more difficult, this paper designs a four-legged inverted triangle soft lander, supplemented by thrust reversers and rope anchors for stable landing. A mathematical model of the lander landing on the surface of target asteroid is established, and the motion and dynamic response of lander in different landing modes is studied, conditions and safe landing range is well defined. Results of the analysis have demonstrated the effectiveness of dynamic landing model for the proposed lander.
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Wang, R., K. Di, W. Wan, Z. Liu, Y. Wang, W. Liang, Y. Wang, X. Chen y S. Zhi. "TOPOGRAPHIC MAPPING AND ANALYSIS BASED ON 3D RECONSTRUCTION MODEL OF SIMULATED ASTEROID". ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLIII-B3-2020 (21 de agosto de 2020): 1165–70. http://dx.doi.org/10.5194/isprs-archives-xliii-b3-2020-1165-2020.

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Abstract. Asteroid exploration is of great scientific significance in understanding the evolution of the solar system. Unlike lunar missions, asteroids are far away from the earth, the communication between the spacecraft and the ground station has a large delay. Moreover, the small size, irregular shape and uneven mass distribution of asteroids further increase the difficulty of landing missions. This paper presented a topographic mapping and analysis method based on three-dimensional (3D) reconstruction model of a simulated asteroid. First, 3D reconstruction of a simulated asteroid was achieved using Structure from Motion (SfM) technique. Then Digital Elevation Model (DEM) and Digital Orthophoto Map (DOM) were produced based on the 3D point cloud data. By analysing the DEM data, we finally obtained the obstacles distribution map. In order to verify the proposed method, we used a simulated asteroid to conduct experiments. And the experimental results demonstrated the effectiveness of the developed method. The topographic mapping and analysis method presented in this study can be applied to landing/sampling area selection in further asteroid exploration research.
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Wang, Weimin y K. L. Yung. "Analysis of a Mechanical Anchoring System for Landing on Asteroids". Journal of Physics: Conference Series 2542, n.º 1 (1 de julio de 2023): 012017. http://dx.doi.org/10.1088/1742-6596/2542/1/012017.

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Abstract The landing process to an asteroid is discussed with a Nimble Lander. The miniature harpoons are chosen as the anchoring device to landing to asteroid in the Nimble Lander. The analysis results provide detailed information of the anchoring with harpoon as anchoring device. Many different designs of harpoon have been tested by simulation, the best of three designs of harpoon are analyzed for anchoring to Apophis. Instead of the modelling of the anchor as a rigid cylindrical projectile in penetration models, the deformation of the harpoon is fully considered in the anchoring analysis. The analysis provides ground base a reliable design anchoring system for landing to Asteroids.
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5

Guo, Yundong, Jeng-Shyang Pan, Chengbo Qiu, Fang Xie, Hao Luo, Huiqiang Shang, Zhenyu Liu y Jianrong Tan. "SinGAN-Based Asteroid Surface Image Generation". Journal of Database Management 32, n.º 4 (octubre de 2021): 28–47. http://dx.doi.org/10.4018/jdm.2021100103.

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While it is risky considering spacecraft constraints and unknown environment on asteroid, surface sampling is an important technique for asteroid exploration. One of the sample return missions is to seek an optimal landing site, which may be in hazardous terrain. Since autonomous landing is particularly challenging, it is necessary to simulate the effectiveness of this process and prove the onboard optical hazard avoidance is robust to various uncertainties. This paper aims to generate realistic surface images of asteroids for simulations of asteroid exploration. A SinGAN-based method is proposed, which only needs a single input image for training a pyramid of multi-scale patch generators. Various images with high fidelity can be generated, and manipulations such as shape variation, illumination direction variation, super resolution generation are well achieved. The method's applicability is validated by extensive experimental results and evaluations. At last, the proposed method has been used to help set up a test environment for landing site selection simulation.
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6

Yongbin, Wang, Jiang Wansong, Long Long, Zhu Qian, Feng Rui y Wang Liwu. "Design and Experimental Research of a New Type of Asteroid Anchoring System". International Journal of Aerospace Engineering 2021 (18 de mayo de 2021): 1–7. http://dx.doi.org/10.1155/2021/6677877.

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Asteroid detection is of great significance to the study of the formation of the solar system and the origin of life. However, there are many types of asteroids, and they are far away from the earth, and the understanding of their various characteristics is not clear, which brings huge technical challenges to the landing and attachment of star catalogs. At present, the world is mainly based on surround, overflight, and short-term contact detection, and long-term attachment detection has not yet been realized. In order to solve the long-term attachment detection requirements of asteroids, focusing on the geological characteristics of various types of stars, this paper proposes a new type of asteroid attachment mechanism based on the beetle bionic theory, which can realize intelligent and flexible attachment and has strong adaptability. Around this design, this paper analyzes the mechanism of adhesion and realizes the adaptive matching of unascertained terrain landing point adhesion. On this basis, a prototype of the asteroid landing attachment mechanism was developed and verified by experiments. The experiment proved that the mechanism has strong multiterrain matching ability and can obtain an adhesion force of not less than 36 N on ordinary concrete ground.
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7

Zhao, Zhijun, Shuang Wang, Delun Li, Hongtao Wang, Yongbing Wang y Jingdong Zhao. "Development of an Anchoring System for the Soft Asteroid Landing Exploration". International Journal of Aerospace Engineering 2019 (7 de febrero de 2019): 1–13. http://dx.doi.org/10.1155/2019/1257038.

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The landing mechanism is easy to flow away from the surface of the asteroid, as there is nearly no gravity on the asteroid. One of the most problems for the asteroid landing exploration is to anchor the landing mechanism on the asteroid surface. In the paper, an anchoring system employed on the soft asteroid anchoring is designed. It is mainly composed of penetrating unit, advancing unit, winding unit, damping unit, and so on. On the basis of the mechanical design, the resistance characteristic of the anchor body in penetrating process is analyzed, and the shape of the anchor tip is designed with the least resistance as the constraint. Then, the validity of the anchor tip design is tested by comparing penetrating ability of different anchor tips. Finally, the penetrating and the anchoring performances of the anchoring system are tested in a variety of media.
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8

Zhao, Yingjie, Hongwei Yang y Jincheng Hu. "The Fast Generation of the Reachable Domain for Collision-Free Asteroid Landing". Mathematics 10, n.º 20 (12 de octubre de 2022): 3763. http://dx.doi.org/10.3390/math10203763.

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For the mission requirement of collision-free asteroid landing with a given time of flight (TOF), a fast generation method of landing reachable domain based on section and expansion is proposed. First, to overcome the difficulties of trajectory optimization caused by anti-collision path constraints, a two-stage collision-free trajectory optimization model is used to improve the efficiency of trajectory optimization. Second, the velocity increment under a long TOF is analyzed to obtain the distribution law of the reachable domain affected by the TOF, and the generation problem of the reachable domain is transformed into the solution problem of the initial boundary and the continuous boundary. For the initial boundary, the section method is used to acquire a point on the boundary as the preliminary reachable domain boundary. The solution of continuous boundary is based on the initial boundary continuously expanding the section into the reachable domain until the boundary is continuous. Finally, the proposed method is applied to the asteroids 101955 Bennu and 2063 Bacchus. The simulation results show that this method can quickly and accurately obtain the reachable domain of collision-free asteroid landing in a given TOF and is applicable to different initial positions.
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9

Dunham, David W., Robert W. Farquhar, James V. McAdams, Mark Holdridge, Robert Nelson, Karl Whittenburg, Peter Antreasian et al. "Implementation of the First Asteroid Landing". Icarus 159, n.º 2 (octubre de 2002): 433–38. http://dx.doi.org/10.1006/icar.2002.6911.

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Cocaud, Cedric y Takashi Kubota. "Development of an Intelligent Simulator with SLAM Functions for Visual Autonomous Landing on Small Celestial Bodies". Journal of Advanced Computational Intelligence and Intelligent Informatics 15, n.º 8 (20 de octubre de 2011): 1167–74. http://dx.doi.org/10.20965/jaciii.2011.p1167.

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As space agencies are currently looking at Near Earth Asteroids as a next step on their exploration roadmap, high precision autonomous landing control schemes will be required for upcoming missions. In this paper, an intelligent simulator is proposed to reproduce all of the visual and dynamic aspects required to test an autonomous Simultaneous Localization and Mapping (SLAM) system. The proposed simulator provides position and attitude information to a spacecraft during its approach descent and Landing phase toward the surface of an asteroid or other small celestial bodies. Because the SLAM system makes use of navigation cameras and a range sensor moving with the spacecraft as it approaches the surface, the simulator is also developed to reproduce a fully integrated 3D environment using computer graphics technology that mimics the noise, image detail and real-time performances of the navigation cameras and the range sensors. This paper describes the architecture and capability of the developed simulator and the SLAM system for which it is designed. The developed simulator is evaluated by using the specifications of the onboard sensors used in the Hayabusa spacecraft sent by JAXA/ISAS to the Itokawa asteroid in 2003.
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Tesis sobre el tema "Asteroid Landing"

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Hartmann, Jacob. "Guidance of a Small Spacecraft for Soft Landing on an Asteroid using Fuzzy Control". University of Cincinnati / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1439300900.

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2

Lin, Hui Ju y 林輝巨. "A study of missile interception and spacecraft landing on an asteroid". Thesis, 1995. http://ndltd.ncl.edu.tw/handle/80821511292622605392.

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鄭治中. "= Control design for missile interception and spacecraft landing on an asteroid". Thesis, 2000. http://ndltd.ncl.edu.tw/handle/46261331163213571017.

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Chang, Chin-Liang y 張欽亮. "NONLINEAR GUIDANCE CONTROL OF MISSILE INTERCEPTION AND SOFT- LANDING ON AN ASTEROID". Thesis, 1997. http://ndltd.ncl.edu.tw/handle/83688577641922919145.

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碩士
國立交通大學
控制工程系
85
In this thesis, we study the problems of missile interception and soft landing on an asteroid. First we employ linear stability theory to design guidance control laws for missile interception problem. Lyapunov approach is then used to enlarge the capture region. However, for the case of large capture distance and/or maneuvering target, such a guidance control law is found to fail to intercept the target. Variable structure control type guidance laws are proposed to tackle the problem. This is achieved by treating the maneuver motion of the target as unmodeled dynamics and suitably selecting the sliding surfaces. Moreover, feedback linearization type control laws are also proposed for missile interception. These two control schemes are shown to be effective in intercepting both non-maneuvering and maneuvering target. Same approaches are then employed to design the guidance control laws for the soft-landing on an asteroid. The main difference between interception and landing problems is that both aero-drag and gravitational force are concerned in landing problem but not in missile interception. Numerical simulations are presented to demonstrate the main results, which show that feedback linearization type guidance control laws provide better performance in both missile interception problem and the soft landing on an asteroid.
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5

Mathavaraj, S. "Innovative Optimal Guidance of Spacecrafts for Soft-Landing on Atmosphere-less Celestial Bodies". Thesis, 2019. https://etd.iisc.ac.in/handle/2005/4396.

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Nonlinear trajectory optimization based optimal guidance schemes are presented in this thesis for soft-landing of spacecrafts on atmosphere-less celestial bodies. First, a pseudo-spectral philosophy based multi-phase constrained fuel-optimal trajectory optimization problem for soft-landing on the closest celestial body (moon) is presented. The objective here is to find an optimal approach to successfully guide a spacecraft from the perilune of 18 km altitude of a transfer orbit to a height of 100 m over a specific landing site. The proposed approach takes into account various mission constraints in different phases from perilune to the landing site. These constraints include Phase-1 from 18 km to 7 km altitude where the lander's velocity is reduced suitably for camera imaging, Phase-2 to hold the attitude for 35 sec for vision camera processing for obtaining navigation error, and Phase-3 from the end of phase-2 to 100 m altitude over the landing site, where navigation accuracy is good (due to vision camera navigation inputs). This multi-phase constrained trajectory optimization problem has been successfully solved using the Legendre pseudo-spectral method. Owing to its computational efficiency this approach can be used as a guidance strategy using highly-efficient on-board processors that are going to be used in the not so distant future. Next, attention is focused on landing on more challenging celestial bodies such as asteroids, which are far away from earth, odd-shaped and have near-zero gravity. In parallel, attention is also focused to develop computationally efficient numerical techniques for solving nonlinear trajectory optimization problems so that those can be used as optimal guidance schemes in the upcoming processors in the very near future. Moreover, these techniques need to be fairly robust to uncertain parameters, which typically consist of uncertainties in initial conditions as well as gravitational inaccuracies of the relatively-unknown celestial body. With this motivation in mind, the Unscented Model Predictive Static Programming (U-MPSP) and a Quasi-Spectral version of it are developed in this thesis. U-MPSP is a fusion of two philosophies, namely the unscented optimal control formulation (which in turn is inspired from the unscented Kalman filter philosophy) as well as the model predictive static programming (MPSP), which is known for its computational efficiency. First, the unscented transform is utilized to construct a low-dimensional finite number of deterministic problems to cater for the infinitely-many possible values of the uncertain parameters. The philosophy of MPSP is utilized next so that the solution can be obtained in a computationally efficient manner. The resulting solution not only ensures that the mean value of the ensemble meets the terminal constraint in the sense of a hard constraint, but it also ensures that the associated co-variances are minimized. To reduce the dimension of the optimization problem even further, getting inspired by the pseudo-spectral philosophy, a Quasi-spectral version of U-MPSP (named as QS-UMPSP) is also presented next in this thesis. In QS-UMPSP design, a much lesser number of basis functions is used in the process, even though regular sampling time based large number of grid points can be selected for the associated numerical computations. As the optimization problem eventually leads to the optimal selection of coefficients of the basis functions, the overall dimension of the optimization process is significantly reduced. This is the core reason why QS-UMPSP is computationally much more efficient than U-MPSP. The significance of the U-MPSP and QS-UMPSP have been demonstrated by successfully solving the soft-landing problem on the asteroid Vesta.
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Libros sobre el tema "Asteroid Landing"

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P, Melko Joseph y United States. National Aeronautics and Space Administration., eds. Planetary and asteroid missions, getting there. Los Angeles, CA: University of California, Los Angeles, 1993.

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Publishing, Ronald. Rocket Activity for Kids: Picture Quiz Words Activity and Coloring Books 45 Activity Asteroid, Saturn, Earthgrid, Rocket, Chemical, Landing, World, Leo for Kid Ages 6-8. Independently Published, 2020.

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Capítulos de libros sobre el tema "Asteroid Landing"

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Hu, Ronghai, Xiangyu Huang y Chao Xu. "Visual Navigation Based on Nonlinear Optimization Method for Asteroid Landing". En Lecture Notes in Electrical Engineering, 3999–4011. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-8155-7_334.

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Zhang, Yingying, Jiangchuan Huang, Yang Tian y Hutao Cui. "Trajectory Design for 6-DoF Asteroid Powered Landing via Convex Optimization". En Wireless and Satellite Systems, 99–115. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-69072-4_9.

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Raharijaona, Thibaut, Guillaume Sabiron, Stephane Viollet, Nicolas Franceschini y Franck Ruffier. "Bio-inspired Landing Approaches and Their Potential Use on Extraterrestrial Bodies". En Asteroids, 221–46. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-39244-3_9.

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Bolonkin, Alexander A. "Using Asteroids for Launch/Landing, Change of Trajectory and Acceleration of Space Ships". En Asteroids, 605–32. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-39244-3_26.

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Li, Shuang. "Computer Vision Based Autonomous Navigation for Pin-Point Landing Robotic Spacecraft on Asteroids". En Intelligent Robotics and Applications, 1115–26. Berlin, Heidelberg: Springer Berlin Heidelberg, 2008. http://dx.doi.org/10.1007/978-3-540-88518-4_119.

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Yoshikawa, Kent, Stefaan Van Wal, Yuya Mimasu, Naoko Ogawa, Go Ono, Fuyuto Terui, Takanao Saiki y Yuichi Tsuda. "MINERVAI-I-1A/B asteroid rover: Deployment and landing". En Hayabusa2 Asteroid Sample Return Mission, 209–28. Elsevier, 2022. http://dx.doi.org/10.1016/b978-0-323-99731-7.00011-8.

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Kikuchi, Shota, Tomohiro Yamaguchi, Sei-ichiro Watanabe, Hikaru Yabuta, Koji Wada, Takanao Saiki, Yuto Takei, Satoshi Tanaka y Yuichi Tsuda. "Landing site selection for the Hayabusa2 mission: Pre-arrival training and post-arrival analyses". En Hayabusa2 Asteroid Sample Return Mission, 189–208. Elsevier, 2022. http://dx.doi.org/10.1016/b978-0-323-99731-7.00010-6.

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Verschuur, Gerrit L. "Craters and Tsunamis". En Impact! Oxford University Press, 1996. http://dx.doi.org/10.1093/oso/9780195101058.003.0015.

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Until the lunar explorations began in earnest in the 1960s, the Barringer crater in Arizona was believed to be one of the few, if not the only, impact crater on earth. Before the moon landings, many scientists thought that lunar craters were volcanic in origin and that the moon might be covered in a layer of volcanic dust meters thick so that astronauts would sink up to their eyeballs when disembarking from their space capsules. A pleasant sense of relief greeted the news that the first unmanned lunar spacecraft did not disappear into the dust. For a century or more it was doubted that lunar craters were produced by impacts because it was assumed that such craters would seldom be circular. It seemed obvious that circular craters could only be produced by objects falling straight down, a rare situation, since meteorites are likely to approach from random directions, especially on the moon where there is no atmosphere to slow them down before impact. W. M. Smart in 1928 stated this explicitly: “Objections to lunar craters being caused by meteors is that the craters are round and there is no a priori reason why meteors should fall vertically and in no other direction.” He also shuddered at the notion that the impactors would have to be as large as asteroids to create the lunar basins. At about the same time, Thomas Chamberlin ruled out impacts on the moon because there was no evidence for an appropriate population of objects anywhere in the solar system that could have made the craters That was in 1928 when near-earth asteroids had not yet been found, and when little was known about the history of the moon or the formation of the solar system. Richard A. Proctor in 1896, however, had concluded that because so many meteors continued to fall to earth that the planet and the solar system were still forming. To him, this made more sense than to blame the formation of the planets on “the creative fiats of the Almighty.” There is merit to his point of view, because today’s bombardment merely represents a faint, ongoing manifestation of the process of accretion that assembled the planets in the first place.
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Actas de conferencias sobre el tema "Asteroid Landing"

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Zhao, Zhijun, Delun Li, Baofeng Yuan, Sheng Gao y Jingdong Zhao. "Landing performance simulation of an asteroid landing mechanism". En 2015 IEEE International Conference on Information and Automation (ICIA). IEEE, 2015. http://dx.doi.org/10.1109/icinfa.2015.7279601.

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Zhao, Zhijun, Jingdong Zhao y Hong Liu. "An asteroid landing mechanism and its landing simulation". En 2012 IEEE International Conference on Robotics and Biomimetics (ROBIO). IEEE, 2012. http://dx.doi.org/10.1109/robio.2012.6490967.

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Udomkesmalee, S., Ching-Fang Lin, A. Politopoulos, Guohui Hu y T. Huntsberger. "Autonomous Target Tracking for Asteroid Landing". En 4th International Conference on Control and Automation. Final Program and Book of Abstracts. IEEE, 2003. http://dx.doi.org/10.1109/icca.2003.1595036.

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Li, Jian-geng, Jia Zhen y Xiao-gang Ruan. "Optimal site selection for soft landing on asteroid". En 2014 26th Chinese Control And Decision Conference (CCDC). IEEE, 2014. http://dx.doi.org/10.1109/ccdc.2014.6852676.

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Liu, Hong, Zhijun Zhao y Jingdong Zhao. "Preliminary anchoring technology for landing on the asteroid". En 2013 IEEE International Conference on Robotics and Biomimetics (ROBIO). IEEE, 2013. http://dx.doi.org/10.1109/robio.2013.6739828.

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Jiangeng, Li, Zhang Rong, Wei Ruoyan y Zhang Yu. "An asteroid landing location algorithm based on image feature". En 2013 25th Chinese Control and Decision Conference (CCDC). IEEE, 2013. http://dx.doi.org/10.1109/ccdc.2013.6561060.

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Zhao, Zhijun, Jingdong Zhao y Hong Liu. "Study on the landing mechanism employed in asteroid exploration". En 2012 IEEE International Conference on Mechatronics and Automation (ICMA). IEEE, 2012. http://dx.doi.org/10.1109/icma.2012.6283392.

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Wang, Y., Y. Zhang, X. Liu, Y. Yuan, S. Wu, H. Jia y X. Hou. "Penetration dynamics of asteroid exploration landing based on DEM". En 1st International Conference on Mechanical System Dynamics (ICMSD 2022). Institution of Engineering and Technology, 2022. http://dx.doi.org/10.1049/icp.2022.1630.

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Sie, Ouattara, Xiaogang Ruan, Ruoyan Wei y Yan Yan. "Study on Algorithm of Selecting Safe Landing Area on Ground During Asteroid Soft Landing". En 3rd International Conference on Electric and Electronics. Paris, France: Atlantis Press, 2013. http://dx.doi.org/10.2991/eeic-13.2013.34.

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Baresi, Nicola y Daniel J. Scheeres. "Estimation of Asteroid Landing Trajectories Via Line-Of-Sight Measurements". En AIAA/AAS Astrodynamics Specialist Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-4143.

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