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Статті в журналах з теми "Asteroid Landing"

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Автор: Grafiati

Опубліковано: 6 вересня 2023

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1

Yan, Weifeng, Ruoyu Feng, and Hexi Baoyin. "Stability of a Flexible Asteroid Lander with Landing Control." Aerospace 9, no. 11 (November 16, 2022): 719. http://dx.doi.org/10.3390/aerospace9110719.

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Анотація:

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, and Zhou Su. "Dynamics Research and Analysis of landing on the surface of Asteroid." Journal of Physics: Conference Series 2472, no. 1 (May 1, 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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3

Wang, R., K. Di, W. Wan, Z. Liu, Y. Wang, W. Liang, Y. Wang, X. Chen, and 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 (August 21, 2020): 1165–70. http://dx.doi.org/10.5194/isprs-archives-xliii-b3-2020-1165-2020.

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Анотація:

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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4

Wang, Weimin, and K. L. Yung. "Analysis of a Mechanical Anchoring System for Landing on Asteroids." Journal of Physics: Conference Series 2542, no. 1 (July 1, 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, and Jianrong Tan. "SinGAN-Based Asteroid Surface Image Generation." Journal of Database Management 32, no. 4 (October 2021): 28–47. http://dx.doi.org/10.4018/jdm.2021100103.

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Анотація:

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, and Wang Liwu. "Design and Experimental Research of a New Type of Asteroid Anchoring System." International Journal of Aerospace Engineering 2021 (May 18, 2021): 1–7. http://dx.doi.org/10.1155/2021/6677877.

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Анотація:

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, and Jingdong Zhao. "Development of an Anchoring System for the Soft Asteroid Landing Exploration." International Journal of Aerospace Engineering 2019 (February 7, 2019): 1–13. http://dx.doi.org/10.1155/2019/1257038.

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Анотація:

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, and Jincheng Hu. "The Fast Generation of the Reachable Domain for Collision-Free Asteroid Landing." Mathematics 10, no. 20 (October 12, 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, no. 2 (October 2002): 433–38. http://dx.doi.org/10.1006/icar.2002.6911.

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10

Cocaud, Cedric, and 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, no. 8 (October 20, 2011): 1167–74. http://dx.doi.org/10.20965/jaciii.2011.p1167.

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Анотація:

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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11

Geng, Shujuan, Binghong Zhou, and Mingtao Li. "On the capture of small stony asteroids into the Earth's orbit by atmospheric grazing." Monthly Notices of the Royal Astronomical Society 507, no. 3 (August 30, 2021): 4661–68. http://dx.doi.org/10.1093/mnras/stab2439.

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ABSTRACT An Earth-grazing asteroid can be captured into a gravitational bound orbit around the Earth during its transitory atmospheric journey. Otherwise, it will either escape back to space or plunge to the Earth directly. With fragmentation taken into account, we subdivide the captured and direct impact modes, expanding the above three modes into five – escaping, captured impact with and without fragmentation, and direct impact with and without fragmentation. We then investigate the conditions of those various impact modes of shallow-angle impacts of small stony asteroids no larger than 100 m in diameter. Moreover, the atmospheric entry processes of captured stony asteroids are further studied. Results show that asteroids with larger diameters are easier to fragment for less deceleration due to the smaller area-to-mass ratio, narrowing the corridor for capture. A captured asteroid can enter the atmosphere many times, highlighting itself by a series of explosive phenomena due to the shock wave it produced during every passage. The number of revolutions before its final entry increases as the theoretical perigee altitude rises. The multi-entry phenomenon of captured impact reduces the velocity and mass of the impactor and raises the possibility of an intact landing of the object via atmospheric dissipation. The time and space intervals between each entry make it difficult to identify whether the scattered impacts come from one captured impact event or just a series of different fireballs. The long path before its final hit also increases the difficulty of predicting the exact airburst position or landing site.

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12

Guelman, M., and D. Harel. "Power limited soft landing on an asteroid." Journal of Guidance, Control, and Dynamics 17, no. 1 (January 1994): 15–20. http://dx.doi.org/10.2514/3.21153.

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13

Herrera-Sucarrat, E., P. L. Palmer, and R. M. Roberts. "Asteroid Observation and Landing Trajectories Using Invariant Manifolds." Journal of Guidance, Control, and Dynamics 37, no. 3 (May 2014): 907–20. http://dx.doi.org/10.2514/1.59594.

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14

Martin, Iain, Steve Parkes, Martin Dunstan, and Nick Rowell. "Asteroid Modeling for Testing Spacecraft Approach and Landing." IEEE Computer Graphics and Applications 34, no. 4 (July 2014): 52–62. http://dx.doi.org/10.1109/mcg.2014.22.

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15

Tachibana, S., H. Sawada, R. Okazaki, Y. Takano, K. Sakamoto, Y. N. Miura, C. Okamoto, et al. "Pebbles and sand on asteroid (162173) Ryugu: In situ observation and particles returned to Earth." Science 375, no. 6584 (March 4, 2022): 1011–16. http://dx.doi.org/10.1126/science.abj8624.

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The Hayabusa2 spacecraft investigated the C-type (carbonaceous) asteroid (162173) Ryugu. The mission performed two landing operations to collect samples of surface and subsurface material, the latter exposed by an artificial impact. We present images of the second touchdown site, finding that ejecta from the impact crater was present at the sample location. Surface pebbles at both landing sites show morphological variations ranging from rugged to smooth, similar to Ryugu’s boulders, and shapes from quasi-spherical to flattened. The samples were returned to Earth on 6 December 2020. We describe the morphology of >5 grams of returned pebbles and sand. Their diverse color, shape, and structure are consistent with the observed materials of Ryugu; we conclude that they are a representative sample of the asteroid.

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16

Okada, Tatsuaki. "Thermography of Asteroid and Future Applications in Space Missions." Applied Sciences 10, no. 6 (March 22, 2020): 2158. http://dx.doi.org/10.3390/app10062158.

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Анотація:

The Near-Earth Asteroid 162173 Ryugu is a C-type asteroid which preserves information about the ancient Solar System and is considered enriched in volatiles such as water and organics associated with the building blocks of life, and it is a potentially hazardous object that might impact Earth. Hayabusa2 is the asteroid explorer organized by the Japan Aerospace Exploration Agency to rendezvous with the asteroid and collect surface materials to return them to Earth. Thermography has been carried out from Hayabusa2 during the asteroid proximity phase, to unveil the thermophysical properties of the primitive Solar System small body, which offered a new insight for understanding the origin and evolution of the Solar System, and demonstrated the technology for future applications in space missions. Global, local, and close-up thermal images taken from various distances from the asteroid strongly contributed to the mission success, including suitable landing site selection, safe assessment during descents into the thermal environments and hazardous boulder abundance, and the detection of deployable devices against the sunlit asteroid surface. Potential applications of thermography in future planetary missions are introduced.

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17

Cheng, Ma. "The significance and related technologies of asteroid detection." Highlights in Science, Engineering and Technology 48 (May 16, 2023): 295–317. http://dx.doi.org/10.54097/hset.v48i.8369.

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Анотація:

Asteroid detection mission plays an important role in the field of deep space exploration, and it has multiple theoretical and practical guidance advantages for asteroid detection missions, and also promotes all critical technologies of deep space exploration. At present, many asteroid exploration missions have been carried out around the world, and China also plans to launch the "Tianwen-2" probe around 2025 to carry out an integrated exploration mission of fly-by, orbit detection, attachment control and sample-return mission for asteroid 2016HO3. In this paper, we discuss the significance of asteroid detection and several related critical technologies. The theoretical value of asteroid detection covers such as promoting theoretical research on the formation and evolution of the solar system, solar system material, geohazard early warning and early warning of spacecraft orbit. As for the key technologies involved in asteroid detection, this paper discusses the design of transfer trajectory and near-orbit operation, autonomous landing, optical navigation, laser communication and electric propulsion, and summarizes the research and application results of these technologies in the international deep space exploration field.

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18

Zhao, Zhijun, Jingdong Zhao, and Hong Liu. "Development of a Landing Mechanism for Asteroids with Soft Surface." International Journal of Aerospace Engineering 2013 (2013): 1–9. http://dx.doi.org/10.1155/2013/873135.

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Анотація:

A landing mechanism to an asteroid with soft surface is developed. It consists of three landing feet, landing legs, cardan element, damping element, equipment base, anchoring system, and so on. Static structural analysis and modal analysis are carried out to check the strength and natural frequency of the landing mechanism with FEA. Testing platform for the anchoring system is introduced, and then the penetrating and anchoring tests of the anchoring system are carried out in different media. It shows that cohesion of the media has large influence on the penetrating and anchoring performance of the anchoring system. Landing tests of the landing mechanism with different velocities under simulated microgravity environment are carried out on the air-floating platform, and the impact accelerations are measured by the sensors on the landing mechanism. At the same time, these impact accelerations are processed by spectrum analysis to find the natural frequency of the landing mechanism.

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19

Furfaro, Roberto, Dario Cersosimo, and Daniel R. Wibben. "Asteroid Precision Landing via Multiple Sliding Surfaces Guidance Techniques." Journal of Guidance, Control, and Dynamics 36, no. 4 (July 2013): 1075–92. http://dx.doi.org/10.2514/1.58246.

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20

Showstack, R. "NEAR spacecraft makes first-ever landing on an asteroid." Eos, Transactions American Geophysical Union 82, no. 8 (2001): 98. http://dx.doi.org/10.1029/01eo00051.

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21

Sanchez, Julio C., Francisco Gavilan, and Rafael Vazquez. "A Predictive Guidance Algorithm for Autonomous Asteroid Soft Landing." IFAC-PapersOnLine 51, no. 12 (2018): 6–11. http://dx.doi.org/10.1016/j.ifacol.2018.07.080.

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22

Yu, Meng, Shuang Li, Shuquan Wang, and Xiangyu Huang. "Single crater-aided inertial navigation for autonomous asteroid landing." Advances in Space Research 63, no. 2 (January 2019): 1085–99. http://dx.doi.org/10.1016/j.asr.2018.09.035.

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23

Kang, Shen, Jianan Wang, Chaoyong Li, and Jiayuan Shan. "Nonlinear optimal control with disturbance rejection for asteroid landing." Journal of the Franklin Institute 355, no. 16 (November 2018): 8027–48. http://dx.doi.org/10.1016/j.jfranklin.2018.06.028.

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24

Lin, Boyu, and Hutao Cui. "Research on A Low Computational Cost Vision-aided Inertial Navigation Method for Precision Landing on Asteroid." Journal of Physics: Conference Series 2203, no. 1 (February 1, 2022): 012020. http://dx.doi.org/10.1088/1742-6596/2203/1/012020.

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Abstract Asteroid exploration missions demand more autonomous navigation system that are precise and in real-time. Visual-aided inertial navigation systems combine the advantages of autonomy of inertial navigation systems and accuracy of visual navigation systems. However, both increase the computational burden for the information processing. With the goal of decreasing the computational load, this paper proposes a low cost vision-aided inertial navigation method which can calculate increment position, velocity and attitude directly in inertial frame by pre-integrating IMU measurements. For visual information, specific combinations of the features are selected according to information entropy theory to reduce computation. Simulation results show that the standard deviations of the spacecraft’s estimated position error is less than 1 m, the velocity less than 0.002 m/s and the attitude angle less than 0.005 deg, compatible with precision landing on asteroids.

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25

Mikawa, Masahiko. "Robust Wireless Communication for Small Exploration Rovers Equipped with Multiple Antennas by Estimating Attitudes of Rovers in Several Experimental Environments." Journal of Robotics and Mechatronics 29, no. 5 (October 20, 2017): 864–76. http://dx.doi.org/10.20965/jrm.2017.p0864.

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We are developing a robotic system for an asteroid surface exploration. The system consists ofmultiplesmall size rovers, that communicate with each other over a wireless network. Since the rovers configure over a wireless mesh sensor network on an asteroid, it is possible to explore a large area on the asteroid effectively. The rovers will be equipped with a hopping mechanism for transportation, which is suitable for exploration in a micro-gravity environment like a small asteroid’s surface. However, it is difficult to control the rover’s attitude during the landing. Therefore, a cube-shaped rover was designed. As every face has two antennas respectively, the rover has a total of twelve antennas. Furthermore, as the body shape and the antenna arrangements are symmetric, irrespective of the face on top, a reliable communication state among the rovers can be established by selecting the proper antennas on the top face. Therefore, it is important to estimate which face of the rover is on top. This paper presents an attitude estimation method based on the received signal strength indicators (RSSIs) obtained when the twelve antennas communicate among each other. Since the RSSI values change depending on an attitude of the rover and the surrounding environment, a significantly large number of RSSIs were collected as a training data set in different kinds of environments similar to an asteroid; consequently, a classifier for estimating the rover attitude was trained from the data set. A few of the experimental results establish the validity and effectiveness of the proposed exploration system and attitude estimation method.

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26

Zhao, Zhijun, JingDong Zhao, and Hong Liu. "Landing Dynamic and Key Parameter Estimations of a Landing Mechanism to Asteroid with Soft Surface." International Journal of Aeronautical and Space Sciences 14, no. 3 (September 30, 2013): 237–46. http://dx.doi.org/10.5139/ijass.2013.14.3.237.

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27

Schulz, Rita. "The Rosetta Mission: Comet and Asteroid Exploration." Proceedings of the International Astronomical Union 5, S263 (August 2009): 312–16. http://dx.doi.org/10.1017/s1743921310001997.

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AbstractIn March 2004 the European Space Agency launched its Planetary Cornerstone Mission Rosetta to rendezvous with Jupiter-family comet 67P/Churyumov-Gerasimenko. The Rosetta mission represents the next step into the improvement of our understanding of comet nuclei naturally following the four successful comet nucleus fly-by missions carried out in the past. It will however not perform a simple fly-by at its target comet, but combines an Orbiter and a Lander Mission. The Rosetta spacecraft will go in orbit around the comet nucleus when it is still far away from the Sun, and escort the comet for more than a year along its pre- and post-perihelion orbit while monitoring the evolution of the nucleus and the coma as a function of increasing and decreasing solar flux input. Different instrumentations will be used in parallel, from multi-wavelength spectrometry to in-situ measurements of coma and nucleus composition and physical properties. In addition the Rosetta Lander Philae will land on the nucleus surface, before the comet is too active to permit such a landing (i.e. at around r = 3 AU) and examine the surface and subsurface composition as well as its physical properties. Two fly-bys at main belt asteroids have been scheduled for the Rosetta spacecraft during its journey to the comet. The first fly-by at E-type asteroid (2867) Steins was already successfully executed in September 2008. The second and main fly-by at asteroid (21) Lutetia is scheduled for July 2010.

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28

Chengyu Zhang, 张成渝, 梁潇 Xiao Liang, 吴奋陟 Fenzhi Wu, and 张琳 Lin Zhang. "Overview of optical navigation for asteroid exploration descent and landing." Infrared and Laser Engineering 49, no. 5 (2020): 20201009. http://dx.doi.org/10.3788/irla.15_invited-zhangchengyu.

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29

Quan, Qiquan, Tingzhang Wang, Hao Guan, Dewei Tang, and Zongquan Deng. "Electromagnetic damping asteroid landing cushioning mechanism and dynamic simulation analysis." Advances in Space Research 69, no. 7 (April 2022): 2756–69. http://dx.doi.org/10.1016/j.asr.2022.01.015.

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30

Ogawa, Naoko, Fuyuto Terui, and Jun'ichiro Kawaguchi. "Precise Landing of Space Probe on Asteroid Using Multiple Markers." IFAC Proceedings Volumes 43, no. 15 (2010): 172–77. http://dx.doi.org/10.3182/20100906-5-jp-2022.00030.

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31

Yang, Hongwei, Xiaoli Bai, and Hexi Baoyin. "Rapid Trajectory Planning for Asteroid Landing with Thrust Magnitude Constraint." Journal of Guidance, Control, and Dynamics 40, no. 10 (October 2017): 2713–20. http://dx.doi.org/10.2514/1.g002346.

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32

Yang, Hongwei, and Hexi Baoyin. "Fuel-optimal control for soft landing on an irregular asteroid." IEEE Transactions on Aerospace and Electronic Systems 51, no. 3 (July 2015): 1688–97. http://dx.doi.org/10.1109/taes.2015.140295.

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33

Zhu, Lingchao, and Shuquan Wang. "Orbit-Attitude Coupled Tracking and Landing Control for an Asteroid." IOP Conference Series: Materials Science and Engineering 685 (November 22, 2019): 012003. http://dx.doi.org/10.1088/1757-899x/685/1/012003.

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34

Zhang, Bo, and Yuanli Cai. "Twistor-based pose control for asteroid landing with path constraints." Nonlinear Dynamics 100, no. 3 (April 28, 2020): 2427–48. http://dx.doi.org/10.1007/s11071-020-05610-w.

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35

Chen, Gang, Peilin Cai, Yifan Wang, Long Zhang, and Ji Liang. "Trajectory Optimization for Asteroid Landing Considering Gravitational Orbit-Attitude Coupling." IEEE Access 7 (2019): 126464–78. http://dx.doi.org/10.1109/access.2019.2938821.

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36

Tsuda, Yuichi, Takanao Saiki, Fuyuto Terui, Satoru Nakazawa, Makoto Yoshikawa, and Sei-ichiro Watanabe. "Hayabusa2 mission status: Landing, roving and cratering on asteroid Ryugu." Acta Astronautica 171 (June 2020): 42–54. http://dx.doi.org/10.1016/j.actaastro.2020.02.035.

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37

Preusker, F., F. Scholten, S. Elgner, K. D. Matz, S. Kameda, T. Roatsch, R. Jaumann, et al. "The MASCOT landing area on asteroid (162173) Ryugu: Stereo-photogrammetric analysis using images of the ONC onboard the Hayabusa2 spacecraft." Astronomy & Astrophysics 632 (December 2019): L4. http://dx.doi.org/10.1051/0004-6361/201936759.

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Анотація:

A high-resolution 3D surface model, map-projected to a digital terrain model (DTM), and precisely ortho-rectified context images (orthoimages) of MASCOT landing site area are important data sets for the scientific analysis of relevant data that have been acquired with MASCOT’s image camera system MASCam and other instruments (e.g., the radiometer MARA and the magnetometer MASMag). We performed a stereo-photogrammetric (SPG) analysis of 1050 images acquired from the Hayabusa2 Optical Navigation Camera system (ONC) during the asteroid characterization phase and the MASCOT release phase in early October 2018 to construct a photogrammetric control point network of asteroid (162173) Ryugu. We validated existing rotational parameters for Ryugu and improved the camera orientation (position and pointing) of the ONC images to decimeter accuracy using SPG bundle block adjustment. We produced a high-resolution DTM of the entire MASCOT landing site area. Finally, based on this DTM, a set of orthoimages from the highest-resolution ONC images around MASCOT’s final rest position complements the results of this analysis.

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38

Liu, Z., X. Chen, X. Li, and F. Jia. "A Framework of High-precision State Estimation for Approaching, Orbiting, and Touching an Asteroid." Journal of Physics: Conference Series 2239, no. 1 (April 1, 2022): 012007. http://dx.doi.org/10.1088/1742-6596/2239/1/012007.

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Abstract High-precision state estimation lies at the core of asteroid exploration. This paper investigates the high-precision state estimation methods in asteroid approaching, orbiting, and touching phases. The system and measurement models are established, and state estimation strategies are designed respectively for each phase. In the approaching phase, the star image is used to directly determine the relative orbit of the spacecraft to the target asteroid. To improve the optical state estimation precision, a deceleration-orientation-deceleration strategy is developed. In the orbiting phase, coupled orbit-attitude estimation is realized based on the terrain features of the asteroid, and the effect of dynamic error on the accuracy of state estimation is analysed. Then, a decoupled orbit-attitude state estimation method is developed to avoid the affection of dynamic error. In the touching phase, lidar measurement is used to determine the relative orbit and attitude of the spacecraft with respect to the landing spot. Based on the triple-stage state estimation framework proposed in this paper, the relative state error of the spacecraft converges from 100km level to 1mm level.

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39

Liu, Keping, Fengxia Liu, Shenquan Wang, and Yuanchun Li. "Finite-Time Spacecraft’s Soft Landing on Asteroids Using PD and Nonsingular Terminal Sliding Mode Control." Mathematical Problems in Engineering 2015 (2015): 1–10. http://dx.doi.org/10.1155/2015/510618.

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This paper presents a continuous control law of probe, which consists of PD (proportional-derivative) controller and nonsingular terminal sliding mode controller for probe descending and landing phases, respectively, in the case of the asteroid irregular shape and low gravity. The probe dynamic model is deduced in the landing site coordinate system firstly. Then the reference trajectory based on optimal polynomial in open-loop state is designed, with the suboptimal fuel consumption. Taking into account different characteristics of phases, PD controller and nonsingular terminal sliding mode controller can be employed in the descending phase and the landing phase, respectively, to track the designed reference trajectory. The controller which used the corresponding control methods can meet the motion characteristics and requirements of each stage. Finally simulation experiments are carried out to demonstrate the effectiveness of the proposed method, which can ensure the safe landing of probe and achieve continuous control.

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40

Dias, Nicole G., Paulo Gordo, Hugo Onderwater, Rui Melicio, and António Amorim. "Analysis on the Isostatic Bipod Mounts for the HERA Mission LIDAR." Applied Sciences 12, no. 7 (March 30, 2022): 3497. http://dx.doi.org/10.3390/app12073497.

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The Light Detection and Ranging (LIDAR) is a time-of-flight altimeter instrument being developed for the HERA mission, designated as Planetary ALTimeter (PALT). PALT is positioned in the center of the top face of the HERA probe, and therefore, it cannot use radiators to stabilize its internal temperature. The contribution of this paper is the design of isostatic bipod mounts for the LIDAR primary mirror. The performance of PALT must be maintained over a wide operational range, from −60 °C to 80 °C. These temperature requirements imply that a careful isostatic mount structure design is critical to maintaining performance in all operational scenarios. The purpose of the instrument is to perform range measurements from 500 m to 14 km. The instrument will contribute to the detailed characterization of the asteroid’s topography, assist the probe navigation in operations such as fly-bys (including on the dark side of the asteroid) or landing. PALT has an emitter system that generates 2 ns, 100 µJ, 1535 nm laser pulses and a receiver system that collects the backscattered signal from the asteroid. The receiver system is composed of a 70 mm diameter Cassegrain telescope and a refractive system that focuses the signal on the sensor.

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41

Mathavaraj, S., and Radhakant Padhi. "Quasi-Spectral Unscented MPSP Guidance for Robust Soft-Landing on Asteroid." Journal of Optimization Theory and Applications 191, no. 2-3 (October 23, 2021): 823–45. http://dx.doi.org/10.1007/s10957-021-01953-5.

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42

Cheng, Lin, Zhenbo Wang, Fanghua Jiang, and Junfeng Li. "Fast Generation of Optimal Asteroid Landing Trajectories Using Deep Neural Networks." IEEE Transactions on Aerospace and Electronic Systems 56, no. 4 (August 2020): 2642–55. http://dx.doi.org/10.1109/taes.2019.2952700.

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43

Veverka, J., B. Farquhar, M. Robinson, P. Thomas, S. Murchie, A. Harch, P. G. Antreasian, et al. "The landing of the NEAR-Shoemaker spacecraft on asteroid 433 Eros." Nature 413, no. 6854 (September 2001): 390–93. http://dx.doi.org/10.1038/35096507.

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44

Kubota, Takashi, Tatsuaki Hashimoto, Shujiro Sawai, Jun'ichiro Kawaguchi, Keiken Ninomiya, Mashashi Uo, and Kenichi Baba. "An autonomous navigation and guidance system for MUSES-C asteroid landing." Acta Astronautica 52, no. 2-6 (January 2003): 125–31. http://dx.doi.org/10.1016/s0094-5765(02)00147-9.

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45

Zhang, Yingying, Jiangchuan Huang, and Hutao Cui. "Trajectory optimization for asteroid landing with two-phase free final time." Advances in Space Research 65, no. 4 (February 2020): 1210–24. http://dx.doi.org/10.1016/j.asr.2019.11.031.

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46

AlandiHallaj, MohammadAmin, and Nima Assadian. "Asteroid precision landing via Probabilistic Multiple-Horizon Multiple-Model Predictive Control." Acta Astronautica 161 (August 2019): 531–41. http://dx.doi.org/10.1016/j.actaastro.2019.04.009.

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47

Thuillet, Florian, Patrick Michel, Clara Maurel, Ronald-Louis Ballouz, Yun Zhang, Derek C. Richardson, Jens Biele, Eri Tatsumi, and Seiji Sugita. "Numerical modeling of lander interaction with a low-gravity asteroid regolith surface." Astronomy & Astrophysics 615 (July 2018): A41. http://dx.doi.org/10.1051/0004-6361/201832779.

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Context. Landing on the surface of small bodies is particularly challenging, as the physical properties of the surface material are not well known and the mechanical response of this material in a low-gravity environment is not well understood. Aims. In order to improve our understanding of low-speed impact processes on granular media and their outcome in low-gravity environments, we consider the landing of the package MASCOT, to be released by the JAXA asteroid sample return mission Hayabusa2 on (162173) Ryugu in October 2018. Beyond addressing the theoretical aspects of the mechanical response of granular media in low gravity, this study also supports both engineering and scientific teams of Hayabusa2 in the search for the lander and in the determination of Ryugu’s surface properties. Methods. A campaign of hundreds of numerical simulations using the soft-sphere discrete element method implemented in the N-body code pkdgrav were performed to study the interaction between the lander and the low-gravity surface of the asteroid made of a granular medium representing the regolith. Assuming a broad range of regolith properties, and the lander’s trajectory and motion, we analyzed the outcomes of the landing (distance traveled by the lander, penetration depth, and shape of the traces left in the regolith surface) to determine the influence of the many parameters defining the properties of MASCOT and of the grains, and the ingoing motion of the lander. Results. We identify well-marked trends for the fate of the lander and the traces left in the granular material. Distances traveled by the lander are greater and penetrations are shallower for gravel-like media than for less frictional material. A similar trend is found for grazing impacts as opposed to vertical ones. Different regolith properties also generate different traces on the ground after the impact.

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48

Wang, Jinlin, Hai Li, Zhangjin Lin, and Hong Huo. "Time-Fixed Glideslope Guidance for Approaching the Proximity of an Asteroid." Aerospace 8, no. 5 (May 15, 2021): 137. http://dx.doi.org/10.3390/aerospace8050137.

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The guidance and control problem of spacecraft approaching an asteroid using constant continuous thrust is studied in this work. The range of interest is from hundreds of kilometers to several kilometers, in which relative measurements of much higher accuracy than based on Earth can be used to facilitate further hovering or landing operations. Time-fixed glideslope guidance algorithm is improved by introducing a substitute of an existing control parameter and combined with elliptical relative orbital dynamics to rendezvous the spacecraft with a prescribed location in the proximity of a given asteroid. A vast range of values for the control parameters are explored and suitable combinations are found. To fully validate the robustness and accuracy of the proposed control algorithm, Monte Carlo simulations are done with the navigational error and implementation error considered.

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49

Ren, Yuan, and Jinjun Shan. "Reliability-Based Soft Landing Trajectory Optimization near Asteroid with Uncertain Gravitational Field." Journal of Guidance, Control, and Dynamics 38, no. 9 (September 2015): 1810–20. http://dx.doi.org/10.2514/1.g000903.

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50

Yang, Hongwei, Xiaoli Bai, and Hexi Baoyin. "Rapid Generation of Time-Optimal Trajectories for Asteroid Landing via Convex Optimization." Journal of Guidance, Control, and Dynamics 40, no. 3 (March 2017): 628–41. http://dx.doi.org/10.2514/1.g002170.

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