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Autonomous relative optical navigation based on unified modeling of external systematic errors

Chinese Journal of Aeronautics 2024年第3期37卷 282-289页

作者： Dayi WANG Bowen SUN Maodeng LI Jiaxing LI Haiyin ZHOU Beijing Institute of Spacecraft System Engineering Beijing 100191China College of Sciences National University of Defense TechnologyChangsha 410073China National Key Laboratory of Space Intelligent Control Beijing Institute of Control EngineeringBeijing 100191China

To solve the problem that external systematic errors of the optical camera cannot be fully estimated due to limited computing resources,a unified dimensionality reduction representation method for the external systematic errors of the optical camera is proposed,and autonomous relative optical navigation is *** camera translational and misalignment errors are converted into a three-dimensional rotation error,whose differential model can be established through specific attitude control and appropriate ***,the rotation error and the relative motion state are jointly estimated in an augmented Kalman filter *** with the traditional method that estimates the camera translational and misalignment errors,the proposed method reduces the computational complexity in that the estimated state dimension is ***,as demonstrated by numerical simulation,the estimation accuracy is improved significantly.

关键词： Unified model Systematic errors optical navigation Observability analysis Calibration

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Autonomous navigation for Mars Atmospheric Aerobraking based on optical and Inertial Integrated Method

Autonomous Navigation for Mars Atmospheric Aerobraking based...

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新型导航技术及应用研讨会

作者： XIE Pan ZHANG Heng Shanghai Institute of Satellite Engineering Shanghai Key Laboratory of Deep Space Exploration Technology

Mars atmospheric aerobraking is an effective way to decrease fuel mass for Mars Probe. Because of the limitation of radio navigation system which uses the ground stations, real-time and high-precision autonomous navigation is required during the atmospheric aerobraking phase to avoid falling into atmosphere or Mars impact. Under the engineering background of Mars atmospheric aerobraking, integrated navigation method based on optical and inertial measurement is proposed. State model affected by aerodynamic force is built and measurement model by optical navigation sensor and inertial measurement unit(IMU) is established. In addition, combined with position information of Mars, Phobos and Deimos in ephemeris, UKF filter algorithm is applied to optimal fusion of navigation information. Simulation results indicate that the integrated navigation method based on optical and inertial measurement is feasible and effective.

关键词： Mars Exploration Aerobraking optical navigation Autonomous navigation

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Rendezvous to asteroid with highly uncertain ephemeris: Hayabusa2’s Ryugu-approach operation result

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Astrodynamics 2020年第2期4卷 137-147页

作者： Yuichi Tsuda Hiroshi Takeuchi Naoko Ogawa Go Ono Shota Kikuchi Yusuke Oki Masateru Ishiguro Daisuke Kuroda Seitaro Urakawa Shin-ichiro Okumura Hayabusa2 Project Team Institute of Space and Astronautical Science Japan Aerospace Exploration AgencySagamihara252-5210Japan Research and Development Directorate Japan Aerospace Exploration AgencySagamihara252-5210Japan Research and Development Directorate Japan Aerospace Exploration AgencyTsukuba305-8505Japan Seoul National University Seoul08826Republic of Korea Okayama Observatory Kyoto UniversityAsakuchi719-0232Japan Japan Spaceguard Association Bisei714-1411Japan 不详

This paper describes the guidance and navigation technique used by Hayabusa2 for the asteroid rendezvous operation to reach *** operation results,including the achieved guidance and navigation performance,are also *** assessment and navigation teams worked closely to provide reliable navigation solutions with a short solution delivery *** the uncertainty of the Ryugu’s ephemeris was considerable before Hayabusa2’s arrival,a combination of radiometric-optical hybrid navigation and a stochastic-constrained optimum guidance method was able to achieve an accuracy of less than 100 m and 1 cm/s,and the arrival was precisely timed.

关键词： solar system exploration sample return optical navigation trajectory optimization spacecraft guidance

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Simultaneous estimation of spacecraft position and asteroid diameter during final approach of Hayabusa2 to Ryugu

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Astrodynamics 2020年第2期4卷 163-175页

作者： Yuki Takao Yuya Mimasu Yuichi Tsuda Institute of Space and Astronautical Science Japan Aerospace Exploration AgencySagamihara252-5210Japan

This paper presents the optical navigation results of the asteroid explorer Hayabusa2 during the final rendezvous approach phase with the asteroid *** orbit determination of Hayabusa2 during the cruising phase uses a triangulation-based method that estimates the probe and asteroid orbits using the directions from which they are ***,the asteroid size is available as optical information just prior to *** size information allows us to estimate the relative distance between the probe and the asteroid with high accuracy,that is strongly related to the success or failure of the *** this study,the relative distance and asteroid size in real space are simultaneously estimated in real time by focusing on the rate of change of the asteroid size observed in sequential *** real-time estimation results coincided with those of precise analyses performed after arrival.

关键词： asteroids small bodies optical navigation size estimation orbit determination real time

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The deep-space multi-object orbit determination system and its application to Hayabusa2’s asteroid proximity operations

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Astrodynamics 2020年第4期4卷 377-392页

作者： Hiroshi Takeuchi Kent Yoshikawa Yuto Takei Yusuke Oki Shota Kikuchi Hitoshi Ikeda Stefania Soldini Naoko Ogawa Yuya Mimasu Go Ono Fuyuto Terui Naoya Sakatani Manabu Yamada Toru Kouyama Shingo Kameda Takanao Saiki Yuichi Tsuda Institute of Space and A stronautical Science Japan A erospace Exploration AgencySagamihara 252-5210Japan The Graduate University for Aduanced Studies Hayama 240-0193Japan Research and Development Directorate Japan Aerospace Exploration AgencySagamihara 252-5210Japan University of Liverpool Liverpool L693BXUK Chiba Institute of Technology Narashino 275-0016Japan National Institute of Aduanced Industrial Science and Technology Koto-ku 135-0064Japan Rikkyo University Toshima-ku 171-8501Japan

The deep-space multi-object orbit determination system(DMOODS)and its application in the asteroid proximity operation of the Hayabusa2 mission are *** was developed by the Japan Aerospace Exploration Agency(JAXA)for the primary purpose of determining the trajectory of deep-space spacecraft for JAXA’s planetary *** weighted least-squares batch filter is used for the orbit estimator of *** orbit estimator supports more than 10 data types,some of which are used for relative trajectory measurements between multiple space objects including natural satellites and small *** system consists of a set of computer programs running on Linux-based consumer PCs on the ground,which are used for orbit determination and the generation of radiometric tracking data,such as delta differential one-way ranging and doppler tracking *** the asteroid proximity phase of Hayabusa2,this system played an essential role in operations that had very strict navigation requirements or operations in which few optical data were obtained owing to special constraints on the spacecraft attitude or distance from the *** example is orbit determination during the solar conjunction phase,in which the navigation accuracy is degraded by the effect of the solar *** large range bias caused by the solar corona was accurately estimated with DMOODS by combining light detection and ranging(LIDAR)and ranging measurements in the superior solar conjunction phase of *** the orbiting operations of target markers and the MINERVA-II2 rover,the simultaneous estimation of six trajectories of four artificial objects and a natural object was made by *** type of simultaneous orbit determination of multi-artificial objects in deep-space has never been accomplished before.

关键词： orbit determination optical navigation gravity measurements superior solar conjunction delta differential one-way ranging(delta-DOR)

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