Urban Air Mobility (UAM) includes new aeronautical applications encompassing the future on-demand urban human air transportation (e.g. air-taxi) and unmanned aerial system operations for goods delivery and public safe...
详细信息
Urban Air Mobility (UAM) includes new aeronautical applications encompassing the future on-demand urban human air transportation (e.g. air-taxi) and unmanned aerial system operations for goods delivery and public safe...
详细信息
ISBN:
(数字)9798350349610
ISBN:
(纸本)9798350349627
Urban Air Mobility (UAM) includes new aeronautical applications encompassing the future on-demand urban human air transportation (e.g. air-taxi) and unmanned aerial system operations for goods delivery and public safety in urban, sub-urban and inter-city areas. One of the key technology enablers of UAM implementation is related to the availability of robust and resilient positioning, navigation and timing measurements. In this context, the Global Navigation Satellite Systems (GNSS) is in principle able to provide valid technological solutions to above required performances that are threatened in dense urban environments. In this framework, the present work describes a hybrid navigation unit for UAM applications implementing all the algorithms for a tightly coupled sensor fusion between a dual frequency multi constellation GNSS receiver, an inertial measurements unit and barometric altitude from an air data computer, together with related autonomous fault detection and exclusion of GPS/Galileo/BeiDou satellites and estimation of navigation solution integrity/accuracy. Such prototype has been validated through real-time hardware-in-the-loop simulations and in-flight demonstrations in reproduced UAM scenarios.
作者：
吴伟仁田玉龙黄翔宇Institute for Pattern Recognition and Artificial Intelligence
State Key Lab. for Image Processing and Intelligent Control Huazhong University of Science and Technology Wuhan 430074 China Deep Space Exploration Research Center
Harbin Institute of Technology Harbin 150001 Chinahe image elements of earth-center and moon-center are obtained by processing the images of earth and moon these image elements in combination with the inertial attitude information and the moon ephemeris are utilized to obtain the probe initial position relative to earth and the Levenberg-Marquardt algorithm is used to determine the accurate probe position relative to earth and the probe orbit relative to earth is estimated by using the extended Kalman filter. The autonomous optical navigation algorithm is validated using the digital simulation.
The image elements of earth-center and moon-center are obtained by processing the images of earthand moon, these image elements in combination with the inertial attitude information and the moon ephemerisare utilized ...
详细信息
The image elements of earth-center and moon-center are obtained by processing the images of earthand moon, these image elements in combination with the inertial attitude information and the moon ephemerisare utilized to obtain the probe initial position relative to earth, and the Levenberg-Marquardt algorithm is usedto determine the accurate probe position relative to earth, and the probe orbit relative to earth is estimated by u-sing the extended Kalman filter. The autonomous optical navigation algorithm is validated using the digital simu-lation.
The observed images of the asteroid and the asteroid reference images are used to obtain the probe-to-asteroid direction and the location of the limb features of the asteroid in the inertial coordinate. These informa-...
详细信息
The observed images of the asteroid and the asteroid reference images are used to obtain the probe-to-asteroid direction and the location of the limb features of the asteroid in the inertial coordinate. These informa-tion in combination with the shape model of the asteroid and attitude information of the probe are utilized to ob-tain the position of the probe. The position information is then input to the UKF which determines the real-timeorbit of the probe. Finally, the autonomous orbit determination algorithm is validated using digital *** determination of orbit using UKF is compared with that using extended Kalman filter (EKF), and the resultshows that UKF is superior to EKF.
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