|
|
|
题名
|
作者
|
年代
|
出处
|
被引量
|
| 1 | 地磁导航技术研究现状综述显示文摘地磁导航具有全区域、全天候、抗干扰能力强及无积累误差的优点,是一种重要的辅助性导航方式,在多个领域得到了研究和应用。针对不同的应用载体,本文对地磁导航技术的研究和发展现状进行了综述,探讨了地磁导航方法选取的准则,为国内地磁导航技术的发展应用提供了一定参考。 | 踪华 刘嬿 杨业 | 2018 | 航天控制2018，36，3： | 14 |
| 2 | DOA estimation for attitude determination on communication satellites显示文摘In order to determine an appropriate attitude of three-axis stabilized communication satellites, this paper describes a novel attitude determination method using direction of arrival(DOA) estimation of a ground signal source. It differs from optical measurement, magnetic field measurement, inertial measurement, and global positioning system(GPS) attitude determination.The proposed method is characterized by taking the ground signal source as the attitude reference and acquiring attitude information from DOA estimation. Firstly, an attitude measurement equation with DOA estimation is derived in detail. Then, the error of the measurement equation is analyzed. Finally, an attitude determination algorithm is presented using a dynamic model, the attitude measurement equation, and measurement errors. A developing low Earth orbit(LEO)satellite which tests mobile communication technology with smart antennas can be stabilized in three axes by corporately using a magnetometer, reaction wheels, and three-axis magnetorquer rods. Based on the communication satellite, simulation results demonstrate the effectiveness of the method. The method could be a backup of attitude determination to prevent a system failure on the satellite. Its precision depends on the number of snapshots and the input signal-to-noise ratio(SNR) with DOA estimation. | Yang Bin He Feng Jin Jin Xiong Huagang Xu Guanghan | 2014 | Chinese Journal of Aeronautics2014，27，3： | 6 |
| 3 | Space Flight Validation of Design and Engineering of the ZDPS-1A Pico-satellite显示文摘The ZDPS-1A pico-satellites are the first satellites in China within the 1-10 kg mass range that are successfully operated on orbit. Unlike common pico-satellites, they are designed to be 'larger but stronger' with more powerful platforms and unique payloads so as to bear a better promise for real applications. Through their space flight mission, the functionality and performance of the two flight models are tested on orbit and validated to be mostly normal and in consistency with design and ground tests with only several inconforming occasions. Moreover, they have worked properly on orbit for one year so far, well exceeding their life expectancy of three months. Therefore, the space flight mission has reached all its goals, and verified that the design concept and the engineering process of the picosatellites are sufficient in allowing them the desired functionality and performance in, and the adaption to the launch procedure and the low-Earth orbit space environment. In the foreseeable future, the platform together with the design concept and the engineering process of the pico-satellites are expected to be applied to more complicated real space applications. | YANG Mu WANG Hao WU Changju WANG Chunhui DING Licong ZHENG Yangming JIN Zhonghe | 2012 | Chinese Journal of Aeronautics2012，25，5： | 5 |
| 4 | Autonomous orbit determination using epoch-differenced gravity gradients and starlight refraction显示文摘Autonomous orbit determination via integration of epoch-differenced gravity gradients and starlight refraction is proposed in this paper for low-Earth-orbiting satellites operating in GPSdenied environments. Starlight refraction compensates for the significant along-track position error that occurs from only using gravity gradients and benefits from integration in terms of improved accuracy in radial and cross-track position estimates. The between-epoch differencing of gravity gradients is employed to eliminate slowly varying measurement biases and noise near the orbit revolution frequency. The refraction angle measurements are directly used and its Jacobian matrix derived from an implicit observation equation. An information fusion filter based on a sequential extended Kalman filter is developed for the orbit determination. Truth-model simulations are used to test the performance of the algorithm, and the effects of differencing intervals and orbital heights are analyzed. A semi-simulation study using actual gravity gradient data from the Gravity field and steady-state Ocean Circulation Explorer(GOCE) combined with simulated starlight refraction measurements is further conducted, and a three-dimensional position accuracy of better than 100 m is achieved. | Pei CHEN Tengda SUN Xiucong SUN | 2017 | Chinese Journal of Aeronautics2017，30，5： | 4 |
| 5 | On-orbit real-time magnetometer bias determination for micro-satellites without attitude information显示文摘Due to the disadvantages such as complex calculation, low accuracy of estimation, and being non real time in present methods, a new real-time algorithm is developed for on-orbit magnetometer bias determination of micro-satellites without attitude knowledge in this paper. This method uses the differential value approach. It avoids the impact of quartic nature and uses the iterative method to satisfy real-time applications. Simulation results indicate that the new real-time algorithm is more accurate compared with other methods, which are also tested by an experiment system using real noise data. With the new real-time algorithm, a magnetometer calibration can be taken on-orbit and will reduce the demand for computing power effectively. | Zhang Zhen Xiong Jianping Jin Jin | 2015 | Chinese Journal of Aeronautics2015，28，5： | 1 |
| 6 | 基于模糊调节无迹卡尔曼滤波器的地磁定轨研究显示文摘地磁定轨系统适合于对仪器复用率要求高的微纳卫星使用。考虑到地磁定轨系统的性能受限于地磁偏差,本文设计了模糊调节器,并构建了模糊调节无迹卡尔曼滤波器。将地磁偏差建模为随机游走,并将其变化率作为调节器的输入量,经模糊处理后,自适应调节滤波器的参数。SWARMA卫星的实测数据实验表明,该算法可有效提升地磁偏差的估计精度,从而提升地磁定轨系统的性能。相较于传统的无迹卡尔曼滤波器,该算法的收敛速度更快,精度也更高,其位置误差均方根值为3.1 km. | 陈贵芳 郁丰 踪华 王润 | 2021 | Transactions of Nanjing University of Aeronautics and Astronautics2021，38，4： | 1 |
| 7 | CubeSat Autonomous Orbit Determination Based on Magnetometer and Sun Sensor Data显示文摘CubeSats have evolved from purely educational tools to a standard platform for technology demonstration,scientific instrumentation and application in less than a decade.They open the door to new challenges and interplanetary missions which lead to the direct realization of autonomous orbit determination(AOD)which has been investigated before with different integrated sensors combined with various filters.Mostly these studies were carried out for larger satellites with more accurate sensors.Magnetometer and sun sensor combined with extended Kalman filter(EKF)are chosen to complete AOD task considering their light weight.For the purpose of AOD and the computational cost requirements imposed on CubeSats,it is important to develop and apply low cost on-board models.In this perspective,a magnetic model based on a table look up is proposed to generate the reference magnetic field with a low computational burden.In current article the simulations through Matlab and Satellites Tool Kit(STK)especially focus on the accuracy of the AOD system provided by this model.For analysis three EKFs are carried out with different calculation models and data types.The system based on the proposed model is fully autonomous,low-cost and has moderate-accuracy required by most CubeSats missions.The AOD system can be applied as main or backup system depending on the space missions′demands. | Wesam Mohammed Elmahy Zhang Xiang Lu Zhengliang Liao Wenhe | 2017 | Transactions of Nanjing University of Aeronautics and Astronautics2017，34，6： | 0 |
| 8 | 基于新息趋势的纳卫星地磁定轨显示文摘针对地磁定轨系统受地磁偏差影响精度不高的问题,提出了一种基于新息趋势的自适应地磁定轨算法(AKF)。该算法将地磁偏差建模为随机游走模型,使之参与滤波。在滤波器运行过程中,依据新息的变化趋势,实时调整滤波器状态。以Swarm-A卫星的观测数据的实验表明,该算法和传统滤波器相比具有计算量低,收敛速度快,定位精度高等优点。通过改善地磁偏差的估计性能,该算法提升了系统的定位精度,其最大定位误差为6 km。 | 陈贵芳 郁丰 王润 | 2021 | 航天控制2021，39，1： | 0 |
您所在的机构暂未开通此部分的功能，请联系管理员