Wei J.,State Key Laboratory of Astronautic Dynamics
Journal of Beijing Institute of Technology (English Edition) | Year: 2016
In recent years, a large quantity of micro satellite has been launched into space, which makes the space environment of low Earth orbit (LEO) more complex. To reduce the negative influence bringing by micro satellite, the present situation of space environment and micro satellite are introduced. Based on the analysis of the relationship between micro satellite and space debris, especially the potential effect of micro satellite on monitoring and mitigation of space debris, some advices are presented. © 2016 Beijing Institute of Technology.
Zhang J.,State Key Laboratory of Astronautic Dynamics
CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference | Year: 2016
In order to eliminate the transient high frequency oscillation signal which contained in the rocket vibration signal, and extract feature frequency, the paper proposed a novel method which bases on ensemble empirical mode decomposition and correlation coefficient test. First, the vibration signal is decomposed by Ensemble empirical mode decomposition (EEMD), and a series of intrinsic mode functions (IMF) are obtained. Then, the correlation coefficient between the IMF components and the original signal is calculated, and the effective IMF components are identified by the correlation coefficient significance test. In the end, Hilbert transform (HT) method is used to analyze the effective IMF components, and the purpose of extracting the feature frequency is achieved. The extract results of simulation signal and rocket vibration signal show that this method is feasible and effective. © 2016 IEEE.
Zhang D.,State Key Laboratory of Astronautic Dynamics |
Yu N.,PLA Second Artillery Engineering University
Proceedings - 2015 8th International Symposium on Computational Intelligence and Design, ISCID 2015 | Year: 2016
To cooperate different satellites in the complexity multi-satellite systems, this paper introduces the idea of self-assembly which is one of the basic mechanisms in the supramolecular chemistry. The multi-satellite systems is modeled by a half-edge graph model and its assembly growing method is proposed to automatically assemble resources for some mission. Finally, the simulation results of the resource assignment for the spaceflight mission by the proposed method show that the self-assembly method shed some light on the cooperation of multi-satellites. © 2015 IEEE.
Wang X.-H.,Tsinghua University |
Wang X.-H.,State Key Laboratory of Astronautic Dynamics |
Li J.-F.,Tsinghua University |
Wang Y.-R.,State Key Laboratory of Astronautic Dynamics
Guangxue Jingmi Gongcheng/Optics and Precision Engineering | Year: 2013
As space-based cameras have advantages of lower energy consumption, higher accuracy, and easy to be miniaturized when they are used to observe space objects with middle or smaller sizes, this paper explores the orbit determination method and observability calculation method of space objects by space-based cameras. The advantages that the sun synchronous orbit is set as a space-based satellite orbit are analyzed and a space-based satellite orbit is designed by referencing several foreign space-based satellite orbits. Then the visible arc sections of space objects for different orbit types are simulated based on the space-based satellite orbit. According to the orbit measurement accuracy of existing space based optical observation equipment and errors of orbit dynamic model, the different system errors, random errors and dynamic model errors for the orbit measurements are added. Finally, the orbit determination precisions for space objects in different orbital altitudes are analyzed. Analysis results show that, for determining space target in low earth orbit with 6 of 7 minutes a day / two days of space-based optical measurement orbit data, the orbit determination precision is coincident with that of the United States of America cataloging (Two-line Elements, TLE) when the orbit measurement accuracy is better than 30″ and the dynamic model error is less than 50%. Moreover, for determining space target in earth synchronous orbit with 10 min / day of space-based optical measurement orbit data, the orbit determination precision is in the orbit accuracy range of the United States of America cataloging when the orbit measurement accuracy is better than 10″ and the dynamic model error is less than 50%.
Chen Q.,National University of Defense Technology |
Kuang G.,National University of Defense Technology |
Li J.,Xiamen University |
Sui L.,State Key Laboratory of Astronautic Dynamics |
Li D.,93502 Unit
IEEE Transactions on Geoscience and Remote Sensing | Year: 2013
This paper presents a new unsupervised land cover/land use classification scheme using polarimetric synthetic aperture radar (PolSAR) imagery based on polarimetric scattering similarity. Compared with the H/alpha classification scheme based on a dominant 'average' scattering mechanism, the proposed scheme has such advantages as the following: 1) The major scattering mechanism represents a target scattering in the low-entropy case; 2) it also represents both the major and minor scattering mechanisms in the medium-entropy case; and 3) all the scattering mechanisms in the high-entropy case can be represented. The major and minor scattering mechanisms have been identified automatically based on the relative magnitude of multiple-scattering similarities. The canonical scattering corresponding to maximum scattering similarity is regarded as the major scattering mechanism. The result obtained using the National Aeronautics and Space Administration/Jet Propulsion Laboratory's AIRSAR L-band PolSAR imagery reveals that the proposed scheme is more effective as compared to the existing models and promises to increase the accuracy of the classification and interpretation. Copyright © 1980-2012 IEEE.
Luo Y.,National University of Defense Technology |
Yang Z.,National University of Defense Technology |
Li H.,State Key Laboratory of Astronautic Dynamics
Science China: Physics, Mechanics and Astronomy | Year: 2014
The optimal rendezvous trajectory designs in many current research efforts do not incorporate the practical uncertainties into the closed loop of the design. A robust optimization design method for a nonlinear rendezvous trajectory with uncertainty is proposed in this paper. One performance index related to the variances of the terminal state error is termed the robustness performance index, and a two-objective optimization model (including the minimum characteristic velocity and the minimum robustness performance index) is formulated on the basis of the Lambert algorithm. A multi-objective, non-dominated sorting genetic algorithm is employed to obtain the Pareto optimal solution set. It is shown that the proposed approach can be used to quickly obtain several inherent principles of the rendezvous trajectory by taking practical errors into account. Furthermore, this approach can identify the most preferable design space in which a specific solution for the actual application of the rendezvous control should be chosen. © 2014 Science China Press and Springer-Verlag Berlin Heidelberg.
Gao Y.,State Key Laboratory of Astronautic Dynamics |
Gao Y.,Chinese Academy of Sciences |
Li H.-N.,State Key Laboratory of Astronautic Dynamics |
He S.-M.,Chinese Academy of Sciences
Acta Mechanica Sinica/Lixue Xuebao | Year: 2012
Chang'e-2, Chinese second lunar probe, was inserted into a 100 km altitude low lunar orbit on October 9th, 2010, its purpose is to continuously photograph the lunar surface and possibly chosen landing sites for future lunar missions. The probe will still carry considerable amount of propellant after completing all prescribed tasks in about six months. After the successful launch of Chang'e-2, we began designing the probe's subsequent flight scenario, considering a total impulse of 1 100 m/s for takeoff from low lunar orbit and a maximum 3×106 km distance for Earth-probe telecommunication. Our first-round effort proposed a preliminary flight scenario that involves consecutive arrivals at the halo orbits around the Earth-Moon L1/L2 and Sun-Earth L1/L2 points, near-Earth asteroid flyby, Earth return, and lunar impact. The designed solution of Chang'e-2's subsequent flight scenario is a multi-segment flight trajectory that serves as a reference for making the final decision on Chang'e-2's extended mission, which is a flight to the Sun-Earth L2 point, and a possible scheme of lunar impact via Earth flyby after remaining at the Sun-Earth L2 point was also presented. The proposed flight trajectory, which possesses acceptable solution accuracy for mission analysis, is a novel design that effectively exploits the invariant manifolds in the circular restricted three-body problem and the patched-manifold-conic method. © The Chinese Society of Theoretical and Applied Mechanics and Springer-Verlag Berlin Heidelberg 2012.
Xi T.,State Key Laboratory of Astronautic Dynamics |
Li J.C.,State Key Laboratory of Astronautic Dynamics |
Pan W.Q.,State Key Laboratory of Astronautic Dynamics
Applied Mechanics and Materials | Year: 2013
Spacecraft proximity formation flying is essential for future autonomous space mission such as autonomous rendezvous and docking and assembly of space system on-orbit. In order to improve the autonomy of relative motion control between two spacecrafts and concerning the effect of perturbation by bounded uncertain disturbance, a novel nonlinear adaptive feedback controller is developed based on sliding mode control law to maintain the desired reference trajectory as precisely as possible. The simulation results demonstrate the control scheme can effectively carry out the relative motion maintenance and have better asymptotically stability. © (2013) Trans Tech Publications, Switzerland.
Gao Y.,State Key Laboratory of Astronautic Dynamics |
Gao Y.,Chinese Academy of Sciences
Acta Mechanica Sinica/Lixue Xuebao | Year: 2013
Driven by curiosity about possible flight options for the Chang'e-2 spacecraft after it remains at the Sun-Earth L2 point, effective approaches were developed for designing preliminary fuel-optimal near-Earth asteroid flyby trajectories. The approaches include the use of modified unstable manifolds, grid search of the manifolds' parameters, and a two-impulse maneuver for orbital phase matching and z-axis bias change, and are demonstrated to be effective in asteroid target screening and trajectory optimization. Asteroid flybys are expected to be within a distance of 2 × 107 km from the Earth owing to the constrained Earth-spacecraft communication range. In this case, the spacecraft's orbital motion is significantly affected by the gravities of both the Sun and the Earth, and therefore, the concept of the "heliocentric oscillating-Kepler orbit" is proposed, because the classical orbital elements of the flyby trajectories referenced in the heliocentric inertial frame oscillate significantly with respect to time. The analysis and results presented in this study show that, among the asteroids whose orbits are the most accurately predicted, "Toutatis", "2005 NZ6", or "2010 CL19" might be encountered by Chang'e-2 in late 2012 or 2013 with total impulses less than 100m/s. © 2013 The Chinese Society of Theoretical and Applied Mechanics; Institute of Mechanics, Chinese Academy of Sciences and Springer-Verlag Berlin Heidelberg.
Wei P.-B.,Xidian University |
Zhang M.,Xidian University |
Niu W.,State Key Laboratory of Astronautic Dynamics |
Jiang W.-Q.,Xidian University
IEEE Transactions on Antennas and Propagation | Year: 2012
In the radar cross section (RCS) prediction of complex target, the intensive computational burden occurs while calculating the multiple scattering effect. In order to overcome the large computing, we present the program executing on graphics processing units (GPUs). In this paper, we analyze the scattering properties of the satellite, on which the antennas are described as cubes and columns, by employing the GPU-based combinational method of geometrical optics (GO) and physical optics (PO) together with the kd-tree technique. Furthermore, due to this distinctive treatment, the improved method yields a superior performance at high frequency. Some examples will be displayed in the following text. The agreement of the results yielded in this paper with the experimental and other exact results demonstrates the accuracy and efficiency of this useful technique. © 2012 IEEE.