Beijing Aerospace Command and Control Center

Beijing, China

Beijing Aerospace Command and Control Center

Beijing, China
SEARCH FILTERS
Time filter
Source Type

Xing J.,Beijing Aerospace Command and Control Center | Zhu H.,Beijing Aerospace Command and Control Center | Zou X.,Beijing Aerospace Command and Control Center
Journal of Aerospace Information Systems | Year: 2017

The unified scheduling language is a Chinese domain-specific language with both programming and natural language features for space mission scheduling. To create a functional and yet simple language for all space-missionrelated staff, a hybrid framework for language defining and interpreting is proposed. This framework combines script programming languages and natural language processing technologies, and it creates a language that is easy to learn yet still powerful to fulfill the automating and extending requirements of mission scheduling. A coordinated natural language processing approach is designed to parse human-oriented languages, and a general-purpose script engine is integrated for processing the script aspect of the unified scheduling language. The translating mechanism maintains logic consistency between the two parsers. Related logic models and algorithms are introduced to illustrate the parsing mechanism. This framework achieves sound practical results in the unified scheduling language, considering a valid domain-specific language system is built and parsed correctly. The framework can be generalized to other Chinese domain-specific languages in various application fields. © Copyright 2017 by Jinjiang Xing. Published by the American Institute of Aeronautics and Astronautics, Inc.


Zhao Y.,National University of Defense Technology | Zhang Y.-S.,Beijing Institute of Technology | Yi D.-Y.,National University of Defense Technology | Zhang Q.,Beijing Aerospace Command and Control Center
Yuhang Xuebao/Journal of Astronautics | Year: 2011

The problem of multi-target/multi-sensor management for tracking coasting-phase targets by means of sensors located on the LEO satellite constellation is studied. The coasting-phase target dynamics model and the satellite-borne IR sensor measurement model are reviewed. Considering the space-time uncertainties events of targets emergence, the unexpected-event and rolling-period (UERP) based management framework, together with the closed-form structure composed of sensor management and target track, is established to realize the excellent tracking performance. Furthermore, a detailed management algorithm is proposed. Specially, aiming to maximize the system's information increment in the scheduling period, the PCRLB based performance criteria is explicitly deducted to evaluate the system performance in terms of tracking error which is dependent on different sensor placements. The numerical simulations are implemented to confirm that the proposed management algorithm is provided with feasibility, superiority and adaptability confronted with the scenario of varying number of targets.


Zhao Y.,National University of Defense Technology | Yi D.,National University of Defense Technology | Li Y.,Victoria University of Melbourne | Zhang Q.,Beijing Aerospace Command and Control Center
Proceedings of 2010 International Conference on Intelligent Control and Information Processing, ICICIP 2010 | Year: 2010

For space-based bearing-only observations, the initial state estimation of the boost phase object is the solution to the nonlinear Least squared estimation (LSE) problem. This paper transformed the nonlinear problem into a linear LSE problem using the linearization of the bearing-only measurement and the target trajectory, which facilitated the direct estimation of initial state whilst avoiding to use the Gauss-Newton iteration. In particular, the explicit derivation of the pseudo-linear measurement and its statistical moments are deduced, which helped to determine the applying conditions of the proposed method. The numerical simulations illustrated the advantage of the proposed method with respect to precision and efficiency. © 2010 IEEE.


Zhao Y.,National University of Defense Technology | Yi D.,National University of Defense Technology | Li Y.,Victoria University of Melbourne | Zhang Q.,Beijing Aerospace Command and Control Center
Proceedings - 2010 3rd IEEE International Conference on Computer Science and Information Technology, ICCSIT 2010 | Year: 2010

In this paper, the relative sensor-target geometry for bearing-only localization in 3-dimensional space is characterized. Aiming to characterize and state explicit results in terms of the potential localization performance, the geometry in terms of the Cramer-Rao lower bound and the corresponding Fisher information matrix is studied. Specially, the formulation of the Fisher information matrix on the basis of the single sensor and its geometrical comprehension are derived, and the relationship of the geometrical characterizations to the Fisher information matrix, thus to the bearing-only localization with two sensors is explored and represented © 2010 IEEE.


Zhao Y.,National University of Defense Technology | Li Y.,Victoria University of Melbourne | Zhang Q.,Beijing Aerospace Command and Control Center
Proceedings of 2010 International Conference on Intelligent Control and Information Processing, ICICIP 2010 | Year: 2010

This paper introduced the adoption of a Track Sensor on the satellite of the STSS to improve the precision of the STSS. The concepts of space coverage were proposed and the corresponding models established. A simplified computation strategy of space coverage was proposed to obtain the simulation results. Space coverage rate under different scenarios was simulated as well as its characteristics illustrated. Finally, a valuable result about the optimal orbit altitude for the given working distance of the Track Sensor regardless of the specific constellation was obtained. © 2010 IEEE.


Yan J.,Wuhan University | Yan J.,Japan National Astronomical Observatory | Goossens S.,Japan National Astronomical Observatory | Matsumoto K.,Japan National Astronomical Observatory | And 11 more authors.
Planetary and Space Science | Year: 2012

Using Chang'E-1 orbital tracking data, in combination with orbital tracking data of SELENE, Lunar Prospector, and historical spacecraft, a lunar gravity field model denoted CEGM02 is developed. Analyses show that due to its higher orbit altitude (200 km), tracking data of Chang'E-1 contribute to the long wavelengths of the lunar gravity field. When compared to SGM100h, formal error of CEGM02 coefficients below degree 5 is reduced by a factor of about 2. Lunar mean moment of inertia is found to be 0.393466±0.000065, which can be served as a strong constraint in lunar internal structure research. Lunar potential Love number k 2 is estimated to be 0.0242±0.0004 (ten times the formal error), which may provide better constraints on lunar interior by combination with lunar moments of inertia. © 2011 Elsevier Ltd. All rights reserved.


Zhao Y.,National University of Defense Technology | Cheng H.-W.,Beijing Institute of Technology | Yi D.-Y.,National University of Defense Technology | Zhang Q.,Beijing Aerospace Command and Control Center
Dianzi Yu Xinxi Xuebao/Journal of Electronics and Information Technology | Year: 2010

The initial state estimation for boost phase object is an important issue to estimate the missile's tactical parameters, as well as the precondition for the surveillance system to perform the real-time tracking. In the condition of the space-based observations, the initial state estimation is the solution of the nonlinear LSE problem. Firstly, the 8-state gravity turn model for the boost phase object is established, and then the target's kinematic parameters are approximated by using the linear constant acceleration derivative model, and the nonlinear measurements are pseudo linearized. Therefore, the nonlinear LSE problem is translated into the linear LSE problem after the aforementioned steps . Specially, in this paper, the explicit derivation of the pseudo linearized space-based observation and its statistical moments are deduced, and its application conditions are illuminated. Finally, the advantage of the proposed method is illustrated in the aspects of precision and efficiency by comparing with the CRLB and classical Gauss-Newton iteration algorithm.


Yan J.,Wuhan University | Yan J.,Austrian Academy of Sciences | Zhong Z.,Wuhan University | Zhong Z.,Guizhou Normal University | And 5 more authors.
Advances in Space Research | Year: 2013

We analyzed the 150 × 150 lunar gravity field models, LP150Q, GLGM-3 and SGM150, using the power spectrum on the lunar nearside and farside, the lunar global and localized gravity/topography admittance and correlation, and Chang'E-2 precision orbit determination to investigate which model is a more effective tool to estimate geophysical parameters and determine the lunar satellite precision orbit. Results indicate that all gravity field models can be used to estimate the lunar geophysical parameters of the nearside of the Moon. However, SGM150 is better in such computation of the farside. Additionally, SGM150 is shown to be the most useful model for determining the lunar satellite orbit. © 2013 COSPAR. Published by Elsevier Ltd. All rights reserved.


Zhang Y.,Beijing Aerospace Command and Control Center | Sun Z.-J.,Beijing Aerospace Command and Control Center | Li J.,Beijing Aerospace Command and Control Center
Xitong Fangzhen Xuebao / Journal of System Simulation | Year: 2011

The DCSP models on different disturbance factors including changing mission time request, adding new mission, resource failure were established to solve TDRS dynamic scheduling problem. Moreover, DEDTS was designed, which adopted the ratio of delete mission parameter to change mission parameter directing search combining conflict chain. DEDTS reflects the user request on search process, then it improves usability and efficiency of algorithm. Simulation results indicate the validity of this method.


Zheng Y.,Academy of Equipment Command and Technology | Sun H.,Academy of Equipment Command and Technology | Zhao Y.,Academy of Equipment Command and Technology | Zhang L.,Beijing Aerospace Command and Control Center
Hongwai yu Jiguang Gongcheng/Infrared and Laser Engineering | Year: 2015

The cat-eye effect based active laser detection technique has a broad prospect in antimissile and air defense field, while the distortion effect on the incident and reflected waves caused by aerodynamic flow field around the planes and missiles is an important part of the echo wave characteristic analysis. Facing the complicated physical process of the laser waves in the cat-eye lenses and aerodynamic flow field both in the incidence and reflection propagation, a Zemax based aero-optical distortion calculation method was proposed. Firstly, based on finite element theory, the aero-optical flow field was divided into multiple layers according to the refractive index gradient. Secondly, curve surface fitting of the interfaces between the layers was done with standard, even asphere and Zernike polynomial surface, then a multilayer lens group model with different refractive index was established in Zemax, and the whole incidence and reflection Zemax model was accomplished with imaging optical system added in. Take a typical missile model as the example, the computational fluid dynamics and optical propagation distortion simulation in Zemax were performed, the feasibility of this method was validated after comparing with the analytical results of ray tracing. © 2015, Editorial Board of Journal of Infrared and Laser Engineering. All right reserved.

Loading Beijing Aerospace Command and Control Center collaborators
Loading Beijing Aerospace Command and Control Center collaborators