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Hu X.,Shaanxi Baocheng Aviation Instrument Co.
Zhongguo Guanxing Jishu Xuebao/Journal of Chinese Inertial Technology | Year: 2010

Avionics map mainly presents the aviation-related topographic factor and aviation factor, and can be used to study the aviation area, determine the routes and the aircraft position and flight direction as well as the implementation of the air commands. It is embedded in the carrier equipment as a database, which can be used as an important signal source and reference point for communications, navigation, guidance and control systems, to complete the system functions and fly missions with them. The digital elevation model and database development are key technologies of the avionics map research. Avionics map has broad application prospects in the flight simulator simulation, battle command, and weapons systems terrain contour matching navigation. Source


Zhang Y.-F.,Shaanxi Baocheng Aviation Instrument Co. | Yao S.-H.,Shaanxi Baocheng Aviation Instrument Co. | Cheng X.-Z.,Office of Military Representatives Station in Northwest China for Peoples Liberation Army Air Force | Duan L.-Y.,Shaanxi Baocheng Aviation Instrument Co.
Zhongguo Guanxing Jishu Xuebao/Journal of Chinese Inertial Technology | Year: 2015

By analyzing the forces on the pendulum assembly of the suspension-wire pendulous accelerator at 0° and 180° positions, the relationship between unbalance S and misalignment swing-angle δ0 of the pendulum assembly is revealed. Based on the accelerator's structure, three methods for reducing the unbalance of the pendulum assembly are presented. The feasibilities and adverse effects of the three methods are analyzed. The linear relationship between E0 and S is obtained by calculating the relationship between δ0 and the output E0 at 0° position, and then the detectable E0 can be used instead of rarely detectable S to detect the pendulum assembly's unbalance. The method and procedure for controlling unbalance S of the pendulum assembly by detectable and controllable parameter E0 are derived, and the relationships between E0 and misalignment variation Δδ0G and Δδ0D at high and low temperatures are experimentally obtained, respectively, and the maximum value of control parameter E0 is determined. Practical application indicates that the control method and procedure are feasible and effective and with reasonable controlled maximum E0, which can also provide reference for dealing with other accelerators. ©, 2015, Editorial Department of Journal of Chinese Inertial Technology. All right reserved. Source


Zeng Q.-H.,Nanjing University of Aeronautics and Astronautics | Huang L.,Nanjing University of Aeronautics and Astronautics | Huang L.,Nanjing Forestry University | Liu J.-Y.,Nanjing University of Aeronautics and Astronautics | And 2 more authors.
Zhongguo Guanxing Jishu Xuebao/Journal of Chinese Inertial Technology | Year: 2015

The modeling and filtering methods of FOG random noise based on ARMA (Auto-Regressive and Moving Average) model are studied. A new method for whitening colored system noise is presented to solve the problem that colored system noise can not be whitened by traditional state-expand methods: The parameters as well as the white noise of ARMA model are estimated by extended least squares (ELS) algorithm; Then the colored system noise can be whitened by being expanded to system equation as control input term; By Sage-Husa's maximum a posteriori(MAP) noise estimator, the estimated mean and variance of the system noise are achieved; Finally an adaptive Kalman filter is employed to eliminate the error and achieve accurate state estimation. Test results indicate that, for the FOG which output noise has trailing characteristics on both self-correlation and partial correlation, the noise reduction effect based on the new filtering method is improved by >10% compared with that of traditional AR model-based methods. ©, 2015, Editorial Department of Journal of Chinese Inertial Technology. All right reserved. Source


Liu M.,Nanjing University of Aeronautics and Astronautics | Lai J.-Z.,Nanjing University of Aeronautics and Astronautics | Huang K.,Shaanxi Baocheng Aviation Instrument Co. | Liu J.-Y.,Nanjing University of Aeronautics and Astronautics | Wang W.,Nanjing University of Aeronautics and Astronautics
Zhongguo Guanxing Jishu Xuebao/Journal of Chinese Inertial Technology | Year: 2015

In view that the receiver autonomous integrity monitoring is not available when there are not enough visible satellites or many satellites simultaneously malfunction, an airborne autonomous integrity monitoring method is presented which is based on weighted parity vector and aided by land-based navigation system. The observation equation of the monitoring system is established by using slope range of the land-based navigation system and the observations of GPS pseudorange. Test statistics is constructed to diagnose fault satellites by the weighted parity vector method. Simulation results show that this method can accurately identify fault satellites in time, and thus ensure the integrity of satellite navigation system and the positioning accuracy of the integrated navigation, showing that it has great reference value for engineering applications. ©, 2015, Editorial Department of Journal of Chinese Inertial Technology. All right reserved. Source


Chen Z.,Nanjing University of Aeronautics and Astronautics | Lai J.-Z.,Nanjing University of Aeronautics and Astronautics | Chen L.-J.,Shaanxi Baocheng Aviation Instrument Co. | Liu J.-Y.,Nanjing University of Aeronautics and Astronautics | Liu M.,Nanjing University of Aeronautics and Astronautics
Zhongguo Guanxing Jishu Xuebao/Journal of Chinese Inertial Technology | Year: 2015

Since China's Beidou satellite navigation system has unique constellation structure which consists of GEO (Geostationary Orbit), MEO (Medium Earth Orbit) and IGSO (Inclined Geosynchronous Satellite Orbit) Satellites, the common tightly integrated algorithm is not completely applicable. To solve this problem, an improved algorithm is proposed based on the analysis of the pseudorange measurement noise model of different orbit types of Beidou satellites. In order to construct a more accurate fusion model, three kinds of Beidou satellites are used to implement states extension and measurement. Simulation results show that the designed algorithm can increase the positioning precision by more than 50%, showing that it can provide great reference for the following development and application of Beidou system. ©, 2015, Editorial Department of Journal of Chinese Inertial Technology. All right reserved. Source

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