2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)

Conference Information
Name: 2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC)
Location: Nanjing, China
Date: 2016-8-12 - 2016-8-14

Latest articles from this conference

Zhenxing You, Zhihao Cai, Yingxun Wang, Tingting Wang, Yu Zhang
2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC) pp 779-784; https://doi.org/10.1109/cgncc.2016.7828884

In view of the applications on the small unmanned aircrafts (UAVs), the data noises of Attitude and Heading Reference System (AHRS) has a great influence on the accuracy of attitude estimation of UAVs. This paper analyses the characteristics of the measurement data noises of AHRS in the time domain and frequency domain, and puts forwards corresponding filtering algorithm, combining with attitude estimation algorithm by fusing multi-sensors. Experiments are carried on to verify the effectiveness of the filter algorithm.
, Wei An, , Lihua Wu, Xueying Wang
2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC) pp 998-1001; https://doi.org/10.1109/cgncc.2016.7828922

A modified particle filter is proposed and applied in real-time extracting of laser ranging information in this paper. We propose a particle of line type which can fit the character of laser echoes accurately and introduce it to the traditional particle filter algorithm. Further, the proposed line type particle filter is tested with simulation data and several real data from different earth-based laser ranging devices. The results demonstrate the good performance of the proposed line type particle filter in laser ranging information extracting.
Yong-Kang Jiao, Kun-Hu Kou, Yong Chen
2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC) pp 238-240; https://doi.org/10.1109/cgncc.2016.7828790

The establishment of accurate engine performance model could greatly improve the fidelity of flight simulator. The mean value model of the UAV piston engine was made up by adopting the method of combination mechanism modeling and experimental modeling, while the simulation of the engine was carried out under MATLAB/SIMULINK environment. The simulation results indicated that the established model could describe the operating characteristic of the engine and laid the foundation of further development of the flight simulator.
Zuo Jingxing, Wu Yunjie, Li He
2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC) pp 1454-1459; https://doi.org/10.1109/cgncc.2016.7829003

A novel approach for disturbance observing assisted by terminal sliding mode is proposed, due to the fact that the traditional disturbance observer underestimates the high frequency disturbances in flight simulator system. One terminal sliding mode surface and a new kind of control scheme is defined, which makes the system meet the stability condition. Estimation and compensation of the high frequency disturbances are available by the high-speed switching controller in the auxiliary system. Then the high accuracy control for the flight simulator is achieved with the help of sliding mode controller. The experiment on one flight simulator shows that, controller based on terminal sliding mode assist disturbance observer has a better performance with more robustness against external disturbance in angle tracking than the controller based on traditional disturbance observer.
Wenying Chen, Libin Yang, Weiliang Liu, Yinsong Wang, Ng Wang
2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC) pp 1840-1844; https://doi.org/10.1109/cgncc.2016.7829069

In order to raise the efficiency of the small permanent magnet direct-drive wind power generation system, this paper presents a wind speed estimation model using FASVR(Firefly Algorithm & Support Vector Regression) method, which takes the turbine rotor speed signal and mechanical power signal as inputs. A MPPT(Maximum Power Point Tracking) control method is proposed based on the wind speed estimation model and P&O (Perturb and Observe) algorithm, and the effectiveness is verified by simulation results.
Yaozhong Yu, Chen Yang, Hong Jiang, Tianqu Zhao
2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC) pp 2321-2324; https://doi.org/10.1109/cgncc.2016.7829153

This paper introduces a nonlinear composite control, method, i.e., a combination of time optimal control (TOC) and PID control, for double integrating systems with input saturation. The TOC part is designed to enable the time optimization. Unfortunately, it is well known that the classical TOC is not robust with respect to the system uncertainties and measurement noises. Therefore, we proposed the method to solve the drawback of TOC. In the method, when the error is small to a certain level, it will switches to the PID part to overcome the chatter problem caused by the TOC. Finally, the simulation results, approximate time optimization and fair robustness demonstrate the effectiveness and feasibility of the proposed method.
Liang Duanzhang, Cheng Peng, Cheng Nong
2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC) pp 1969-1974; https://doi.org/10.1109/cgncc.2016.7829091

Earlier flights relied mainly on ground-based navigation aids. As a result, waypoints were defined by the relative position to navigation aids. As navigation technology evolves, the application of Global Navigation Satellite System becomes more popular [1]. The coordinates of each waypoint can be precisely defined in the WGS84 coordinate system. Therefore, accurate coding of flight procedures using only the TF and RF legs is preferred. In order to be compatible with old flight procedures, advanced FMS (flight management system) must be able to deal with these inaccurate legs. To solve this problem, a generic trajectory prediction and smoothing algorithm is proposed. The accurate starting and terminating point of each inaccurate leg is calculated along the trajectory predicting process according to its definition. Also, smooth transitions between adjacent legs are established using RF legs. Simulation results show that the generated trajectories of this algorithm are accurate and can be well performed by various aircrafts.
Siyang Zhang, Shuquan Wang
2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC) pp 1905-1910; https://doi.org/10.1109/cgncc.2016.7829080

This paper investigates the configuration control of two-craft Lorentz force formation. The Lorentz force is generated by actively controlling the charge of the deputy flying around the chief with an electromagnetic device installed. The system's equation of motion is developed based on the Hill's equation. Three sets of non-trivial equilibrium are identified. Among all the three sets of equilibrium, two of them are unstable but controllable, while the other one is unstable and uncontrollable. State space based linear controller is developed to stabilize the configuration to the equilibrium. Multiple cases are simulated to demonstrate the effectiveness of the control algorithm.
Yuxia Liu, Peng Zhang
2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC) pp 748-752; https://doi.org/10.1109/cgncc.2016.7828879

In order to realize geomagnetism aided navigation (GAN) in the regions with insignificant geomagnetic characteristic, inspired by the pattern recognition idea, the geomagnetic matching (GM) problem was transformed into statistical pattern recognition and was analyzed from the aspect of pattern recognition. A matching algorithm based on support vector machine (SVM) was proposed. The selection of training sample for SVM, the relation between the parameter of the SVM and the geomagnetic roughness were studied. Then a SVM was constructed for GM. Simulation results show that the proposed method can greatly improve the efficiency and achieve better performance than ordinary correlative matching algorithm. The accuracy of matching method is less than the unit cell size of the geomagnetic map.
Daoguang Tang, Hui Wang, Qiugui Song
2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC) pp 1429-1435; https://doi.org/10.1109/cgncc.2016.7828999

The open loop guidance dynamics and hardware demands in engineering systems of the ground attack terminal guidance laws are analyzed. It shows that the proportional navigation (PN) guidance law has a lower demand of the hardware measuring precision and a faster guidance dynamic than the other “angle” guidance laws. As the representative of the ground attack terminal guidance laws, a comparative guidance model for the proportional navigation and velocity pursuit (VP) is established. The comparison research work on the guidance precision is implemented employing the non-dimensional technique and method of adjoints when the initial heading error, seeker angle zero position error, seeker noise and target glint noise are introduced into the PN/VP guidance system. The results show that to eliminate the miss distance due to the initial heading error, a long terminal guidance time is necessary for VP and when the terminal guidance time is short, the miss of VP is larger than that of PN. With the increasing of the terminal guidance time, the VP's miss distance due to the seeker angle zero position error approaches to a stable value and cannot be eliminated, while PN can eliminate the miss due to the seeker angle zero position error when the guidance ratio N≥3. In addition, the PN miss distance due to seeker noise and glint noise is larger than VP, implying that when the seeker noise and glint noise is too large, the proportional navigation guidance law is not applicable. Finally, the most appropriate guidance law can be selected according to the relations of the missile system hardware, the guidance signal types, the guidance signal quality and the missile total tactical demands.
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