Beijing System Design Institute of Electro mechanic Engineering

Beijing, China

Beijing System Design Institute of Electro mechanic Engineering

Beijing, China
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Wang J.,Beijing System Design Institute of Electro Mechanic Engineering | Zhong S.,Beijing System Design Institute of Electro Mechanic Engineering | Jiang Y.,China Aerospace Science and Technology Corporation
CGNCC 2016 - 2016 IEEE Chinese Guidance, Navigation and Control Conference | Year: 2016

An involute guidance laws with terminal velocity direction constraint have been proposed for terminal maneuver unpowered reentry vehicle. According to the flight characteristics of unpowered vehicles and the geometric properties of the involute of a circle, an involute trajectory was generated by two positions of vehicle and target and an impact angle between the desired terminal velocity and line of sight. And a 3-D trajectory tracking guidance method is designed based on the error of flight path angle and heading angle for achieving accurate tracking of the involute trajectory. Simulation results demonstrated that the involute guidance laws can guide the vehicle accurately arriving the target point with the directed the terminal impact angle constraint, and are superior to the circular guidance laws in curvature, required acceleration and terminal speed. The involute guidance laws have a high engineering application value. © 2016 IEEE.


LI M.,Harbin Engineering University | LU L.,Beijing System Design Institute of Electro Mechanic Engineering | DAI Z.,Beijing System Design Institute of Electro Mechanic Engineering | HONG Y.,Beijing System Design Institute of Electro Mechanic Engineering | And 3 more authors.
Surface Review and Letters | Year: 2017

Amorphous Al–Cu–Ti metal foams were prepared by spark plasma sintering (SPS) process with the diameter of 10(Formula presented.)mm. The SPS process was conducted at the pressure of 200 and 300(Formula presented.)MPa with the temperature of 653–723(Formula presented.)K, respectively. NaCl was used as the space-holder, forming almost separated pores with the porosity of 65 vol%. The microstructure and mechanical behavior of the amorphous Al–Cu–Ti metal foams were systematically investigated. The results show that the crystallinity increased at elevated temperatures. The effect of pressure and holding time on the crystallization was almost negligible. The intermetallic compounds, i.e. Al–Ti, Al–Cu and Al–Cu–Ti were identified from X-ray diffraction (XRD) patterns. It was found that weak adhesion and brittle intermetallic compounds reduced the mechanical properties, while lower volume fraction and smaller size of NaCl powders improved the mechanical properties. © 2018 World Scientific Publishing Company


Wang X.,Beijing Institute of Technology | Guo J.,Beijing Institute of Technology | Tang S.,Beijing Institute of Technology | Xu Q.,China Aerospace Science and Technology Corporation | And 3 more authors.
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | Year: 2017

A new nonlinear disturbance observer based Terminal sliding mode backstepping controller is proposed for flexible air-breathing hypersonic vehicles with parameter perturbations and external disturbances. The longitudinal vehicle model considering the elastic mode is expressed as strict feedback form. On the basis of traditional backstepping method, the nonsingular fast Terminal sliding mode is introduced to control the pitch angle and pitch rate, thus optimizing the control structure and enabling the system with finite time convergence property. A new nonlinear disturbance observer developed from tracking differentiator is then introduced to estimate and compensate the uncertainties including the derivatives of virtual control laws to improve the robustness of the controller, which avoids the explosion of differentiation terms. The system tracking error is proven to converge to zero in finite time with Lyapunov stability theory. Simulations demonstrate the effectiveness of tracking input commands with the designed controller in the presence of uncertainties. © 2017, Press of Chinese Journal of Aeronautics. All right reserved.


Liu D.,Harbin Institute of Technology | Luo Y.,Beijing System Design Institute of Electro Mechanic Engineering | Liu J.,Carleton University | Peng Y.,Harbin Institute of Technology | And 2 more authors.
Neural Computing and Applications | Year: 2013

The lithium-ion battery cycle life prediction with particle filter (PF) depends on the physical or empirical model. However, in observation equation based on model, the adaptability and accuracy for individual battery under different operating conditions are not fully considered. Therefore, a novel fusion prognostic framework is proposed, in which the data-driven time series prediction model is adopted as observation equation, and combined to PF algorithm for lithium-ion battery cycle life prediction. Firstly, the nonlinear degradation feature of the lithium-ion battery capacity degradation is analyzed, and then, the nonlinear accelerated degradation factor is extracted to improve prediction ability of linear AR model. So an optimized nonlinear degradation autoregressive (ND-AR) time series model for remaining useful life (RUL) estimation of lithium-ion batteries is introduced. Then, the ND-AR model is used to realize multi-step prediction of the battery capacity degradation states. Finally, to improve the uncertainty representation ability of the standard PF algorithm, the regularized particle filter is applied to design a fusion RUL estimation framework of lithium-ion battery. Experimental results with the lithium-ion battery test data from NASA and CALCE (The Center for Advanced Life Cycle Engineering, the University of Maryland) show that the proposed fusion prognostic approach can effectively predict the battery RUL with more accurate forecasting result and uncertainty representation of probability density distribution (pdf). © 2013 Springer-Verlag London.


Du J.,Beihang University | Du J.,Beijing System Design Institute of Electro mechanic Engineering | Wang S.,Beihang University | Zhang H.,Purdue University
Mechanical Systems and Signal Processing | Year: 2013

Efficient diagnosis is very important for improving reliability and performance of aircraft hydraulic piston pump, and it is one of the key technologies in prognostic and health management system. In practice, due to harsh working environment and heavy working loads, multiple faults of an aircraft hydraulic pump may occur simultaneously after long time operations. However, most existing diagnosis methods can only distinguish pump faults that occur individually. Therefore, new method needs to be developed to realize effective diagnosis of simultaneous multiple faults on aircraft hydraulic pump. In this paper, a new method based on the layered clustering algorithm is proposed to diagnose multiple faults of an aircraft hydraulic pump that occur simultaneously. The intensive failure mechanism analyses of the five main types of faults are carried out, and based on these analyses the optimal combination and layout of diagnostic sensors is attained. The three layered diagnosis reasoning engine is designed according to the faults' risk priority number and the characteristics of different fault feature extraction methods. The most serious failures are first distinguished with the individual signal processing. To the desultory faults, i.e., swash plate eccentricity and incremental clearance increases between piston and slipper, the clustering diagnosis algorithm based on the statistical average relative power difference (ARPD) is proposed. By effectively enhancing the fault features of these two faults, the ARPDs calculated from vibration signals are employed to complete the hypothesis testing. The ARPDs of the different faults follow different probability distributions. Compared with the classical fast Fourier transform-based spectrum diagnosis method, the experimental results demonstrate that the proposed algorithm can diagnose the multiple faults, which occur synchronously, with higher precision and reliability. © 2012 Elsevier Ltd.


Guo L.,Harbin Institute of Technology | Peng Y.,Harbin Institute of Technology | Liu D.,Harbin Institute of Technology | Luo Y.,Beijing System Design Institute of Electro Mechanic Engineering
2014 International Conference on Prognostics and Health Management, PHM 2014 | Year: 2015

Due to the high performance on state tracking and predicting, particle filter (PF) algorithm has been utilized for diagnosis and prognosis in a variety of areas. Especially, PF can provide uncertainty representation and management on estimating the remaining useful life (RUL) of components and systems. However, particle degeneracy phenomenon limits its performance and application in most of the situations. Therefore, several re-sampling algorithms are proposed to alleviate this problem. Thus, different re-sampling algorithms should be focused and studied for the adaptability and applicability in RUL estimation. This work aims to compare the capabilities of different re-sampling algorithms and evaluate the performance in lithium-ion battery RUL prediction. Four re-sampling algorithms including multinomial re-sampling, residual re-sampling stratified re-sampling and systematic re-sampling are involved and analyzed. Actual battery test data sets from NASA PCoE are used to conduct experiments for evaluation and comparison. Moreover, some quantitative analysis metrics are applied to compare the results of battery RUL estimation. © 2014 IEEE.


Liu D.,Harbin Institute of Technology | Luo Y.,Beijing System Design Institute of Electro Mechanic Engineering | Guo L.,Harbin Institute of Technology | Peng Y.,Harbin Institute of Technology
PHM 2013 - 2013 IEEE International Conference on Prognostics and Health Management, Conference Proceedings | Year: 2013

The uncertainty of prognostics and remaining useful life (RUL) estimation for the lithium-ion battery is emphasized in the battery management system (BMS). Many machine learning algo rithms and statistical methods can not only realize the RUL prediction but also provide the probability density function (PDF) as the prognostic uncertainty representation, involving particle filter (PF), Relevance Vector Machine (RVM), etc. This paper presents a fusion RUL prediction approach with PF algorithm and data-driven autoregression (AR) algorithm for lithium-ion battery. Moreover, a framework to quantitatively analyze and evaluate the PDF distribution of the lithium-ion battery RUL prediction is presented. The probability confidence interval estimation, PDF histogram and distribution hypothesis test are included in quantifying the uncertainty. These quantitative analysis results can be meaningful for lithium-ion battery health management and maintenance. The experimental results with the battery data of NASA Ames Prognostics Data Repository show that the proposed framework can achieve the quantification of PDF to introduce the reference for the corresponding maintenance and management. The proposed work also shows pote ntial prospective for industrial application. © 2013 IEEE.


Zeng X.-F.,Beijing Institute of Technology | Wang J.-Y.,Beijing System Design Institute of Electro Mechanic Engineering | Wang X.-H.,Beijing Institute of Technology
Xi Tong Gong Cheng Yu Dian Zi Ji Shu/Systems Engineering and Electronics | Year: 2013

For hypersonic gliding problem, a gliding guidance approach based on energy and analytical predictor corrector is proposed. In this approach, the gliding guidance is divided into two parts: longitudinal guidance and lateral guidance. In the longitudinal guidance, analytical mathematical formulas of range-to-go and energy, bank angle are established based on quasi-equilibrium gliding condition to analytically predict range-to-go, and then the bank angle magnitude is calculated online through the correct algorithm to satisfy the range-to-go and energy request. An angle of attack adjustment algorithm based on altitude is proposed to achieve quasi-equilibrium gliding and make sure that the terminal altitude and velocity constraints are met. In the lateral guidance, a lateral threshold based on cross range and range-to-go is proposed to determine the sign of bank angle command and control terminal heading error.compared with the traditional numerical predictor-corrector guidance method, the calculation cost of the proposed approach is significantly reduced, and the guidance precision and adaptation are good.


Wang J.-Y.,Beijing System Design Institute of Electro Mechanic Engineering | Jiang Y.,Changfeng Electromechanical Technology Design Academy | Zhong S.-Y.,Beijing System Design Institute of Electro Mechanic Engineering
Yuhang Xuebao/Journal of Astronautics | Year: 2016

A high accuracy analytical estimation method for glide range is proposed to solve the current problem of the low accuracy of hypersonic glide trajectory analytical estimation. In this approach, an analytical formula of glide range, lift to drag ratio, initial velocity and final velocity is established from the perspective of unit mass mechanical energy. By using quasi equilibrium glide conditions, the equilibrium function of glide altitude and kinetic energy is derived, and the glide range is corrected. The estimation precision of the gliding range is improved significantly in the case of small change of flight path angle. Finally, the simulation results show that the errors between the analytical estimation results and the numerical simulation results are less than 1%, which indicate that the precision of the analytical estimation approach is high. As a result, the analysis results can provide theoretical basis for analyzing the performances of glide trajectory, estimating the glide range and planning trajectory online of hypersonic long-range missile. © 2016, Editorial Dept. of JA. All right reserved.


Wang J.-Y.,Beijing System Design Institute of Electro Mechanic Engineering | Jiang Y.,Changfeng Electromechanical Technology Design Academy | Zhong S.-Y.,Beijing System Design Institute of Electro Mechanic Engineering | Xiong L.-F.,Beijing System Design Institute of Electro Mechanic Engineering
Yuhang Xuebao/Journal of Astronautics | Year: 2016

An analytical method of trajectory parameter estimation is proposed for the boost-glide trajectory of hypersonic long-range missile. From the view of energy, an analytical estimation formula of gliding range and flight time is established by using the quasi-equilibrium gliding conditions. Then the effectiveness of glide trajectory parameters such as lift-drag ratio and initial velocity on range and time is studied. Moreover, the range and flight time characteristics of minimum energy elliptical trajectory are analyzed theoretically. Based on the analytical formula, the range and time characteristics of the glide trajectory and the elliptical trajectory under various conditions are compared. Also a criterion on determining the best application scope of the two trajectories is proposed. Finally, the simulation results show that the errors between the analytical estimation results and the numerical simulation results are less than 2%, indicating that the precision of the analytical estimation approach is high. As a result, the performances of glide trajectory may be analyzed reliably and effectively by use of the analytical method, and the analysis results may be provided for the preliminary selection of the trajectory scheme. © 2016, Editorial Dept. of JA. All right reserved.

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