Avic Aerospace Life Support Industries Ltd

Hugang, China

Avic Aerospace Life Support Industries Ltd

Hugang, China

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Wang Z.,Beihang University | Fan H.,Beihang University | Liang H.,University of Science and Technology Beijing | Ma J.,University of Science and Technology Beijing | And 3 more authors.
Electrochimica Acta | Year: 2017

Carbon supported FePt and FePtSn alloy nanocrystals were synthesized via a hybrid microfluidic-batch process. Their microstructures and compositions were characterized by transmission electron microscopy, high resolution transmission electron microscope, energy dispersive X-ray spectrometer, X-ray powder diffraction and X-ray photoelectric spectroscopy. All the nanocatalysts show a homogeneous distribution of ultra-small alloy nanoparticles (∼2–3 nm) on the surface of carbon black. The electrochemical results indicate that FePtSn/C nanocatalysts have more excellent catalytic activity for methanol oxidation compared with Pt/C catalyst. Chronoamperometry measurements were performed at 0.45 V for 3600 s. At 3600 s, the mass specific activity of FePtSn/C (Sn at% = 14) can retain 103 mA mgPt −1, about 10 times higher than that of Pt/C catalyst (10 mA mgPt −1). The CO-stripping tests indicate that FePtSn/C (Sn at% = 14) nanocatalysts preserve a high electrochemical active specific surface and a higher ability to resist poisons, thus making the FePtSn/C (Sn at% = 14) catalyst an excellent electrocatalyst for direct methanol fuel cells. © 2017 Elsevier Ltd


Zhang B.,Nanjing University of Technology | Chen L.,AVIC Aerospace Life support Industries Ltd | Yang X.,Nanjing University of Technology | Xu T.,Nanjing University of Technology | And 3 more authors.
Journal of Materials Science: Materials in Electronics | Year: 2017

A luminescent lanthanide coordination polymer (Ln-CP) of [Tb2(SA)3(H2O)2]·2H2O [SA: succinic acid] has been largely prepared by co-precipitation method at room temperature. Powder X-ray diffraction (PXRD), elemental microanalysis, Fourier transform infrared spectra (FT-IR), thermogravimetric analysis (TGA) were used to confirm the composition and phase purity of the prepared powder material. The photoluminescent and sensing properties of the powders have been studied. The results show that Tb-SA powders exhibits characteristic luminescence of Tb3+ ion, and present the selective detection of Fe3+ in aqueous solution. There is an inverse correlation between the luminescent intensities and concentration of Fe3+ ions, which displays a linear region at low concentrations (1 × 10−5 to 8 × 10−4 M), but deviates from linearity at higher concentrations. Furthermore, the potential quenching mechanism was proposed. © 2017 Springer Science+Business Media New York


Minsheng G.,AVIC Aerospace Life support Industries LTD | Jinling Z.,AVIC Aerospace Life support Industries LTD | Wenbo S.,AVIC Aerospace Life support Industries LTD
Proceedings - Annual SAFE Symposium (Survival and Flight Equipment Association) | Year: 2014

The ejection velocity control technique plays a key role in the ejection escape test. In order to solve the problem existing in the original passive fixed-point control method, a new concept of active non-fixed point control is proposed. This paper presented the high reliability and safety of the active velocity window control system, and put forward some improvement suggestions according to the application conditions.


Shen W.-B.,AVIC Aerospace Life support Industries LTD | Min L.-W.,AVIC Aerospace Life support Industries LTD | Hong T.,AVIC Aerospace Life support Industries LTD | Gong M.,AVIC Aerospace Life support Industries LTD
Proceedings - Annual SAFE Symposium (Survival and Flight Equipment Association) | Year: 2014

This paper describes development of the large-scale single-arm centrifuge with the maximum average acceleration charge rate of 10g/s and a gyration radius of 8m, which is to be used for demonstrating adaptability, structural characteristics and dynamic performance of the aviation life-support equipment under stable and dynamic acceleration conditions of aircraft. The study was consisted with three major tasks: I) the jib arm support used an integrated box-type beam structure to ensure that its rigidity and strength are optimally matched with the rotary inertia; 2) three-axis rolling pod and free swinging pod were designed to ensure that the centrifuge is not only capable of conducting object tests but also has the basic functions of aeronautical and astronautic human centrifuge; 3) the high-precision velocity servo system was design by using combination control mode of acceleration-rotating velocity-torque closed loop control, torque forward-feedback control and variable parameter PID, to ensure that lower acceleration overshoot is controlled under the rotary inertia of 30×104kg-m2 and to meet the requirements of accurate simulation under aircraft acceleration conditions and aviation life-support equipment performance evaluation. Approximately, when the performance tests of the rocket-assisted ejection seat restriction system were conducted by the centrifuge, it verified effect of restriction units and harness system on pilot under different flight attitude conditions. As results, the large scale centrifuge provides important platforms for the performance verification test of the aviation life-support equipment under all the acceleration conditions.


Zhu E.,Nankai University | Sun Q.,Nankai University | Tan P.,Nankai University | Chen Z.,Nankai University | And 2 more authors.
Nonlinear Dynamics | Year: 2014

Powered parafoil is a kind of flexible wing vehicle, which is composed of traditional parafoil system and power plant. Considering the relative motion of canopy and payload, two coordinates are built separately to analyze the motion properties of canopy and payload. According to the Kirchhoff motion equation, eight degrees of freedom (DOF) dynamic model of powered parafoil is built, including six DOF motion of canopy and relative yaw and relative pitch motion of payload. The simulation focuses on the basic motions of gliding, turning, flare landing and the responses to the wind and power. The simulation results verify the validity of dynamic model of powered parafoil. © 2014, Springer Science+Business Media Dordrecht.


Pu Q.,North University of China | Zhen Y.,North University of China | Rui S.,AVIC Aerospace Life Support Industries. Ltd.
Journal of Information and Computational Science | Year: 2015

A numerical simulation model for the airbags landing system is developed by using control volume method to research the cushioning performance of the airbag landing system and analysis the affect of the typical external factors on the buffer characteristics. A series of experiments were conducted to verify the validity of the simulation model by comparing the calculation results and test data. By analyzing the simulation results, the influence of external factors on cushioning buffer are obtained. From the results we can see that the affect of the important factors such as the weight of airdropped loads, landing velocity and the altitude of landing site are significant. Based on the simulation model, the environmental adaptability of the airbags buffer system was analyzed too. Some suggestions for the adaptability of the airbags buffer system are provided and its cushioning characteristics are estimated. Copyright © 2015 Binary Information Press.


Zhao Y.,Beihang University | Hu C.,AVIC Aerospace Life Support Industries LTD. | Shen H.,Beihang University | Ma D.,Beihang University | And 2 more authors.
Earth Science Informatics | Year: 2012

With the rapid development of the World Wide Web, remote sensing (RS) data have become available to a wider range of public/professional users than ever before. Web Map Services (WMSs) provide a simple Web interface for requesting RS data from distributed geospatial databases. RS data providers typically expect to provide lightweight WMSs. They have a low construction cost, and can be easily managed and deployed on standard hardware/software platforms. However, existing systems for WMSs are often heavyweight and inherently hard to manage, due to their improper usage of databases or data storage. That is, they are not suitable for public data services on the Web. In addition, RS data are moving toward the multi-dimensional paradigm, which is characterized by multi-sensor, multi-spectral, multi-temporal and high resolution. Therefore, an efficient organization and storage approach of multi-dimensional RS data is needed for lightweight WMSs, and the efficient WMSs must support multi-dimensional Web browsing. In this paper, we propose a Global Remote Sensing Data Hierarchical Model (GRHM) based on the image pyramid and tiling techniques. GRHM is a logical model that is independent upon physical storage. To support lightweight WMSs, we propose a physical storage structure, and deploy multi-dimensional RS data on Web servers. To further improve the performance of WMSs, a data declustering method based on Hilbert space-filling curve is adopted for the distributed storage. We also provide an Open Geospatial Consortium (OGC) WMS and a Web map system in Web browsers. Experiments conducted on real RS datasets show promising performance of the proposed lightweight WMSs. © 2012 Springer-Verlag.


Chen B.,Beihang University | Xu H.,AVIC Aerospace Life Support Industries LTD | Xu Z.,AVIC Aerospace Life Support Industries LTD | He W.,Beihang University
Aerodynamic Decelerator Systems Technology Conferences | Year: 2015

A ballute is an inflatable, aerodynamic drag device and can provide efficient drag in a wide speed regime. In this paper, two ballute shapes have been proposed and studied in order to obtain relatively optimum configuration with maximum drag. This study simulates the flow fields of the optimum ballute configuration to investigate its aerodynamic performance at Mach numbers from 0.3 to 2.0. The burble fence and the air inlets are important components of a ballute whose effects on the decelerating performance were considered as well. © 2015, AIAA American Institute of Aeronautics and Astronautics. All rights reserved.


Tao J.,Nankai University | Sun Q.,Nankai University | Zhu E.,Nankai University | Chen Z.,Nankai University | He Y.,AVIC Aerospace Life Support Industries Ltd.
Harbin Gongcheng Daxue Xuebao/Journal of Harbin Engineering University | Year: 2016

Trajectory planning is the core task in the autonomous homing of a parafoil system. In this paper, we establish a mathematical model for homing trajectory planning, and present an optimal homing trajectory planning method for parafoil systems based on an improved quantum genetic algorithm. In this method, we first adopt a non-uniform B-spline curve to fit the control law, so as to transform the problem of the optimal control of trajectory planning into a parameter optimization problem of the control vertices of the B-spline basis function. Then, using the improved quantum genetic algorithm, we optimize the objective function, and plan the homing trajectory of the parafoil system. We conducted simulation experiments under different initial states in the real environment. The results show that the method is effective for homing trajectory planning, and the obtained optimized control laws and homing trajectories meet the homing control feature requirements of parafoil systems. © 2016, Harbin Institute of Technology. All right reserved.


Wang C.,Nanjing University of Aeronautics and Astronautics | Sun J.,Nanjing University of Aeronautics and Astronautics | Yu D.,AVIC Aerospace Life Support Industries Ltd.
Nanjing Hangkong Hangtian Daxue Xuebao/Journal of Nanjing University of Aeronautics and Astronautics | Year: 2013

The mass-spring damper model is used to analyze the effect factors on drag parachute deployment, including resistance area, elastic modulus and diameter of the parachute system, etc. Results show that drag parachute duration and the maximum falling distance decrease with the increase of deploy velocity. But system tension becomes larger by increasing the deploy velocity (200-300 km/h). Both the increase of pilot chute resistance area and the decrease of parachute system linear density can decrease the deployment duration and the maximum falling distances obviously. The effects on the trajectory of deployment, caused by elastic modulus and diameter of parachute system are insignificant. The key factors affecting drag parachute deployment are resistance area of pilot chute, deploy velocity and linear density of parachute system. Results provide analytical basis for engineering design of drag parachute system in aerospace industry.

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