Shanghai Institute of Spacecraft Equipment

Shanghai, China

Shanghai Institute of Spacecraft Equipment

Shanghai, China
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He Y.,Soochow University of China | Yao R.-J.,Soochow University of China | Xiao Y.,Shanghai Institute of Spacecraft Equipment | Yuan G.-Z.,Soochow University of China | And 3 more authors.
Journal of Chinese Mass Spectrometry Society | Year: 2017

Printed-circuit-board voltage-divided ion trap (PCBVDIT) is a novel mass analyzer with simple electrode structure, mainly composed of printed circuit boards. PCBVDIT is a good choice for the analyzer of miniaturized ion trap mass spectrometer for the reason that PCBVDIT has a compact size, easy process and assembly technology and low cost. The operation mode and geometry structure of a prototype PCBVDIT were improved in order to enhance its analytical performance. The internal electric field distribution of PCBVDIT was calculated by PAN_33. Ion trajectories inside the PCBVDIT and simulated mass spectrum peaks for different electrode structures besides different operation modes were both simulated by software SIMION and AXSIM. The ions used in the simulation experiments were m/z 4 000, 4 001 and 4 002. It shows that different voltage-divided ratios of supplement resonance signal has a significant influence on the resolving power of PCBVDIT, even though the voltage-divided ratio of radio-frequency trapping waveform remains unchanged. With the reduction of voltage-divided ratio of supplement resonance signal, mass resolution could be improved. In the limit case, mass resolution would be improved by about 25% when the supplement resonance signal was only applied to the central electrode, that is, the voltage-divided ratio of supplement resonance signal was equal to zero. On the other hand, enhanced performance, with a mass resolution up to 10 325 for the ions which had the mass-to-charge ratio of 4 001, could be acquired on the structure-optimized PCBVDIT by removing the corner electrodes from the prototype. These simulated results could provide a theoretical foundation for further investigations. © 2017, Editorial Board of Journal of Chinese Mass Spectrometry Society. All right reserved.


Liu Y.,Harbin Institute of Technology | Wang C.,Harbin Institute of Technology | Wang C.,Key Laboratory of Microsystems and Microstructures Manufacturing HIT | Han H.,Shanghai Institute of Spacecraft Equipment | And 4 more authors.
International Journal of Advanced Manufacturing Technology | Year: 2017

Investigations have revealed that size effect obviously affects forming quality and accuracy of micro parts. However, to find effective approaches that can reduce the influence of size effect is still a critical problem to be solved. Ultrasonic vibration has been widely used in industrial metal forming recently, and it has been proved that it is helpful for improving section quality compared with conventional blanking. In this study, micro-blanking process was carried out with a specially developed device. The square holes of copper foil T2 were investigated by analyzing the evolution of microstructure, crack initiation, quality of shearing surface, etc. Inhibition of crack initiation is found due to the softening effect in ultrasonic vibration assisted micro-blanking by analyzing section obtained under different ratios of blanking stroke to thickness (h/t), which increases the ratio of smooth zone. The analysis of microstructure in deformation area shows that a shearing deformation area becomes smaller, and radius of fillet decreases. Surface roughness of smooth zone decreases with ultrasonic vibration due to polishing effect. Compared with traditional micro-blanking, this compound plastic forming technology applying ultrasonic vibration on the punch can improve the section surface quality by increasing the ratio of smooth zone, and decreasing the surface roughness and fillet radius. The experimental outcomes reveal the mechanism of shearing deformation behavior during ultrasonic vibration assisted micro-blanking process of copper foil and the findings confirm that ultrasonic vibration can be regarded as a way to improve the forming quality of micro-blanking. © 2017 Springer-Verlag London Ltd.


Liu G.,Shanghai Institute of Spacecraft Equipment | Liu G.,Shanghai Space Environment Simulation and Verification Engineering Technology Research Center | Zhang L.,Shanghai Institute of Spacecraft Equipment | Zhang L.,Shanghai Space Environment Simulation and Verification Engineering Technology Research Center | Jiang J.,Shanghai Institute of Spacecraft Equipment
Astrophysics and Space Science Proceedings | Year: 2017

The diglycidyl ether of bisphenol A/dicyandimide (DGEBA/DICY) films were tested using 160 keV electron irradiation simulation facility. The degradation mechanism of the irradiated DGEBA/DICY was analyzed using EPR, FT-IR, and XPS. The kinetic process of irradiation induced degradation of DGEBA/DICY was expressed quantitatively based on the data from FT-IR and XPS. The relationship between the micro-mechanism and the macro-property was proposed that allowed describing the property variation of DGEBA/DICY with electron irradiation fluence. © Springer International Publishing AG 2017.


Qin W.,Harbin Institute of Technology | Pan Y.,Shanghai Institute of Spacecraft Equipment
RSC Advances | Year: 2015

Electron irradiation in outer space causes severe damage to the polymer materials of spacecrafts. An effective approach to prevent such damage is to incorporate nanoparticles into the polymeric materials. Herein, we fabricated modified cyanate ester (CE) and carbon/CE composites by the incorporation of reduced graphene oxide-TiO2 (rGO-TiO2) nanoparticles and studied their resistance performance to electronic radiation. Compared with the carbon/TiO2/CE composite, the interlayer shear strength of the resulting carbon/rGO-TiO2/CE composite increased by 10.4% and its mass loss reduced by 16.5%. Scanning electron microcopy (SEM) images showed that there are more cracks at the fiber and resin interfaces of carbon/CE than at the interfaces of carbon/rGO-TiO2/CE after irradiation. X-ray photoelectron spectroscopy (XPS) investigation showed that irradiation with 160 keV electrons could break the chemical bonds at the surface layer of the pristine CE resin, which is effectively prevented by the incorporation of rGO-TiO2 nanoparticles. © The Royal Society of Chemistry 2015.


Bo Z.,Shanghai Institute of Spacecraft Equipment | Bo Z.,Shanghai Space Environment Simulation & Verification Engineering Technology Research Center | Gang L.,Shanghai Institute of Spacecraft Equipment | Gang L.,Shanghai Space Environment Simulation & Verification Engineering Technology Research Center | And 3 more authors.
Astrophysics and Space Science Proceedings | Year: 2017

As an essential part of the spacecraft thermal control system, thermal control coatings are widely used. In this paper, nanometer modification technology for spacecraft thermal control coatings is studied. Sol-Gel technology is used to add nano-SiO2 into thermal control coating system, where TEOS is used as the precursor of SiO2, in order to modify the binder and the filler of the coating system. The thermal control coatings were characterized by FTIR, PL and optical properties testing, both before and after proton irradiation, which has a significant applied background in engineering and theoretical research importance. The test results prove that the nano modified coating has well established optical properties (αs < 0.2) and radiation stability. After 90 keV proton irradiation, Δαs of the nano modified coating is reduced to 0.12. The stability improves almost 50 % as compared to ordinary ZnO white paint. The main reason why the performance of nano modified coating degrades is that defects are formed in ZnO during the irradiation, according to the analysis. Modified ZnO powder can effectively eliminate the variations and quantities of irradiation defects, such as oxygen vacancies. This not only improves the proton irradiation stability of ZnO powder, but also effectively reduces the absorbed oxygen content in the coating system, thereby, lowering the damage to chemical bonds in the adhesives. © Springer International Publishing AG 2017.


Wang Z.,University of Chinese Academy of Sciences | Zhao K.,Shanghai Institute of Spacecraft Equipment | Chen W.,Shanghai Institute of Spacecraft Equipment | Chen X.,Shanghai Institute of Spacecraft Equipment | Zhang L.,University of Chinese Academy of Sciences
Applied Thermal Engineering | Year: 2013

Tungsten is remarkable for its robustness; especially it has the highest melting point of all the non-alloyed metals. Tungsten and tungsten alloys have been widely used in aerospace, weapon, nuclear industries and fusion reactor. Tungsten is expected to become fusion reactor first wall material for this reason. In this paper, phase transformation processes of fusion reactor first wall material tungsten have been investigated via molecular dynamics simulation based on the modified embedded atom model. Surface melting velocities at different temperatures are calculated as V(T) = -5.082 + 0.00136T and thermodynamic melting point is determined by fitting front advance velocities. Structure changes, thermal expansion coefficient, radial distribution function, static structure factor and average atomic energy for uniform melting processes are studied to simulate plasma thermal shock heating to superheat state of tungsten in fusion reactor. The superheat limit of tungsten crystals can be gotten according to simulation results. The superheat limit for tungsten crystal melting is about 27.2%. Tungsten is the best plasma-facing material because of its highest melt point and highest limiting superheating of all the non-alloyed metals. © 2013 Elsevier Ltd. All rights reserved.


Wang Z.,University of Chinese Academy of Sciences | Zhao K.,Shanghai Institute of Spacecraft Equipment | Chen W.,Shanghai Institute of Spacecraft Equipment | Chen X.,Shanghai Institute of Spacecraft Equipment | Zhang L.,University of Chinese Academy of Sciences
Applied Thermal Engineering | Year: 2014

Tungsten is remarkable for its robustness, especially it has the highest melting point of all the non-alloyed metals. Metallic material tungsten and tungsten alloys have been widely used in aerospace, weapon, nuclear industries and fusion reactor. Tungsten is expected to be the fusion reactor first wall material for this reason. In this paper, self-diffusion coefficients of metallic material tungsten have been investigated via molecular dynamics simulation method using the modified embedded atom potential model. Diffusion activation energy of tungsten can be gotten according to Arrhenius relation between the self-diffusion coefficients simulation results and temperatures. The dipole interaction model is introduced to analyze metallic material tungsten self-diffusion process in a uniform magnetic field. The strong magnetic field increases diffusion activation energy by 34.52% and limits self-diffusion coefficient by 1.15% in 2 T uniform magnetic field. © 2014 Elsevier Ltd. All rights reserved.


Wen X.,Shanghai Institute of Spacecraft Equipment | Wen X.,Zhejiang University | Chen Z.-W.,Zhejiang University | He H.-N.,Zhejiang University
Zhendong yu Chongji/Journal of Vibration and Shock | Year: 2014

A continuous contact force model was built in order to investigate joint clearance effects on the dynamics of two-axis hydraulic vibration test system. The test system with clearance joint was imported into the software ADAMS for dynamic simulation, and an experimental set-up was designed and built to achieve some experimental validations under the simple harmonic excitation inputs with different phases. The results indicate that the coupling vibration effect between two exciters leads to the apparent fluctuation of steady response of accelerations in the case of certain clearance size and with excitations out of phase, meanwhile, the rapid increase of peak acceleration happens when the excitation frequency and excitation amplitude increase. Thus, the selection of appropriate clearance size in revolute joint for two-axis hydraulic vibration test system is a crucial step for eliminating the non-linear influence.


Liu C.-L.,Northwestern Polytechnical University | Zhu H.-R.,Northwestern Polytechnical University | Zhang X.,Shanghai Institute of Spacecraft Equipment | Xu D.-C.,Northwestern Polytechnical University | Zhang Z.-W.,Northwestern Polytechnical University
International Journal of Heat and Mass Transfer | Year: 2014

Film cooling performances of the cylindrical film holes and the laid-back film holes on the turbine blade leading edge model are investigated in this paper. Experimental measurements have been carried out to investigate the influence of the inclined angle in the spanwise direction (i.e. radial angle for a blade in the engine) on the film cooling performances of these two kinds of holes. Three rows of holes are arranged in a semi-cylinder model which is used to model the blade leading edge. Two inclined angles and three blowing ratios are tested. Transient heat transfer measurement technique with double thermochromic liquid crystals is employed in the present experiment. The results show that the trajectory of the film jets in the leading edge region deviates from the mainstream direction to the spanwise direction gradually as the blowing ratio increases. Under large blowing ratio, more area can benefit from the film protection and the film cooling effectiveness distribution is more uniform than those under small blowing ratio, while the heat transfer coefficient is also higher. The basic distribution features of heat transfer coefficient are similar for all the tested models. The heat transfer coefficient in the region where the jet core flows through is relatively lower, while the heat transfer coefficient in the jet edge region is relatively higher. Compared with the cylindrical holes, the jets from the laid-back holes have better film coverage and meanwhile make more area have relatively higher heat transfer coefficient, especially under large blowing ratio. Under the same blowing ratio, the jets from film holes with small radial angle can attach on the wall surface better and give higher film cooling effectiveness in the region close to the hole exit than the film holes with large radial angle, while they also produce relatively higher heat transfer coefficient. © 2013 Elsevier Ltd. All rights reserved.


Hou P.,Shanghai Institute of Spacecraft Equipment | Li Z.,Shanghai Institute of Spacecraft Equipment | Song T.,Shanghai Institute of Spacecraft Equipment | Chen L.,Shanghai Institute of Spacecraft Equipment
Harbin Gongye Daxue Xuebao/Journal of Harbin Institute of Technology | Year: 2016

In order to decrease satellite attitude turnover and guarantee high-accuracy pointing for satellite optical payload, a novel method is designed for horizontal deployment experiment of satellite solar array. A multi-degree-of-freedom balance weight strategy is used to counterbalance the gravity. Firstly, the kinematics model and dynamics model are established. Then, the error analysis is deduced. Finally, the experiment is carried out. The experimental results show that the method can truly simulate the micro-gravity in-orbit environment compared with the previous method. Moreover, it is very strict with mass deviation and centroid deviation of solar array and the system frictions. The results indicate that the model and test methods are correct and meet the test requirements. © 2016, Editorial Board of Journal of Harbin Institute of Technology. All right reserved.

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