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Shanghai, China

The Shanghai Aircraft Design and Research Institute , previously known as Shanghai Aircraft Research Institute , is a Chinese design institute, part of the ACAC consortium. Founded in the 1970s as First Aircraft Design Institute Shanghai Branch it became a part of ACAC in 2002 and was renamed Shanghai Aircraft Design and Research Institute in 2009. The design institute's head office is located at 5 Yunjin Road next to Longhua Airport in the Xuhui District of Shanghai.SADRI has done liaison engineering and airworthiness test for MD-82 and MD-90 airliners. Wikipedia.

Zhu L.,Shanghai Aircraft Design and Research Institute
Chinese Journal of Aeronautics | Year: 2013

This research focused on how to improve damage resistance of carbon fiber laminates. It was carried out at Cranfield University Composites Centre, Milton Keynes, UK as an MSc by research thesis project. A series of low-cost composite laminates, with or without novel veils provided by Tenax, was manufactured using current aircraft carbon fiber preforms via vacuum infusion (VI) molding in this research. All the investigations on damage resistance of these panels were carried out according to the British Standard (BS ISO 18353:2009). Initial damage was induced using a falling weight apparatus mounting a 16 mm hemispherical tip. C-scan and Micrograph were employed to reveal damage characteristics. Finally, both compression after impact (CAI) and plain compression strength were experimented. The behaviors of these panels, including damage size, damage construction, residual compression strength, and compression strength reduction, were utilized to investigate how and to what extent the veils affected the damage resistance. The results show that using veils is an efficient method of improving the damage resistance of the laminates studied. Maximum 32% increase in residual compression strength is achieved via veils accompanying with 7% increase in cost. © 2013 Production and hosting by Elsevier Ltd. on behalf of CSAA & BUAA. Source

Chen G.,Shanghai Aircraft Design and Research Institute
Wuhan Ligong Daxue Xuebao (Jiaotong Kexue Yu Gongcheng Ban)/Journal of Wuhan University of Technology (Transportation Science and Engineering) | Year: 2016

According to the flow control theory of 2D-airfoil, blowing seamless flap is generated by applying jetting-nozzle on seamless flap, which is able to improve the maximum lift coefficient (CL, max). To ensure the feasibility of this technology, CFD simulation is conducted to calculate CL, max due to different blowing angle θ, nozzle height h and blowing velocity v with the method of “Control Variables”. After that, the method of “genetic algorithm” combined with the mathematical model is utilized for design and optimization. The result illustrates that CL, max is obviously improved by applying technology of “blowing flaps”. Such innovative concept can be used in following research of civil aircraft high-lifting devices. © 2016, Editorial Department of Journal of Wuhan University of Technology. All right reserved. Source

Liang E.,Shanghai Aircraft Design and Research Institute
Jinshu Rechuli/Heat Treatment of Metals | Year: 2015

Hot compression deformation behavior of Ti-2Al-9.2Mo-2Fe alloy compressed at 850-1000 ℃ with strain rates 0.01-10 s-1 was conducted by Gleeble-1500 thermal simulator. The results show that serrated β grain boundaries and elongated β grains can be found in the alloy after hot compressed. At low strain rates(0.01 s-1 and 0.1 s-1), large amount of low angle grain boundaries form along serrated grain boundaries, accompanying with small amounts of recrystallized β grains. But at high strain rates(1 s-1and 10 s-1), large amount of recrystallized grains form along original β grain boundaries. During hot compression, the alloy presents different phenomena of strain hardening or softening with the increase of strain rates after yield. When the alloy deformed at high strain rates, a significant rheological hardening can be found, as well as periodic fluctuations. Moreover, with increasing strain, rheological softening is found in the compress with 10 s-1, but is not found in condition of 1 s-1. However, when the alloy deformed at 950 ℃ and 1000 ℃ with low strain rates, rheological static stage can be found after yielding without any noticeable hardening or softening. While compressed at 850 ℃ and 900 ℃ with the same strain rates, yielding followed by slight rheological hardening is observed. ©, 2015, Chinese Mechanical Engineering Society of Heat Treatment. All right reserved. Source

Zhang R.,Shanghai Aircraft Design and Research Institute
Jinshu Rechuli/Heat Treatment of Metals | Year: 2015

Ti-6Al-4V titanium alloy extruded profiles with extruding ratio of 25 or 85 were prepared and then anealed or double anealed to investigate the effect of heat treatment on microstructure and mechanical properties. The results show that Ti-6Al-4V extruded profiles exhabit good adaptability of heat treatment, the microstructure and the value of ultimate strength, elongation and the reduction of area show little variations with the temperature, soaking time or the number of treatment cycles when anealed below 750 ℃ and within 3 h. The yield strength of the profiles can be improved by double annealing. ©, 2015, Chinese Mechanical Engineering Society of Heat Treatment. All right reserved. Source

Zhang D.-N.,Shanghai Normal University | Shangguan Q.-Q.,Shanghai Normal University | Xie C.-J.,Commercial Aircraft Corporation of China | Liu F.,Shanghai Aircraft Design and Research Institute
Journal of Alloys and Compounds | Year: 2014

The dynamic mechanical behaviors of 7075-T6 aluminum alloy at various strain rates were measured by dynamic tensile tests using the electronic universal testing machine, high velocity testing system and split Hopkinson tensile bar (SHTB). Stress-strain curves at different rates were obtained. The results show that the strain rate hardening effect of 7075-T6 aluminum alloy is significant. By modifying the strain rate hardening term in the Johnson-Cook constitutive model, a new Johnson-Cook (JC) constitutive model of 7075-T6 aluminum alloy was obtained. The improved Johnson-Cook model matched the experiment results very well. With the Johnson-Cook constitutive model, numerical simulations of tensile tests at different rates for 7075-T6 aluminum alloy were conducted. According to tensile loading and stress-strain relation of 7075-T6 aluminum alloy, calculation results were compared with experimental results. Accuracy of the modified Johnson-Cook constitutive equation was further proved. © 2014 Elsevier B.V. All rights reserved. Source

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