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Chen G.-Q.,The Institute of Aerodynamics Theories and Application of China Academy of Aerodynamic of Aerospace | Wang G.-D.,The Institute of Aerodynamics Theories and Application of China Academy of Aerodynamic of Aerospace | Chen B.-Y.,The Institute of Aerodynamics Theories and Application of China Academy of Aerodynamic of Aerospace | Zhou W.-J.,The Institute of Aerodynamics Theories and Application of China Academy of Aerodynamic of Aerospace | And 2 more authors.
Yuhang Xuebao/Journal of Astronautics | Year: 2015

The flush air data sensing (FADS) system technology was researched by using mature and low cost supersonic(Ma>3) rocket projectile platform flight test for the first time in domestic. According to the key technology problems of algorithm for FADS solving and measurement system and the error influence, that FADS solving algorithm was built based on neural network technology and flight test scheme was designed, and the flight test and data analysis were done. Research results showed that the FADS algorithm based on neural network technique had good reliability and precision; The measurement results were basically consistent with the radar measurements results, which verified the algorithm design. The FADS measurement results relative to the radar measurement results, average relative error of static pressure was 5.2% and the maximum relative error was 18.8%; the average relative error of Ma number was 4.2% and the maximum relative error was 14.9%; FADS measurement results of attack angle and side slip angle were close to the results theoretic trajectory. The research results could provide reference for the relative study of flight test technology. © 2015, Editorial Dept. of JA. All right reserved.


Chen G.,The Institute of Aerodynamics Theories and Application of China Academy of Aerodynamic of Aerospace | Bai P.,The Institute of Aerodynamics Theories and Application of China Academy of Aerodynamic of Aerospace | Zhan H.,The Institute of Aerodynamics Theories and Application of China Academy of Aerodynamic of Aerospace | Ji C.,The Institute of Aerodynamics Theories and Application of China Academy of Aerodynamic of Aerospace
Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica | Year: 2015

For the layout design of an Unmanned Air Vehicle (UAV) with propeller engine, application of three dimensional numerical simulation method on the slipstream aerodynamic effect is investigated based on Multiple Reference Frame (MRF) model. The reseach results shown that the flow field of the MRF model is consistent with true propeller flow, and MRF simulates aerodynamic interference accurately. The influence of propeller slipstream on the aerodynamic performance of an UAV at the status of taking off is most significant, becomes weaker at the status of climbing and the least at the status of cruising. The influence of propeller slipstream is enhanced with the increment of propeller thrust and keeps nearly the same if two sets of propeller who have same thrust but different blade attack angle. The pressure drag on the afterbody of the UAV fuselage increases rapidly because of the effect of propeller slipstream flow, deteriorates the aerodynamic performance of the UAV evidently. ©, 2015, Editorial Office of ACTA AERODYNAMICA SINICA. All right reserved.

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