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For some hypersonic flight vehicles with sharp wedged fore-bodies,especially for those which are used to verify supersonic combustion ramjet engine technology,the precision of angle of attack cannot be achieved only through inertial navigation system(INS).The aerodynamic model for flush air data sensing system(FADS) is built based on the surface pressure distribution obtained through the pressure orifices laid on specific positions of the surface,and the flight parameters,such as angle of attack,are inferred from the aerodynamic model.Therefore,FADS system can be applied in hypersonic flight vehicles with sharp wedged fore-bodies together with INS.Theory model for FADS/INS integrated system is built based on oblique shock wave theory,and its working principles and calibration procedures are also presented.
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Basic Information:
DOI：10.16358/j.issn.1009-1300.2012.06.012
China Classification Code:V448
Citation Information:
[1]Wang Peng,Jin Xin,Zhang Weimin(China Academy of Aerospace Aerodynamics,Beijing 100074,China).Fusion Method for FADS/INS Integrated System[J].Tactical Missile Technology,2012,No.156(06):70-73.DOI:10.16358/j.issn.1009-1300.2012.06.012.
2012-11-15
2012-11-15