The aerodynamic model of the embedded flight parameter sensing system (FADS) is briefly introduced, and the algorithm implementation of the system is described in detail using the X-33 aircraft of the United States as an example. The verification method of the FADS system is designed, and the verification results under another FADS system structure are listed. The results show that the calculation results of this flight parameter sensing system can meet the design requirements of the aircraft compared with the rigid results of the wind tunnel experiment.
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