Comparative study on the aeroservoelastic stability analysis for slender body aircraft
In order to effectively avoid the closed-loop system instability problem caused by the coupling of unsteady aerodynamics,body structure,and control system in the aircraft design process,and to meet the requirements of aeroservoelastic stability analysis for slender body aircraft,an aeroservoelastic stability analysis method for slender body aircraft is established based on aerodynamic derivative method and engineering panel method.Taking a slender body aircraft as research object,the deviation of two methods at subsonic state and supersonic state are within 2 dB.The deviation of two methods at hypersonic state are over 10 dB.It is recommended to adopt aerodynamic derivative method to achieve higher accuracy at hypersonic state.
slender body aircraftaeroservoelasticstabilityaerodynamic derivative methodengi-neering panel methodsubsonichypersonic