This paper presents the concept of dynamic wind tunnel testing using captive flight method, in which the airplane is supported by three elastic lines mainly in the vertical direction, and given oscillatory motions by an external actuator. This experimental method is designed for the aerodynamic parameter estimation. Longitudinal and lateral dynamic tests are carried out sweeping driving frequency, and every mode except surging motion, of which damping is weak, was excited. Aerodynamic parameters estimated from flight data showed good accordance with reference data. This experimental method has the advantages of the experimental simplicity, quite small aerodynamic interference, stable flight and the capability of the excitation of motion necessary for the estimation.
|Translated title of the contribution||Captive Flight Testing in a Wind Tunnel for Identification of Dynamic Characteristics of a Small-Sized UAV|
|Number of pages||8|
|Journal||日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences|
|Publication status||Published - Jun 5 2004|