基于翼面压力的飞行器气动力感知技术与自由飞验证

doi:10.7527/S1000-6893.2020.24138

Abstract

Abstract: The complex flow around the aircraft at high Angle of Attack (AOA) will lead to uncommanded motions, seriously damaging the maneuverability and flight safety of the aircraft. Since the existing airborne equipment with inertial core components is unable to provide unsteady aerodynamic parameters, real-time perception of the unsteady aerodynamic force/moment of aircraft at high AOA, which is the core of restraining uncommanded motions, will be one of the key problems in aerodynamics and flight control in the future advanced aircraft design. To solve these problems, this paper proposes a new method to estimate the unsteady aerodynamic moment of the whole aircraft at high AOA based on the distributed pressure to obtain the rolling moment coefficient C_lsec of the characteristic section, and then to judge the rolling motion of the aircraft. The results of wind tunnel and flight experiments show that for the 80°/48° double delta wing, the 0.8c characteristic cross section C_lsec has a correlation with the rolling moment of the model; when the aircraft is flying at high AOA, the rolling moment coefficient C_lsec increases considerably; C_lsec can predict the rolling motion trend of the model ahead of time compared with the inertial sensor, thus providing valuable data foundation for the suppression of uncommanded motions at high AOA.

Key words: aerodynamic perception, uncommanded motion, wing roll, double delta wings, pressure distribution, wind tunnel tests, free flights

CLC Number:

V211.7

CHEN Yin, GU Yunsong, SUN Zhijun, HUANG Zi. Aerodynamic perception from distributed pressure and free flight test[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(3): 124138-124138.

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Aerodynamic perception from distributed pressure and free flight test

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