Abstract
Several new systematic methods for high fidelity and reliability calculation of static and single dynamic derivatives are proposed in this paper. Angle of attack step response is used to obtain static derivative directly; then translation acceleration dynamic derivative and rotary dynamic derivative can be calculated by employing the step response motion of rate of the angle of attack and unsteady motion of pitching angular velocity step response, respectively. Longitudinal stability derivative calculations of SACCON UCAV are taken as test cases for validation. Numerical results of all cases achieve good agreement with reference values or experiments data from wind tunnel, which indicate that the proposed methods can be considered as new tools in the process of design and production of advanced aircrafts for their high efficiency and precision.
Highlights
How to determine an aircraft’s stability characteristics at the boundary of flight envelope is one of the most complicated and important aspects in the process of advanced aircraft design, as well as the aerodynamic and flight dynamic analysis
For slow motion at low angle of attack, velocities and control angles that can model the aerodynamic loads independently are often called the static derivatives, while their rates used to calculate the stability at higher angle of attack and rates are called dynamic derivatives
The corresponding applications are limited by blockage, scaling, and Reynolds number effects together with support interference issues that prevent the proper modeling of the full-scale vehicle behavior [5]
Summary
How to determine an aircraft’s stability characteristics at the boundary of flight envelope is one of the most complicated and important aspects in the process of advanced aircraft design, as well as the aerodynamic and flight dynamic analysis. The dynamic stability indicates the property that the vehicle recovers to its original position after disturbance with dynamic damping moments in terms of time response process Both the static and dynamic stabilities play vital roles in flight control system design and aerodynamic optimization. Ronch et al [6, 7] presented a time-domain solver to compute dynamic derivatives of full aircraft configurations They investigated the longitudinal stability derivatives of the Standard Dynamic Model (SDM) and the Transonic Cruiser (TCR) by using the Fourier integral and linear regression mathematical model. Different from conventional ways, the new methods are recommended for their high precision and computational efficiency, and the high fidelity and reliability single dynamic derivatives could be obtained They can be generalized to the lateral and directional stability derivatives simulation
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