Hongqing Lv

The control of aeroelastic response of a wing section with influence of the fuel sloshing in external tank is examined through analytical studies. Based on the simplified mass-spring-damper equivalent mechanical model of the liquid sloshing and the dynamic modeling method of the wing/store system, the aeroelastic model of the two-dimensional wing/external tank/fuel sloshing system is established in this paper. The aeroelastic instability of the system is studied, and a flutter suppression controller is designed based on linear active disturbance rejection control (LADRC). The stability analysis shows that the tracking error and the estimation error of the linear state observer (ESO) are convergent. It is shown through simulation results that wing flutter suppression under the interference of fuel sloshing and external tank vibrating can be achieved by using two control surfaces.

In this paper, the problem of ABS composite controller design based on optimal slip ratio is studied. First, the design objectives of ABS controller are proposed by taking the characteristics of braking process into account, and then, a practical composite controller is presented by combining robust and the logical threshold control schemes and the corresponding design approach is given. Finally, the composite controller is implemented on a single-wheel ABS system and the experiments are carried out under two kinds of road conditions. The results show that the actual slip ratio is kept near the optimal slip ratio under the composite controller. Thus, the proposed composite controller is feasible and valid.